VERY LOW ASPECT RATIO WINGS IN HYPERSONIC FLOW,
Abstract
The configuration consisted of an 8-caliber long body of revolution with a low drag nose and four different sets of flat, rectangular wings varying in aspect ratio from 0.05 to 0.30. Wind-tunnel tests were conducted at Mach 8 and at Mach 3, 4 and 5. Theoretical calculations of the wing normal force coefficients were made for the same configurations. The agreement between the theoretical calculations and the experimental results was generally good. An observation was the relatively insignificant contribution to the wing normal force coefficient of the wing-on-body flow interference at Mach 8 while at lower Mach numbers the wing normal force contributed by wingon-body interference is of the same order of magnitude as the wing normal force itself. The reduced normal force at hypersonic Mach numbers might make it impractical to consider flat, very low aspect ratio wings as stabilizing surfaces for bodies in hypersonic flow. Wind-tunnel tests were conducted to determine the effect of the boundary-layer thickness of the body on the wing normal force coefficient. They were conducted at Mach 8 only. The effect of the body boundarylayer was small, enabling inviscid flow theory to be used in preliminary design calculations with a satisfactory degree of accuracy. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1963
- Accession Number
- AD0434923
Entities
People
- W. D. Piper
Organizations
- Naval Ordnance Laboratory