It is assumed that the variation in the lift-to-drag ratio with lift of the caret wing is typical of that of a lifting configuration for Mach numbers in the range where nozzle deflections are most significant. Numerical optimization studies using this assumption show that optimum nozzle thrust deflection angles are commonly 50% larger than those suggested by analyses at constant lift-to-drag ratio. Analytical results are obtained for the optimum deflection angle based on Newtonian, Busemann second order and linear theory relationships. (Author)
Optimum Engine Thrust Deflection for High-Speed Cruising Aircraft
1972
43 pages
Report
No indication
English
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