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Online Books by

George C. Ashby

Books from the extended shelves:

• Ashby, George C.: Aerodynamic testing technique for twin-fuselage models at hypersonic speeds (National Aeronautics and Space Administration ;, 1975), also by Langley Research Center (page images at HathiTrust)
• Ashby, George C.: Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 (National Aeronautics and Space Administration ;, 1974), also by Julius E. Harris and Langley Research Center (page images at HathiTrust)
• Ashby, George C.: Comparison of hinge moments for a simple delta wing and a delta-wing orbiter concept at mach 6 (National Aeronautics and Space Administration, 1972), also by Langley Research Center and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ashby, George C.: Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds (National Aeronautics and Space Administration, 1972), also by United States National Aeronautics and Space Administration and Langley Research Center (page images at HathiTrust)
• Ashby, George C.: Flow-field surveys on the windward side of the NASA 040A space shuttle orbiter at 31 ̊angle of attack and Mach 20 in helium (National Aeronautics and Space Administration ;, 1977), also by V. T. Helms and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ashby, George C.: Investigation of the effect of a guide-vane-rotor combination on inlet total-pressure distortions in a compressible fluid (National Aeronautics and Space Administration, 1959), also by Langley Research Center (page images at HathiTrust)
• Ashby, George C.: Longitudinal aerodynamic performance of a series of power-law and minimum-wave-drag bodies at Mach 6 and several Reynolds numbers (National Aeronautics and Space Administration ;, 1974), also by Langley Research Center (page images at HathiTrust)
• Ashby, George C.: NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results (National Advisory Committee for Aeronautics, 1953), also by Wallace M. Schulze, John R. Erwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Ashby, George C.: NASA TN D-1793 (National Aeronautics and Space Administration, 1963), also by Theodore J. Goldberg, James G. Hondros, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ashby, George C.: NASA TN D-4361 (National Aeronautics and Space Administration ;, 1968), also by David R. Stone, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ashby, George C.: NASA TN D-4598 (National Aeronautics and Space Administration ;, 1968), also by W. Frank Staylor, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Ashby, George C.: Near-field sonic-boom pressure signatures for the space shuttle launch and orbiter vehicles at Mach 6 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), also by Langley Research Center and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Ashby, George C.: A parametric study of the aerodynamic characteristics of nose-cylinder-flare bodies at a Mach number of 6.0 (National Aeronautics and Space Administration ;, 1965), also by Aubrey M. Cary and Langley Research Center (page images at HathiTrust)
• Ashby, George C.: A study of the sonic-boom characteristics of a blunt body at a Mach number of 6 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), also by Langley Research Center and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)

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