Joint computational and experimental aerodynamics research on a hypersonic vehicle

Conference · Wed Jan 01 00:00:00 EST 1992

OSTI ID:5381990

Oberkampf, W L; Aeschliman, D P; Walker, M M

A closely coupled computational and experimental aerodynamics research program was conducted on a hypersonic vehicle configuration at Mach 8. Aerodynamic force and moment measurements and flow visualization results were obtained in the Sandia National Laboratories hypersonic wind tunnel for laminar boundary layer conditions. Parabolized and iterative Navier-Stokes simulations were used to predict flow fields and forces and moments on the hypersonic configuration. The basic vehicle configuration is a spherically blunted 10{degrees} cone with a slice parallel with the axis of the vehicle. On the slice portion of the vehicle, a flap can be attached so that deflection angles of 10{degrees}, 20{degrees}, and 30{degrees} can be obtained. Comparisons are made between experimental and computational results to evaluate quality of each and to identify areas where improvements are needed. This extensive set of high-quality experimental force and moment measurements is recommended for use in the calibration and validation of computational aerodynamics codes. 22 refs.

• Research Organization: Sandia National Labs., Albuquerque, NM (United States)
• Sponsoring Organization: USDOE; USDOE, Washington, DC (United States)
• DOE Contract Number: AC04-76DP00789
• OSTI ID: 5381990
• Report Number(s): SAND-92-0919C; CONF-920534-2; ON: DE92013439
• Resource Relation: Conference: Advisory Group for Aerospace Research and Development (AGARD) fluid dynamics panel symposium on theoretical and experimental methods in hypersonic flows, Torino (Italy), 5-7 May 1992
• Country of Publication: United States
• Language: English

Related Subjects

45 MILITARY TECHNOLOGY, WEAPONRY, AND NATIONAL DEFENSE
99 GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE
42 ENGINEERING
AIRCRAFT
AERODYNAMICS
HYPERSONIC FLOW
COMPUTERIZED SIMULATION
COMPUTER CALCULATIONS
EXPERIMENTAL DATA
FLIGHT TESTING
LAMINAR FLOW
NAVIER-STOKES EQUATIONS
NOSE CONES
WIND TUNNELS
DATA
DIFFERENTIAL EQUATIONS
EQUATIONS
FLUID FLOW
FLUID MECHANICS
INFORMATION
MECHANICS
NUMERICAL DATA
PARTIAL DIFFERENTIAL EQUATIONS
SIMULATION
TESTING
TUNNELS
UNDERGROUND FACILITIES
450000* - Military Technology
Weaponry
& National Defense
990200 - Mathematics & Computers
420500 - Engineering- Materials Testing