PRESSURE AND HEAT TRANSFER MEASUREMENTS OVER A CIRCULAR CYLINDER AT ANGLES OF ATTACK UP TO 15 AT M11
Abstract
As a continuation of a fundamental study of hypersonic wings and control surfaces, some detailed pressure distribution and heat transfer results have been obtained about a circular cylinder with various nose shapes at angles of attack up to 15 degrees and at azimuth angles from zero to 180 degrees. The tests were carried out in the Princeton University 3 inch helium hypersonic wind tunnel at a Mach number of 11. The experimental results were compared with theory along the windward side and in the cross flow plane for both the pressure and heat transfer distributions. Some effects of the nose shape on the flow over the circular cylinder under study were determined up to 13 cylinder diameters back from the nose.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1963
- Accession Number
- AD0409142
Entities
People
- C. C. Horstman
Organizations
- Princeton University