Flow over a Biconic Configuration with an Afterbody Compression Flap.
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 MacCormack's 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1984
- Accession Number
- ADA151882
Entities
People
- J. S. Shang
- R. W. Maccormack
Organizations
- Wright Laboratory