A proposed wing-body reusable launch vehicle was tested in the NASA Marshall Space Flight Center's 14 x 14-inch trisonic wind tunnel during the winter of 1994. This test resulted in the vehicle's subsonic and transonic, Mach 0.3 to 1.96, longitudinal and lateral aerodynamic characteristics. The effects of control surface deflections on the basic vehicle's aerodynamics, including a body flap, elevons, ailerons, and tip fins, are presented.
Transonic Aerodynamic Characteristics of a Proposed Wing-Body Reusable Launch Vehicle Concept
1995
111 pages
Report
Keine Angabe
Englisch
Aerodynamics , Space Launch Vehicles & Support Equipment , Aerodynamic characteristics , Aerodynamic forces , Aerodynamic stability , Angle of attack , Body-wing configurations , Control surfaces , Lateral stability , Longitudinal stability , Mach number , Sideslip , Single stage to orbit vehicles , Spacecraft stability , Subsonic speed , Transonic speed , Wind tunnel tests , Ailerons , Elevons , Fins , Pitching moments , Rolling moments , Yawing moments
Transonic Aerodynamic Characteristics of a Proposed Wing Body Reusable Launch Vehicle Concept
British Library Conference Proceedings | 1996
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