
by American Institute of Aeronautics and As
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Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing
Thomas A. Byrdsong1983
Wind-tunnel pressure data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊
Emma Jean Landrum1977
Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊
Emma Jean Landrum1979