Experimental Investigation of Aerodynamic Interference Heat Transfer Around a Protuberance on a Flat Plate Subjected to Hypersonic Flow
Heat generation due to interference of hypersonic flow by a protuberance on the surface of a hypersonic craft is an important topic of study. Generally, designers try to keep the surface smooth, but protrusions with size of the order of the local boundary layer thickness have to be expected. They interfere with the flow and make it locally three-dimensional. Increased heat transfer rates will be felt on the protrusion as well as regions in the close vicinity. It is essential that these rates are properly quantified and documented since if design adjustments are not made to accommodate them, the performance of the aircraft might fall, the worst case holding disastrous results for the vehicle itself .
KeywordsHeat Transfer Heat Transfer Rate Recirculation Zone Hypersonic Flow Stanton Number
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- 1.Nestler, D.E.: The effects of surface discontinuities on convective heat transfer in hypersonic flow. AIAA Paper 85-0971 (1985)Google Scholar
- 3.Estruch-Samper, D., Stollery, J.L., MacManus, D.G., Lawson, N.J., Garry, K.P.: Hypersonic Interference Heating: a Semi-Empirical Hot Spot Predictive Approach. AIAA 2009-7444 (1968)Google Scholar
- 4.Van Driest, E.R.: Investigation of Laminar Boundary Layer in Compressible Fluids Using the Crocco Method. National Advisory Committee for Aeronautics, Technical Note 2597 (1952)Google Scholar
- 5.Vidal, R.J.: Model Instrumentation Techniques for Heat Transfer and Force Measurements in a Hypersonic Shock Tunnel. WADC TN 56-315, CAL Report No. AD-917-A-1 (1956)Google Scholar
- 7.Crabtree, L.F., Dommett, R.L., Woodley, J.G.: Estimation of Heat Transfer to Flat Plates, Cones and Blunt Bodies. Aeronautcial Research Council, Reports and Memoranda, No. 3637 (1970)Google Scholar