Accession Number : ADA329044

Title :   Determining the Aerothermodynamic Environment of a Generic Missile,

Corporate Author : AIR FORCE ACADEMY COLORADO SPRINGS CO DEPT OF AERONAUTICS

Personal Author(s) : Zuber, Matthew E. ; Towne, Matthew C. ; Chen, Alice J. ; Bertin, John J. ; Butler, Robert J.

PDF Url : ADA329044

Report Date : 1997

Pagination or Media Count : 16

Abstract : 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 1x10(exp 7) to 1.5x10(exp 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.

Descriptors :   *GUIDED MISSILES, *AEROTHERMODYNAMICS, *AERONAUTICAL ENGINEERING, ALGORITHMS, FLIGHT TESTING, HIGH VELOCITY, COMPUTER PROGRAMMING, MOMENTS, COMPUTATIONAL FLUID DYNAMICS, FLOW VISUALIZATION, PRESSURE, NAVIER STOKES EQUATIONS, SURFACE TEMPERATURE, REYNOLDS NUMBER.

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE