Accession Number:

ADA151882

Title:

Flow over a Biconic Configuration with an Afterbody Compression Flap.

Descriptive Note:

Final rept. Jan-Apr 84,

Corporate Author:

AIR FORCE WRIGHT AERONAUTICAL LABS WRIGHT-PATTERSON AFB OH

Personal Author(s):

• Shang,J. S.
• MacCormack,R. W.

Report Date:

1984-04-01

Pagination or Media Count:

49.0

Abstract:

Three-dimensional Navier-Stokes solutions were obtained for flow over a biconic configuration with an afterbody compuression flap. The simulated flow as achieved for a Mach number of 7.97, a characteristics Reynolds number of 9.23 million and at a zero degree angle of attack. A comparison study was conducted usign the vectorized MacCormacks explicit and implicit numerical schemes. Results from both the explicit and the implicit algorithms correctly yielded the detailed flow field structure and the heat transfer information in comparison with experimental data. However, the implicit numerical procedure exhibited a significant improvement in numerical efficiency over the explicit method. For fine mesh clustering near the solid body surface, necessary to resolve surface shear stress and heat transfer rates, the implicit scheme achieved an order of magnitude reduction in computing time.

Descriptors:

• *FLOW FIELDS
• *NAVIER STOKES EQUATIONS
• *HYPERSONIC FLOW
• COMPRESSION
• HEAT TRANSFER
• ALGORITHMS
• SIMULATION
• NUMERICAL ANALYSIS
• RATES
• EFFICIENCY
• MESH
• SURFACES
• THREE DIMENSIONAL
• MATHEMATICAL PREDICTION
• SHEAR STRESSES
• VECTOR ANALYSIS
• FLAPS(CONTROL SURFACES)
• NUMERICAL METHODS AND PROCEDURES
• REYNOLDS NUMBER
• SOLID BODIES
• THREE DIMENSIONAL FLOW
• AFTERBODIES

Subject Categories:

• Theoretical Mathematics
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE