The analysis of pressure and gage wind tunnel data from space shuttle wind tunnel test IA138 was performed to define the aerodynamic influence of the main propulsion system and solid rocket booster plumes on the total vehicles, elements, and components of the space shuttle vehicle during the supersonic portion of ascent flight. A math model of the plume induced aerodynamic characteristics was developed for a range of Mach numbers to match the forebody aerodynamic math model. The base aerodynamic characteristics are presented in terms of forces and moments versus attitude. Total vehicle base and forebody aerodynamic characteristics are presented in terms of aerodynamic coefficients for Mach numbers from 1.55 to 2.5.
Space Shuttle Plume/Simulation Application: Results and Math Model Supersonic Data
1979
138 pages
Report
Keine Angabe
Englisch
Rocket Propellants , Combustion & Ignition , Space Launch Vehicles & Support Equipment , Manned Spacecraft , Ascent propulsion systems , Solid rocket propellants , Space shuttles , Rocket exhaust , Mathematical models , Wind tunnel tests , Aerodynamic characteristics , Aerodynamic configurations , Elevons , Pressure , Supersonic wind tunnels , Launch vehicles , Liquid rocket propellants
Space shuttle plume/simulation application
NTRS | 1979
|Space Shuttle Plume/Simulation Application
NTIS | 1979
|