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Guided missiles -- Aerodynamics -- Computer simulation

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• Guided missiles -- Aerodynamics
• Guided missiles -- Aerodynamics -- Mathematical models
• Guided missiles -- Computer simulation
• Aerodynamics -- Computer simulation

• Improvements to the missile aerodynamic prediction code DEMON3 (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Marnix F. E. Dillenius, Daniel J. Lesieutre, David L. Johnson, Inc Nielsen Engineering & Research, and Langley Research Center (page images at HathiTrust)
• Development and application of a local linearization algorithm for the integration of quaternion rate equations in real-time flight simulation problems (National Aeronautics and Space Administration ;, 1973), by Lawrence E. Barker, Louise H. Williams, Roland L. Bowles, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)

Items below (if any) are from related and broader terms.

• Mach 6 experimental and theoretical stability and performance of a cruciform missile at angles of attack up to 65⁰ (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by Edward R. Hartman, Patrick J. Johnston, and Langley Research Center (page images at HathiTrust)
• Mach 6 flow field surveys beneath the forebody of an airbreatinng missile (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1986), by Patrick J. Johnston, James L. Hunt, and Langley Research Center (page images at HathiTrust)
• Supersonic aerodynamic characteristics of a Sparrow III type missile model with wing controls and comparison with existing tail-control results (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by William J. Monta and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Stability and control characteristics of an air-breathing missile configuration having a forward located inlet (National Aeronautics and Space Administration ;, 1976), by Wallace C. Sawyer, Clyde Hayes, and Langley Research Center (page images at HathiTrust)
• Jet effects at supersonic speeds on base and afterbody pressures of a missile model having single and multiple jets (National Aeronautics and Space Administration, 1963), by Nickolai Charczenko, Clyde Hayes, and Langley Research Center (page images at HathiTrust)
• Rocket-powered flight test of a roll-stabilized supersonic missile configuration (National Advisory Committee for Aeronautics, 1950), by Robert A. Gardiner, Jacob Zarovsky, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel (National Advisory Committee for Aeronautics, 1952), by Donald E. Coletti, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Preliminary investigation of lithium hydride as a high-temperature internal coolant (National Advisory Committee for Aeronautics, 1957), by Jerry L. Modisette, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Response of an asymmetric missile to spin varying through resonance (Aberdeen Proving Ground, Maryland : U.S. Army Aberdeen Research and Development Center, Ballistic Research Laboratories, 1971., 1971), by C. H. Murphy and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Gravity-induced angular motion of a spinning missile (Aberdeen Proving Ground, Maryland : U.S. Army Aberdeen Research and Development Center, Ballistic Research Laboratories, 1971., 1971), by C. H. Murphy and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Boundary layer studies on a spinning cone (Aberdeen Proving Ground, Maryland : Ballistic Research Laboratories, 1973., 1973), by Walter B. Sturek and U.S. Army Ballistic Research Laboratory (page images at HathiTrust)
• Shock interaction surface pressures for hemispherical and conical bodies (White Oak, Maryland : United States Naval Ordnance Laboratory, 1971., 1971), by Frank P. Baltakis and Md.) Naval Ordnance Laboratory (White Oak (page images at HathiTrust)
• Wrap-around-fin (WAF) pressure distribution (White Oak, Maryland : United States Naval Ordnance Laboratory, 1973., 1973), by John E. Holmes, Md.) Naval Ordnance Laboratory (White Oak, and Technical Cooperation Program (page images at HathiTrust)
• Effects of magnus moments on missile aerodynamic performance (Hanscom Air Force Base, Massachusetts : Phillips Laboratory, Directorate of Geophysics, 1991., 1991), by George Y. Jumper, D. Curtis, J. Willett, J. Smith, R. K. Longstreth, C. J. Frushon, and USAF Phillips Laboratory (page images at HathiTrust)
• Preliminary design aerodynamic prediction methodology for missiles with nose bluntness (Wright-Patterson Air Force Base : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1978., 1978), by Charles W. Ingram, David Shida, Carter J. Dinkeloo, Karlheinz O. W. Ball, Air Force Flight Dynamics Laboratory (U.S.), and Systems Research Laboratories (page images at HathiTrust)
• Development feasibility of missile datcom (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981., 1981), by Steven R. Vukelich, Air Force Flight Dynamics Laboratory (U.S.), Air Force Wright Aeronautical Laboratories, and McDonnell Douglas Astronautics Company-St. Louis (page images at HathiTrust)
• Static stability and drag characteristics of the HAST missile at Mach numbers 2.25, 3.0, and 4.0 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1974., 1974), by J. T. Best, R. W. Rhudy, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Characterization of the flowfield near a wrap-around fin at supersonic speeds (Wright Patterson Air Force Base, Ohio : Air Vehicles Directorte, Air Force Research Laboratory, Air Force Materiel Command, 1998., 1998), by Carl P. Tilmann and Ohio). Air Vehicles Directorate Air Force Research Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Missile supersonic/hypersonic aerodynamics (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Systems Command, United States Air Force, 1991., 1991), by Andrew A. Jenn, Philip K. Wang, Carol D. Matthews, McDonnell Douglas Astronautics Company-St. Louis, Air Force Flight Dynamics Laboratory (U.S.), Ohio) Wright Laboratory (Wright-Patterson Air Force Base, and United States. Air Force. Systems Command (page images at HathiTrust)
• Aerodynamic characteristics of the HAST missile at Mach numbers 2.25, 3.0, and 4.0 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1972., 1972), by J. H. Jones, Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Artificially induced boundary-layer transition on blunt-slender cones using distributed roughness and spherical-type tripping devices at hypersonic speeds (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Von Karman Gas Dynamics Facility, Air Force Systems Command, United States Air Force, 1978., 1978), by A. H. Boudreau, United States. Air Force. Systems Command, Arnold Engineering Development Center, and Inc ARO (page images at HathiTrust)
• A compilation of static stability and fin loads data for slender body missile models with and without tail fins and wings. Volume I (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1976., 1976), by G. R. Gomillion, Air Force Armament Laboratory (U.S.), Inc ARO, Arnold Engineering Development Center, and United States. Air Force. Systems Command (page images at HathiTrust)
• Static aerodynamic characteristics of a series of generalized slender bodies with and without fins at Mach numbers form 0.6 to 3.0 and angles of attack from 0 to 180 deg. Volume 1 (Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, 1976., 1976), by William B. Baker, Arnold Engineering Development Center, United States. Air Force. Systems Command, and Inc ARO (page images at HathiTrust)
• Computations of supersonic vortical flows around ogive-cylinders using central and upwind differences (Wright-Patterson Air Force Base, Ohio : Flight Dynamics Directorate, Wright Laboratory, Air Force Materiel Command, United States Air Force, 1997., 1997), by Eswar Josyula and Ohio) Wright Laboratory (Wright-Patterson Air Force Base (page images at HathiTrust)
• Vortex induced rolling moments on cruciform missiles at high angle of attack (Boston, Massachusetts : Engineering Laboratories, Boston University, 1971., 1971), by Steven I. Kane, United States. |b Air Force. |b Systems Command, Air Force Cambridge Research Laboratories (U.S.), and Boston University (page images at HathiTrust)
• Theoretical analysis of the flow field over a family of ogive bodies (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Directorate, 1977., 1977), by Ronnie W. Guy, Redstone Arsenal (Ala.), United States. Army. Missile Command, and inc Science Applications (page images at HathiTrust)
• Effect of missile nose length and shape on fin effectiveness (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Advanced Systems Laboratory, Research and Engineering Directorate, 1970., 1970), by Donald V. Rubin, Wiley Pettis, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• A summary of jet plume effects on the stability characteristics of a body of revolution with various fin configurations at Mach numbers from 0.2 to 2.3 : normal jet plume simulator (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1976., 1976), by George Batiuk, James H. Henderson, Redstone Arsenal (Ala.), and Development United States. Army. Missile Command. Research (page images at HathiTrust)
• Static aerodynamic stability characteristics of a body of revolution with wraparound fins at Mach numbers from 0.5 to 1.3 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Advanced Systems Laboratory, Research and Engineering Directorate, 1972., 1972), by John E. Vaughn, Calvin Wayne Dahlke, Joseph C. Craft, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• Normal force effectiveness of several fin planforms with streamwise gaps at Mach numbers of 0.8 to 5.0 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Laboratory, 1970., 1970), by C. W. Dahlke, W. Pettis, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust)
• An investigation of the aerodynamic stabilizing effectiveness of several split flare afterbody configurations in the presence of an underexpanded jet plume at transonic Mach numbers (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Directorate, Technology Laboratory, 1978., 1978), by James R. Burt, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• Numerical investigation of aerodynamics of Canard-controlled missile using planar and grid tail fins. Part II, Subsonic and transonic flow (Aberdeen Proving Ground, Maryland : Army Research Laboratory, 2004., 2004), by James DeSpirito, U.S. Army Research Laboratory, W. David Washington, and Milton E. Vaughn (page images at HathiTrust)
• Aerodynamic prediction methods, RDF-129 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Systems Simulation and Development Directorate, Research, Development, and Engineering Center, 1989., 1989), by J. L. Sims, Robert H. Carnesi, L. G. Mendel, John F. Stalnaker, Redstone Arsenal (Ala.), United States. Army. Missile Command, and Georgia Tech Research Institute (page images at HathiTrust)
• Static aerodynamic stability characteristics of a body of revolution with wraparound fins at Mach numbers from 1.6 to 2.86 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1972., 1972), by John E. Vaughn, Calvin Wayne Dahlke, Joseph C. Craft, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• An oil flow study of a sonic reaction jet ejecting from a body of revolution into a free stream of Mach number range 1.75 to 4.5 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Labortory, 1970., 1970), by Troy A. Street, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust)
• Grid fin analysis. Vol. 1 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Systems Simulation and Development Directorate, Research, Development, and Engineering Center, 1994, 1994), by John E. Burkhalter, Todd Michael Leleux, Redstone Arsenal (Ala.), United States. Army. Missile Command, and Auburn University (page images at HathiTrust)
• Aerodynamic characteristics of wraparound fins mounted on bodies of revolution and rheir influence on the missile static stability at Mach numbers from 0.3 to 1.3 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1972., 1972), by Calvin Wayne Dahlke, Joseph C. Craft, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• An experimental investigation of the aerodynamic characteristics of several nose-mounted canard configurations at transonic Mach numbers (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1974., 1974), by James R Burt, Redstone Arsenal (Ala.), Chrysler Corporation, and Development United States. Army. Missile Command. Research (page images at HathiTrust)
• User's manual for the Martin-Marietta high angle of attack aerodynamic methodology for body tail missiles (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Directorate, Technology Laboratory, 1978., 1978), by Gary C. Winn, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• A summary of aerodynamic characteristics for wrap-around fins from Mach 0.3 to 3.0 (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, 1977., 1977), by James A. Humphrey, Calvin Wayne Dahlke, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• An experimental investigation of the aerodynamic characteristics of nose mounted canard configurations at supersonic Mach numbers (1.5 through 4.5) (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research, Development, and Engineering Laboratory, 1976., 1976), by James R Burt, Redstone Arsenal (Ala.), Chryler Corporation, and Development United States. Army. Missile Command. Research (page images at HathiTrust)
• Guide to the operation of the MIRADCOM/UTSI computer program for plume induced sepertion at transonic speeds (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Directorate, Technology Laboratory, 1977., 1977), by D. J. Spring, Trevor H. Moulden, Redstone Arsenal (Ala.), United States. Army. Missile Command, and University of Tennessee (System). Space Institute (page images at HathiTrust)
• Modified Barrowman Method with applications to the Optical Deep Attack Missile Systems and Precision Deep Attack Missile Systems vehicles (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research Directorate, Research, Development, and Enginering Center, 1989., 1989), by Charles E. Hall, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• Correlation of viscous effects and comparison between experimental and theoretical distribution of potential normal force and pitching moment for bodies of revolution at supersonic speeds (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Labortory, 1967., 1967), by William David Washington, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust)
• An experimental investigation of the interference effects due to a lateral jet issuing from a body of revolution over the Mach number range of 0.8 to 4.5 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1968., 1968), by Donald J. Spring, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• An investigation of flow and stability characteristics for a body of revolution with fins and flare in presence of Plume induced separation at Mach numbers 0.7 to 1.4 (Redstone Arsenal, Alabama ; U.S. Army Missile Research and Development Command, Aeroballistics Direcorate, Technology Laboratory, 1977., 1977), by Calvin Wayne Dahlke, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• Aerodynamic characteristics of a series of bodies with and without tails at Mach Numbers from 0.8 to 3.0 and angles of attack from 0 to 45 degrees (Redstone Arsenal, Alabama ; U.S. Army Missile Command, 1976., 1976), by Jimmie N. Derrick, Gary C. Winn, Donald J. Spring, Redstone Arsenal (Ala.), United States. Army. Missile Command, and University of Tennessee (System). Space Institute (page images at HathiTrust)
• Investigation of the effect of low thrust levels on the base pressure of a cylindrical body at supersonic speeds (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Research and Development Directorate, Advanced Systems Labortory, 1970., 1970), by T. A. Martin, C. E. Brazzel, Redstone Arsenal (Ala.), and United States. Army. Missile Command. Research and Development Directorate (page images at HathiTrust)
• Aerodynamic analysis of a "flex" fin concept (Redstone Arsenal, Alabama ; U.S. Army Missile Command, System Simulation and Development Directorate, Research, Development, and Enginering Center, 1987., 1987), by George A. Sanders, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)
• Aerodynamic stability technology for maneuverable missiles. Volume I, Configuration aerodynamic characteristics (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1979., 1979), by Gennaro F. Aiello, Michael C. Bateman, Air Force Flight Dynamics Laboratory (U.S.), Martin Marietta Corporation, and United States. Air Force. Systems Command (page images at HathiTrust)
• An experimental investigation of base pressure on a body of revolution at high thrust levels and free stream Mach numbers of 1.5 to 2.87 (Redstone Arsenal, Alabama ; U.S. Army Missile Command, Advanced Systems Laboratory, Research and Engineering Directorate, 1970., 1970), by Joseph C. Craft, Charles E. Brazzel, Redstone Arsenal (Ala.), and United States. Army. Missile Command (page images at HathiTrust)

More items available under broader and related terms at left.