A Parametric Study of Boundary Layer Effects on Maximum Thrust Nozzle Contours.
Technical rept. 1 Sep 66-31 Aug 69,
PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER
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An optimization analysis employing the calculus of variations and a numerical relaxation scheme for applying the results are presented for the design of optimum, axisymmetric thrust nozzle contours including boundary layer effects. The method is illustrated by comparison with a known solution without boundary layer effects. A parametric study of boundary layer effects for a range of parameters typical of scramjet operation is presented. Author
- Jet and Gas Turbine Engines