Two scaled models of the Aeroassist Flight Experiment (AFE) vehicle were tested in two air wind tunnels and one CF4 tunnel. The tests were to determine the static longitudinal aerodynamic characteristics, and shock shapes for the configuration in hypersonic continuum flow. The tests were conducted with a range of angle of attack to evaluate the effects of Mach number, Reynolds numbers, and normal shock density ratio.
Measured and Predicted Aerodynamic Coefficients and Shock Shapes for Aeroassist Flight Experiment (AFE) Configuration
1989
52 pages
Report
No indication
English
Aerodynamics , Test Facilities & Equipment , Fluid Mechanics , Aeroassist , Aerodynamic coefficients , Aerodynamic configurations , Blunt bodies , Hypersonic flow , Wind tunnel tests , Aerodynamic characteristics , Hypersonic vehicles , Normal shock waves , Angle of attack , Density distribution , Force distribution , Lift drag ratio , Mach number , Pitching moments , Reynolds number , Scale models , Static tests
The Aeroassist Flight Experiment
NTRS | 1987
|Aeroassist Flight Experiment (AFE)
NTRS | 1988
|Aeroassist Flight Experiment (AFE)
NTIS | 1988
|