Joint computational and experimental aerodynamics research on a reentry vehicle
This paper seeks to improve the synergism between computational aerodynamics and wind tunnel experimentation. In this paper, experimental and computational results are presented for a hypersonic vehicle configuration at Mach 8. Comparisons are made between experimental and computational results in order to improve the accuracy of both approaches. The basic vehicle configuration is a spherically blunted cone with a slice parallel with the axis of the vehicle. The half-angle of the cone is 10 deg. and the ratio of spherical nose radius to base radius in 10%. Onto the slice portion of the vehicle can be attached flaps with three different deflection angles; 10, 20, and 30 deg. All of the experimental results were obtained in the Sandia Mach 8 long duration, blow-down, hypersonic wind tunnel. Flow visualization results include surface oil flow, spark schlieren, and liquid crystal photographs and video. The liquid crystals were used as an aid in verifying that a laminar boundary layer existed over the entire body. An extensive uncertainty analysis was conducted to estimate quantitatively the accuracy of the measurement. Computational aerodynamic force and moment predictions are compared with the wind tunnel data. The Sandia Parabolized Navier-Stokes code is used to generate solutions for the sliced vehicle (no flap) and partial solutions for the flapped vehicle. For the geometry with the flap, an axially separated flow occurs and a time iterative Navier-Stokes code is used to provide comparisons with the data. This paper presents a portion of the results given in earlier works and also discusses new experimental results with this configuration.
- Research Organization:
- Sandia National Labs., Albuquerque, NM (United States)
- Sponsoring Organization:
- USDOE; USDOE, Washington, DC (United States)
- DOE Contract Number:
- AC04-76DP00789
- OSTI ID:
- 5813165
- Report Number(s):
- SAND-91-1839C; CONF-920534-1-Extd.Abst.; ON: DE91017315
- 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
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Joint computational/experimental aerodynamics research on a reentry vehicle
Joint computational and experimental aerodynamics research on a hypersonic vehicle
Related Subjects
GENERAL PHYSICS
99 GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE
REENTRY VEHICLES
AERODYNAMICS
COMPUTERIZED SIMULATION
HYPERSONIC FLOW
NAVIER-STOKES EQUATIONS
NOSE CONES
SHEAR
WIND TUNNELS
DIFFERENTIAL EQUATIONS
EQUATIONS
FLUID FLOW
FLUID MECHANICS
MECHANICS
PARTIAL DIFFERENTIAL EQUATIONS
SIMULATION
SPACE VEHICLES
TUNNELS
UNDERGROUND FACILITIES
VEHICLES
661300* - Other Aspects of Physical Science- (1992-)
990200 - Mathematics & Computers