AERODYNAMIC HEATING IN THE VICINITY OF SURFACE PROTUBERANCES.
NORTH AMERICAN AVIATION INC COLUMBUS OHIO ENGINEERING DEPT
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An analytical method based on the two-parameter momentum-integral concept has been developed for laminar supersonic flows over a two-dimensional protuberance. This method is applicable both to the case where the external pressure field is prescribed and to the free interaction problem for which the mathematical solution for the local flow disturbance is not directly influenced by the downstream geometry of the disturbance source. By comparing with experimentally determined pressure and heat transfer data for a wide range of separated flow problems, it has been found that the theory is valid in regions up to and beyond the separation point. The analytical procedures can also be applied to separated flows on the plane of symmetry upstream of a cylindrical protuberance and over an unyawed axisymmetric body. An experimental program utilizing the DTMB hypersonic tunnel facility has been prepared for measuring surface pressure and heat transfer rates in the vicinity of cylindrical protuberances. Protuberance model design and fabrication, as well as preliminary tunnel check-outs have been completed. Development of semi-empirical procedures for predicting protuberance-induced heating effects and verification of the two-parameter analytical theory may be undertaken when quantitative test data are available. Author
- Fluid Mechanics