Validation of a Computer Code for Analysis of Subsonic Aerodynamic Performance of Wings with Flaps in Combination with a Canard Or Horizontal Tail and an Application to Optimization
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20 a deg 44°-swept trapezoidal-wing fighter 60°-swept delta-wing fighter aerodynamic performance airfoil angle of attack arrow-wing supersonic transport attached-flow method attainable leading-edge thrust attainable thrust camber surface canard configuration canard incidence angle canard or horizontal-tail computer code curves default drag drag coefficient edge-flap deflection element aspect ratio estimate Experiment Theory experimental data fighter with canard fighter with horizontal Figure 28 flap deflection angle flow force Without thrust forward-swept wing fraction of chord horizontal tail horizontal-tail configuration horizontal-tail incidence angle inboard/outboard increasing order INPT1 JBYMAX Langley Research Center leading edge leading-edge-flap deflection lift coefficient lifting surfaces limit of 21 linearized-theory matched leading maximum suction parameter NASA pitching pitching-moment planform restraints Reynolds number root chord second surface solution spanwise stations Subsonic table of leading-edge Theoretical and experimental theory and experiment Theory With attainable thrust and vortex thrust or vortex tion TXMTEFD undeflected flaps vortex force Vortex Lift