The Langley 8 foot transonic pressure tunnel and the Langley Unitary Plan wind tunnel used to determine the longitudinal and lateral-directional aerodynamic characteristics of a winged single-state-to-orbit vehicle was investigated. The model was tested over a Mach number range from 0.3 to 4.63 for an angle-of-attack range from 4 to 30 D at both 0 and 5 D sideslip.
Static Aerodynamic Characteristics of a Winged Single-Stage-to-Orbit Vehicle at Mach Numbers from 0.3 to 4.63
1978
119 pages
Report
No indication
English