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Cone

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• Geometry, Descriptive
• Geometry, Solid

• Two Geometrical Memoirs on the General Properties of Cones of the Second Degree and on the Spherical Conics, by M. Chasles (page images at Cornell)
• Effects of nose bluntness, fineness ratio, cone angle, and model base on the static aerodynamic characteristics of blunt bodies at Mach numbers of 1.57, 1.80, and 2.16 and angles of attack up to 180 ̊/ (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1963), by David S. Shaw, C. Donald Babb, Dennis E. Fuller, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Aerodynamic characteristics of towed spheres, conical rings, and cones used as decelerators at Mach numbers from 1.57 to 4.65 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1963), by Nickolai Charczenko, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Two geometrical memoirs on the general properties of cones of the second degree, and on the spherical conics, (Dublin, For Grant and Bolton ; [etc., etc.], 1841), by M. Chasles and Charles Graves (page images at HathiTrust)
• Ueber fusspunkten-curven auf der oberfläche eines geraden kreiskegels ... (Göttingen, Druck der Gebrüder Hofer, 1873), by Ad Stehle (page images at HathiTrust)
• Flight transition data for angles of attack at Mach 22 with correlations of the data / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1975), by Charles B. Johnson, Christine M. Darden, and Langley Research Center (page images at HathiTrust)
• Deployment and performance characteristics of 1.5-meter supersonic attached inflatable decelerators / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Herman L. Bohon, Robert Miserentino, James Wayne Sawyer, and Langley Research Center (page images at HathiTrust)
• Experimental studies of hypersonic boundary-layer transition and effects of wind-tunnel disturbances / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by P. Calvin Stainback and Langley Research Center (page images at HathiTrust)
• A study of methods which predict supersonic flow fields from body geometry, distance, and Mach number / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Robert J. Mack and Langley Research Center (page images at HathiTrust)
• Evaluation of flow properties behind 120-̊ and 140-̊included-angle cones and a Viking '75 entry vehicle at Mach numbers from 1.60 to 3.95 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Clarence A. Brown, James F. Campbell, and Langley Research Center (page images at HathiTrust)
• Subsonic and supersonic static aerodynamic characteristics of a family of bulbous base cones measured with a magnetic suspension and balance system / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1972), by Milan Vlajinac, Langley Research Center, and Massachusetts Institute of Technology (page images at HathiTrust)
• Aerodynamic heating and loading within large open cavities in cone and cone-cyclinder-flare models at Mach 6.7 / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by L. Roane Hunt and Langley Research Center (page images at HathiTrust)
• Discrete-vortex model for the symmetric-vortex flow on cones / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Thomas G. Gainer and Langley Research Center (page images at HathiTrust)
• An approximate method for calculating three-dimensional inviscid hypersonic flow fields / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. : For sale by the National Technical Information Service, 1990), by Christopher J. Riley, Fred R. DeJarnette, and Langley Research Center (page images at HathiTrust)
• Measured pressure distributions on large-angle cones in hypersonic flows of tetrafluoromethane, air, and helium / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Robert A. Jones, James L. Hunt, and Langley Research Center (page images at HathiTrust)
• Jet effects on the drag of conical afterbodies at spersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by William B. Compton and Langley Research Center (page images at HathiTrust)
• Comparison of the aerodynamic characteristics of an ablating and nonablating blunted conical body / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1973), by Robert L. Kruse and Ames Research Center (page images at HathiTrust)
• Effects of wall cooling and angle of attack on boundary-layer transition on sharp cones at M[mathematical symbol for infinity] = 7.4 (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972), by George G. Mateer, United States National Aeronautics and Space Administration, and Ames Research Center (page images at HathiTrust)
• A model for jet-noise analysis using pressure-gradient correlations on an imaginary cone / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by Thomas D. Norum and Langley Research Center (page images at HathiTrust)
• English and American furniture. (New York : Parke Bernet, 1939), by Parke-Bernet Galleries (page images at HathiTrust; US access only)
• Summary and correlation of skin-friction and heat-transfer data for a hypersonic turbulent boundary layer on simple shapes / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], [1969]), by Edward J. Hopkins, Thomas E. Polek, George C. Mateer, Earl R. Keener, Mamoru Inouye, Morris W. Rubesin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• The stabilizing effectiveness of conical flares on bodies with conical noses / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by Donn B. Kirk, Gary T. Chapman, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flow-field investigation for large-angle cones with short spikes at a Mach number of 9.6 / (Washington, D.C. : National Aeronautics and Space Administration, 1970), by W. Frank Staylor, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Hypersonic flow past blunt cones with consideration of the equilibrium physicochemical transformations, ([Washington] National Aeronautics and Space Administration; for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va., [1970]), by Vladimir Lunev, V. G. Pavlov, and K. M. Magomedov (page images at HathiTrust; US access only)
• A method for predicting pressures on elliptic cones at supersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by George E. Kaattari, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Experimental flow properties in the wake of a 120 ̊cone at Mach number 2.20 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va. 22151], 1969), by James F. Campbell, Josephine W. Grow, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Aerodynamic characteristics of a large-angle blunt cone with and without fence-type afterbodies / (Washington, D.C.: National Aeronautics and Space Administration:, 1971), by Kenneth W. McAlister (page images at HathiTrust; US access only)
• Convective heat-transfer rates on a blunted 110° cone with hemispherical afterbody at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by David A. Stewart, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Longitudinal and lateral-directional aerodynamic characteristics of a wing-cone configuration at Mach numbers from 2.5 to 4.5 / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Peter F. Covell, Dorothy T. Howell, Ira J. Walker, and Langley Research Center (page images at HathiTrust)
• Aerodynamic heating on the corrugated surface of a 10.2⁰ half-angle blunted cone at Mach 6.7 / (Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981), by Irving Weinstein, L. Roane Hunt, Don E. Avery, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• An experimental investigation of base heating on typical Mars entry body shapes / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service, 1971]), by O. L. Zappa, William G. Reinecke, Langley Research Center, and Avco Corporation. Systems Division (page images at HathiTrust)
• Fluctuating surface-pressure characteristics on slender cones in subsonic, supersonic, and hypersonic Mach-number flow / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1974), by H. Heller, Anthony R. Clemente, Langley Research Center, and Beranek Bolt (page images at HathiTrust)
• Longitudinal aerodynamic characteristics of two blunted cone reentry configurations at Mach numbers from 17.6 to 22.2 including some Reynolds number effects / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1966]), by Dal V. Maddalon and Langley Research Center (page images at HathiTrust)
• Experimental determination of the recovery factor and analytical solution of the conical flow field for a 20 ̊included angle cone at Mach numbers of 4.6 and 6.0 and stagnation temperatures to 2600 ̊R / (Washington : National Aeronautics and Space Administration, [1961]), by Frank A. Pfyl, Leroy L. Presley, and Ames Research Center (page images at HathiTrust)
• Experimental investigation of the transonic flutter of simple thin truncated-cone panels / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by Jean Gilman and Langley Research Center (page images at HathiTrust)
• A preliminary investigation of modified blunt 13° half-cone re-entry configurations at subsonic speeds / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by George C. Kenyon, George G. Edwards, and Ames Research Center (page images at HathiTrust)
• Convective heat transfer to a lifting flat-faced-cone entry body / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by James E. Terry and Ames Research Center (page images at HathiTrust)
• The lateral and directional aerodynamic characteristics of a re-entry configuration based on a blunt 13° half cone at Mach numbers to 0.90 / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by George C. Kenyon and Ames Research Center (page images at HathiTrust)
• The effects of boundary-layer removal through throat slots on the internal performance of a side inlet at Mach numbers of 2.0 and 2.3 / (Washington, D.C. : National Aeronautics and Space Administration, 1961), by John J. Gawienowski and Ames Research Center (page images at HathiTrust)
• Simulation of real-gas effects on pressure distributions for aeroassist flight experiment vehicle and comparison with prediction / (Washington, D.C. : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by John R. Micol and Langley Research Center (page images at HathiTrust)
• Effects of Reynolds number and model support on the supersonic aerodynamic chacteristics of a 140° included-angle cone / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service [distributor], 1974), by Charles D. Trescot, Dorothy T. Howell, Clarence A. Brown, and Langley Research Center (page images at HathiTrust)
• Aerodynamic investigation of sharp cone-cylinder spikes on 120 ̊blunted cones at Mach numbers of 3.00, 4.50, and 6.00 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1969), by Robert J. McGhee, W. Frank Staylor, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Static longitudinal aerodynamic characteristics of some supersonic decelerator models at Mach numbers of 2.30 and 4.63 / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1969), by Edwin E. Davenport, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1968]), by George E. Kaattari and Ames Research Center (page images at HathiTrust)
• Hypersonic viscous drag on cones in rarefied flow / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1967), by M. I. Kussoy, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Heat-transfer and temperature distribution of a conical porous membrane during planetary entry / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1967]), by Latif M. Jiji and Ames Research Center (page images at HathiTrust)
• Pressure distributions on 140, ̊ 160, ̊ and 180 ̊cones at Mach numbers from 2.30 to 4.63 and angles of attack from 0 ̊to 20 ̊/ (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1969), by James F. Campbell, Dorothy H. Tudor, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Configuration factors for exchange of radiant energy between axisymmetrical sections of cylinders, cones, and hemispheres and their bases / (Washington : National Aeronautics and Space Administration, [1961]), by Albert J. Buschman, C. M. Pittman, and Langley Research Center (page images at HathiTrust)
• An experimental investigation of boundary-layer transition on a 10 ̊half-angle cone at Mach 6.9 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], 1970), by Michael C. Fischer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Angle-of-attack analysis of a spinning slender cone with slight aerodynamic and mass asymmetries (Reentry F) (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by Gerard E. Woodbury, W. Douglas Morris, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Investigation of real-gas and viscous effects on the aerodynamic characteristics of a 40 ̊half-cone with suggested correlations for the shuttle orbiter / (Washington : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the National Technical Information Service, 1977), by James L. Hunt, William C. Woods, Robert A Jones, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Supersonic lifting capabilities of large-angle cones / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by James F. Campbell, Dorothy T. Howell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Supersonic aerodynamic characteristics and shock standoff distances for large-angle cones with and without cylindrical afterbodies / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by James F. Campbell, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Convective heat-transfer rates on large-scale conical bodies at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by David A. Stewart, Joseph G. Marvin, and Ames Research Center (page images at HathiTrust)
• Exploratory heat-transfer measurements at Mach 10 on a 7.5 ̊total-angle cone downstream of a region of air and helium transpiration cooling / (Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1969]), by James C. Dunavant, Philip E. Everhart, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Analytical and experimental investigation of end-plane rotations of truncated cones under bending loads / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Richard W. Faison, William H. Richards, John L. Gilbert, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An approximate solution of additive-drag coefficient and mass-flow ratio for inlets utilizing right circular cones at zero angle of attack / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by Vincent R. Mascitti, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Upwash patterns on ablating and nonablating cones at hypersonic speeds / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1969), by John B. McDevitt, Jack A. Mellenthin, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Newtonian aerodynamics for circular cones modified to produce lift at zero angle of attack / (Washington, D.C. : National Aeronautics and Space Administration ; [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 20230], 1969), by Barbara J. Short, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by W. Douglas Morris, Lana M. Couch, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Laminar heat-transfer distributions for a blunted-cone, cone-frustum reentry configuration at Mach 10 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, Va. : For sale by the Clearinghouse for Federal Scientific and Technical Information, [1969]), by J. David Dearing and Langley Research Center (page images at HathiTrust)
• Hypersonic rarefied flow over sharp slender cones / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972), by M. I. Kussoy, Clifford C. Horstman, David A. Stewart, Ames Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Flow patterns and pressure distributions around a bluff afterbody in the wake of a 120° cone for various separation distances at Mach 3.0 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1971), by William D. Deveikis, James Wayne Sawyer, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of nose bluntness and controlled roughness on the flow on two hypersonic inlet center bodies without cowling at mach 5.98 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, U.S. G.P.O.], 1965), by James M. Cubbage and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Ueber die kegel des Pappus und des Hachette ... (Berlin, W. & S. Loewenthal, 1884), by Theodor Meyer (page images at HathiTrust)
• Effect on base drag of recessing the bases of conical afterbodies at subsonic and transonic speeds / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia], 1968), by William B. Compton, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust; US access only)
• Longitudinal aerodynamic characteristics of blunted cones at Mach numbers of 3.5, 4.2, and 6.0 / (Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce], 1964), by J. Wayne Keyes, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Calibration of 30° included-angle cone for determining local flow conditions in Mach number range of 1.51 to 3.51 / (Washington, D.C. : National Aeronautics and Space Administration ; Springfield, VA : For sale by the Clearinghouse for Federal Scientific and Technical Information, 1968), by Walter A. Vahl, Robert L. Weirich, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Energy transfer from a test electron to a collisionless plasma /, by Joseph G. Kelley, Morton A. Levine, and Air Force Cambridge Research Laboratories (U.S.) (page images at HathiTrust)
• Review of the cone-to-rod efficiency ratio as a specification for lighting systems /, by John Lott Brown, United States. Air Force. Air Research and Development Command. sponsor, Columbia University, and Wright Air Development Center (page images at HathiTrust)
• Effect of convergent ejector nozzles on the boattail drag of a 16©� conical afterbody at Mach number of 0.6 to 1.26 / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by James M. Cubbage, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Data on shape and location of detached shock waves on cones and spheres / (Washington, D.C. : National Advisory Committee for Aeronautics, [1949]), by Juergen W. Heberle, Paul B. Gooderum, George P. Wood, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Base pressure measurements on sharp and blunt 9©� cones at Mach numbers from 3.50 to 9.20 /, by Neil A. Zarin, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Boundary layer transition on the NOL standard cone in the Ballistic Research Laboratories' supersonic wind tunnels /, by J. C. McMullen and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Hypersonic pitch-damping support using water-cooled ball bearings /, by Frank J Regan, Eugene V. Horanoff, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• An experimental investigation of the aerodynamic characteristics of slender hypersonic vehicles at high angles of attack /, by Robert H. Feldhuhn, Lionel Pasiuk, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Separated flow phenomena on a slender cone at Mach 5 /, by Robert H. Feldhuhn, Allen E. Winkelmann, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Measurements of blast-induced transient pressures at the base of a cone in supersonic flow /, by Frank P. Baltakis, Gary D. Senechal, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The effect of the inlet mach number and inlet-boundary-layer thickness on the performance of a 23©� conical-diffuser-tail-pipe combination / (Washington, D.C. : National Advisory Committee for Aeronautics, 1950), by Jerome Persh, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration / (Washington, D.C. : National Advisory Committee for Aeronautics, 1955), by Charles B. Rumsey, Langley Aeronautical Laboratory, United States. National Adviosry Committee for Aeronautics. NACA research memorandum, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Calculation of the velocity profiles of the incompressible laminar boundary layer on a yawed spinning cone and the magnus effect /, by Ira D. Jacobson, Jeffrey B. Morton, Allen Gregory Vollmer, U.S. Army Ballistic Research Laboratory, and University of Virginia. School of Engineering and Applied Science (page images at HathiTrust)
• Three dimensional flow studies over a spinning cone at angle of attack /, by H. A. Dwyer, U.S. Army Ballistic Research Laboratory, and Davis. Department of Mechanical Engineering University of California (page images at HathiTrust)
• The dynamic properties of pure cones and cone cylinders /, by L. E. Schmidt, U.S. Army Ballistic Research Laboratory, and U.S. Atomic Energy Commission (page images at HathiTrust)
• Shock-wave yaw for 9 1/2©� semi-apex cone /, by Eugene D. Boyer and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Comparisons of experimental and theoretical heat transfer to a yawed sphere-cone model at supersonic speeds /, by Lionel Pasiuk and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Measurements of hypersonic turbulent heat transfer on a highly cooled cone /, by Donald M Wilson and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Experimental studies of shock-shock interactions on a 9° cone /, by David L. Merritt, Philip M Aronson, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• The drag of slightly blunted slender cones /, by W. Carson Lyons, H. S. Brown, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Oblique shock interaction experiments /, by David L. Merritt, Philip M. Aronson, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Hypersonic-turbulent boundary-layer separation over a cone-cylinder-flare configuration /, by Arnold Polak, Chris A. Kalivretenos, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• An experimental investigation of the flow field around a yawed cone /, by Robert H. Feldhuhn and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Further evaluation of a telemetry system for use in shock interaction experiments /, by David L. Merritt, Philip M. Aronson, and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Hypersonic, turbulent, cold-wall, skin-friction and heat-transfer measurements on an axisymmetric sharp cone /, by Kuei-Yuan Chien, Md.) Naval Ordnance Laboratory (White Oak, and Technical Cooperation Program (page images at HathiTrust)
• An empirical equation for prediction of transition location on cones in super-or hypersonic flight /, by Neal Tetervin and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Tables for supersonic flow of helium around right circular cones at zero angle of attack, (Washington, Scientific and Technical Information Office, National Aeronautics and Space Administration; [for sale by the Supt. of Docs., U. S. Govt. Print. Off.], 1973), by Joseph L Sims and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust; US access only)
• Aerodynamic characteristics in pitch of several triple-body missile configurations at Mach numbers 0.6 to 1.4 / (Washington, D.C. : National Advisory Committee for Aeronautics, [1956]), by Earl D. Knechtel, Arvid N. Andrea, Ames Research Center, and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Two geometrical memoirs on the general properties of cones of the second degree, and on the spherical conics / (Dublin : For Grant and Bolton, 1841), by M. Chasles and Charles Graves (page images at HathiTrust)
• Preliminary studies of manned satellites wingless configuration : nonlifting / (Washington, D.C. : National Advisory Committee for Aeronautics, 1958), by Maxime A. Faget, James J. Buglia, Benjamine J. Garland, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics. NACA research memorandum (page images at HathiTrust)
• An Intersection property for cones in a linear space /, by R. E. Fullerton, United States. Air Force. Office of Scientific Research, and College Park. Department of Mathematics University of Maryland (page images at HathiTrust)
• Upwash characteristics at several stations on a blunted cone-frustum-cylinder model at mach numbers from 1.60 to 4.65 / (Washington [D.C.] : National Aeronautics and Space Administration, [1959]), by James D. Church, Joseph W. Cremin, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Roll-damping derivative calculations for spinning sharp and blunt cones in supersonic and hypersonic flow /, by Arloe W. Mayne, United States. Air Force. Systems Command. issuing body, sponsor Arnold Engineering Development Center, and Inc. ARO (page images at HathiTrust)
• Static force tests at Mach 8 of sharp and blunt 20-deg half-angle cones with a blunt 70-deg swept delta wing /, by G. H. Merz, O. R. Pritts, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Evaluation of critical sting length on a 7-deg cone as determined by measurements of dynamic stability derivatives and base pressure for Mach numbers 0.2 through 1.3 /, by Frederick B. Cyran, Edward J. Marquart, Bob L. Uselton, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Experimental determination of aerodynamic drag on a blunted 10-deg cone at angles of attack in hypersonic, rarefied flow /, by David E. Boylan, William H. Sims, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Comparison of hotshot tunnel force, pressure heat-transfer and shock shape data with shock tunnel data /, by E. E. Edenfield, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• An investigation of sting interference effects on an oscillating cone in transonic flow /, by Frederick B. Cyran, J. P. Christopher, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Dynamic stability characteristics of a10-deg cone at Mach number 10 /, by A. E. Hodapp, G. E. Burt, B. L. Uselton, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Boundary-layer transition correlation on a slender cone in wind tunnels and flight for indications of flow quality /, by N. Sam Dougherty, David F. Fisher, sponsor Hugh L. Dryden Flight Research Center, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Viscous effects on zero-lift drag of slender blunt cones /, by Jack D. Whitfield, B. J. Griffith, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Hypersonic force, pressure, and heat transfer investigations of sharp and blunt slender cones /, by David B. Wilkinson, Shelby A. Harrington, sponsor Cornell Aeronautical Laboratory, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Pressure distribution and flow visualization tests of a 1.5 elliptic cone at Mach 10 /, by R. L. Palko, A. D. Ray, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Laminar heat transfer on sharp and blunt ten-degree cones in conical and parallel low-density flow /, by David E. Boylan, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Static pressure on sharp and blunt cones in conical and parallel low-density flow /, by Max Kinslow, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• A mehod for the prediction of the effects of free-stream disturbances on boundary-layer transition /, by J. A. Benek, M. Dean High, Inc. ARO, Arnold Engineering Development Center. sponsor, and United States. Air Force. Systems Command. issuing body (page images at HathiTrust)
• Pressure distribution tests of several sharp leading edge wings, bodies, and body-wing combinations at Mach 5 and 8 /, by R. E. Randall, J. L. Burk, D. R. Bell, Inc. sponsor ARO, United States. Air Force. Air Research and Development Command. sponsor, and Arnold Engineering Development Center. issuing body (page images at HathiTrust)
• The Dynamics of spinning bodies at large angle of attack /, by J. E. Brunk, R. W. Rakestraw, W. L. Davidson, and United States. Air Force. Office of Scientific Research. issuing body (page images at HathiTrust)
• Hypersonic heat transfer measurements on re-entry vehivle surfaces at high Reynolds number /, by Bryan E. Richards, issuing body United States. Air Force. Systems Command, sponsor Von Karman Institute for Fluid Dynamics, and sponsor Air Force Materials Laboratory (U.S.) (page images at HathiTrust)

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