Transonic Flow-Field Calculation Around Ogive Cylinders by Nonlinear-Linear Stretching Method,
Abstract
An inviscid transonic approximation theory is developed to calculate the entire mixed flow field around a nonlifting slender ogive body. Because the nonlinearity in the governing transonic equation was retained, the solution accounts for the shock wave and its strength as well as the location. In supercritical flow, the 'supersonic pocket' and, in subcritical flow, the 'subsonic pocket' were obtained. In general, the disturbance extends for quite a distance in the radial direction as expected in transonic flow. Finally, the theory was checked against available wind-tunnel and free-flight experiments, and good agreement was shown. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1970
- Accession Number
- AD0872516
Entities
People
- Jain-ming Wu
- Kinya Aoyama
Organizations
- University of Tennessee Space Institute