Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number
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4r AEDC AEDC 16 AEDC 16T aerodynamic airfoil angle of attack B1/2 FIGURE chord chordwise location COMPOSITE CORRELATION correlated separation development correlation curves CPTE CPTEO and B1/2 data to flight defined development of trailing-edge effective angle extrapolation procedure F-8 SCW Figure 48 FINAL CORRELATION flight data flight Reynolds number flight test high Reynolds number high speed transport INITIAL CORRELATION J. F. Cahill Lockheed-Georgia Company low Reynolds number Mach number and/or NASA number and angle number and/or angle parameter PML peak negative pressure Pearcey planform PLATEAU PRESSURE PML FIGURE pressure distribution data RAE Model 864 Reynolds number changes scale effect curves semispan model separation criteria shock pressure rise shown in Figure single curve supercritical wings swept wing terminal shock three spanwise stations trailing edge separation trailing-edge pressure coefficient trailing-edge pressure recovery transonic tunnel and flight value of CPSH values of B1/2 variation of trailing-edge vortex wind tunnel data XCSH