HEAT TRANSFER AND PRESSURE DISTRIBUTION AT A MACH NUMBER OF 6.8 ON BODIES WITH CONICAL FLARES AND EXTENSIVE FLOW SEPARATION
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC
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An investigation of heat transfer and pressure distribution on flared bodies under laminar, transitional, and turbulent boundary-layer conditions was conducted in the Langley 11-inch hypersonic tunnel at a Mach number of 6.8. The results indicated extensive zones of separated flow ahead of the flares when the boundary layer was laminar at separation. The rate of heat transfer in these zones was considerably less than in attached laminar flow except in regions where transition occurred on the separated boundary. In the turbulent cases the separated zone was so localized as to be undiscernible in schlieren photographs. Downstream of flow reattachment on the flare, the Stanton number based on local conditions was several times greater for large flare angles than the values existing in attached flow on the body ahead of the flare. The results are analyzed to determine the adequacy of available theoretical methods for predicting heat transfer in cases where the transition point and the limits of the separated zone are known.
- Numerical Mathematics