AN INTEGRAL METHOD SOLUTION FOR MASSIVE BLOWING FROM SLENDER BODIES IN LAMINAR VISCOUS HYPERSONIC FLOW.
Rept. for Nov 65-Aug 66,
AEROSPACE CORP EL SEGUNDO CA LABS DIV
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An appraisal is made of the usefulness of boundary layer theory in flow problems involving injection where the blowing rates are from ten to a thousand times larger than those associated with transpiration-cooling applications. An approximate integral-method solution is given for massive blowing in laminar flow and compared with the results obtained by Hartunian and Spencer for uniform massive blowing on hypersonic wedges and cones. The theoretical solution is based on a constant property homogeneous gas model and pertains to the limiting case where the boundary layer is blown off the surface. In this case, it is shown for uniform blowing that the effects of the axial pressure gradient can be neglected to a good approximation, permitting a closed form solution which takes into account both the transverse curvature effect and the influence of viscous-inviscid flow interaction on the local pressure level. The predicted shape and location of the dividing streamline between blown and free stream gas are in good agreement with experimental results over a wide range of massive blowing rates. Author
- Fluid Mechanics