Hypersonic Flow of a Real Gas on the Windward Side of a Delta Wing.
Abstract
The inviscid flow on the windward side of a flat, sharp-edged delta wing is studied for orbital entry at angles of attack near maximum lift. The solutions are numerical and use the one-strip approximation in the method of integral relations. Properties at the wing surface are given for air in thermodynamic equilibrium for angles of attack of 50 and 60 deg and sweep angles of 70, 75, and 80 deg. These solutions are used to illustrate the cross-flow at the wing surface and are shown to agree with those for a perfect gas with an appropriately chosen, constant effective specific heat ratio. Additional solutions for a perfect gas are given for angles of attack between 30 and 70 deg. Surface pressures at the centerline are shown to be accurately approximated by Newtonian theory or by those pressures on a circular cone with the same surface inclination for sweep angles greater than 75 deg. The cross-flow velocity gradient at the centerline is found to be different from that on an equivalent circular disk. It is demonstrated that the solution for a two-dimensional, flat-faced body is a fair approximation of that obtained for a delta wing with large sweep. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 19, 1971
- Accession Number
- AD0731763
Entities
People
- B. E. Pearce
Organizations
- The Aerospace Corporation