############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the Experimental pressure coefficients at y/b = 0.30 # # Mach number : 0.854 # Reynolds number : 4.1 x 10^6 # Angle of incidence : 1.50 (deg) ############################################################################## %AC = 1-02 %Column1Name = x/c %Column1Units = %Column1Type = Real %Column2Name = Cp %Column2Units = %Column2Type = Real %End of Metadata 0.0500 -0.6054 0.0750 -0.8518 0.1000 -0.9947 0.1250 -1.0651 0.1500 -1.1007 0.1750 -1.1010 0.2000 -1.1001 0.2250 -1.0395 0.2500 -0.8455 0.2750 -0.7285 0.3000 -0.6834 0.3250 -0.6726 0.3500 -0.6704 0.3750 -0.6802 0.4000 -0.6894 0.4250 -0.6985 0.4500 -0.7010 0.4750 -0.7086 0.5000 -0.7032 0.5250 -0.7058 0.5500 -0.7121 0.5750 -0.7225 0.6000 -0.7209 0.6250 -0.7190 0.6500 -0.6988 0.6750 -0.5796 0.7250 -0.3016 0.7500 -0.2537 0.8000 -0.1969 0.8500 -0.1247 0.9000 -0.0502 0.9500 0.0179 0.9750 0.0447