Dynamic Stability Testing of Space Shuttle Configurations during Abort Separation at Mach Numbers 1.76 and 2
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Wind tunnel tests were conducted to determine the dynamic- and static-stability derivatives of an approximately 0.011-scale North American Rockwell straight wing and delta wing orbiters in proximity with an 0.011-scale General DynamicsConvair delta wing booster. Interference-free data on the orbiter models were also obtained. Measurements were made with a forced- oscillation dynamic balance as the model oscillated plus or minus 1.6 deg at angles of attack ranging from -6.8 to 9.7 deg. Data were obtained at Mach numbers 1.76 and 2 and at free-stream Reynolds numbers, based on orbiter model length, ranging from 2,030,000 to 6,330,000. Both orbiter configurations were dynamically and statically stable, and in general, the level and trends of the orbiter derivatives were not greatly affected when in the proximity of the booster. The present damping data show fair agreement with damping data from the National Aeronautical Establishment NAE, which are the only other known damping data of this type.
- Manned Spacecraft