Determining the Aerothermodynamic Environment of a Generic Missile,
AIR FORCE ACADEMY COLORADO SPRINGS CO DEPT OF AERONAUTICS
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There are a variety of computer codes of varying degrees of rigor which can be used by the designers of high-speed missile systems in order to define the aerothermodynamic environment at flight conditions. It is assumed that the flow models and the numerical algorithms used in these codes have been validated by their developers. However, the users of such codes must exercise them against a quality data base, gaining knowledge of the intricacies in the use of such codes and calibrating the range of conditions over which the code can be used to predict specific parameters that are important to the design objectives without necessarily verifying that all the features of the flow are correctly modeled. Data which can be used to define the aerothermodynamic environment of a generic missile have been obtained in the Tri-Sonic Wind Tunnel TWT of the Aeronautical Research Center ARC at the U. S. Air Force Academy USAFA. Forces and moments, surface pressures, surface temperatures, and flow visualization photographs have been obtained at a Mach number of 4.28 over a range of Reynolds numbers based on the free-stream conditions and model length from 1x10exp 7 to 1.5x10exp 7. The experimentally-determined parameters are compared in the present paper with parameters computed using the Reynolds-Averaged Navier-Stokes equations in the GASP v3 code and with the aerodynamic coefficients computed using the ATAP code.
- Guided Missile Dynamics, Configurations and Control Surfaces
- Fluid Mechanics