############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the CFD pressure coefficients at y/b = 0.20 # # 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 0.999865353 0.229343191 0.988895178 0.246111125 0.977047324 0.268096417 0.964289367 0.278552085 0.950515687 0.285469115 0.935674906 0.286053836 0.919681549 0.281744093 0.902430594 0.272120088 0.883853674 0.257660538 0.863861620 0.237896517 0.842328191 0.212737158 0.819148839 0.181191698 0.794205308 0.141300231 0.767365813 0.090602249 0.738479912 0.030396048 0.707393169 -0.041346177 0.673942447 -0.146349028 0.637880921 -0.277987033 0.599061310 -0.383581847 0.560649693 -0.430521160 0.525778234 -0.429794073 0.494223118 -0.409266293 0.465563416 -0.384857535 0.439476430 -0.360218734 0.415701240 -0.335305363 0.393875092 -0.310813427 0.373661309 -0.287737787 0.354732990 -0.265530139 0.336763173 -0.243818805 0.319428235 -0.222323656 0.302425325 -0.200582519 0.285411388 -0.177939460 0.268050283 -0.153929412 0.250016361 -0.128242865 0.231011420 -0.100694977 0.210742980 -0.071015507 0.188811883 -0.040899362 0.167021304 -0.014128042 0.147206634 0.008152407 0.129141122 0.026592756 0.112789027 0.042243652 0.097880043 0.056576002 0.084293753 0.069489859 0.072007395 0.081742346 0.060875054 0.095318742 0.050776836 0.111928269 0.041639742 0.131843016 0.033399247 0.160850391 0.025995705 0.198008776 0.019386690 0.242090017 0.013557025 0.309807748 0.008662201 0.411468804 0.004734557 0.535938442 0.001941142 0.646033525 0.000408349 0.698229671 0.000000000 0.668761730 0.000000000 0.668761730 0.000616979 0.589181244 0.002281389 0.477029830 0.005012210 0.346814483 0.008668395 0.223298371 0.013157800 0.103892572 0.018521722 -0.013515127 0.024713831 -0.132158086 0.031778447 -0.258495361 0.039787363 -0.396963835 0.048814137 -0.535186887 0.058936112 -0.667965591 0.070234627 -0.789596736 0.082807362 -0.893263340 0.096776091 -0.978216350 0.112132028 -1.047107816 0.128984705 -1.095555544 0.147572622 -1.116172075 0.167918637 -1.102218866 0.190241903 -1.029643893 0.212664440 -0.898790181 0.233342245 -0.769478500 0.252701402 -0.688751161 0.271040410 -0.650091708 0.288667619 -0.632795036 0.305918992 -0.627071619 0.323132575 -0.628411233 0.340658993 -0.633527398 0.358802825 -0.639969051 0.377890587 -0.646179736 0.398247540 -0.650981486 0.420199007 -0.655485868 0.444079369 -0.660463750 0.470248312 -0.666375637 0.498956144 -0.673500001 0.530520797 -0.679834664 0.565353751 -0.685110807 0.603680372 -0.690554142 0.642381549 -0.689898968 0.678318799 -0.651354551 0.711617768 -0.536638975 0.742532432 -0.374417692 0.771216869 -0.253011018 0.797803760 -0.192930385 0.822449684 -0.152437538 0.845300019 -0.116550058 0.866481662 -0.085149258 0.886113465 -0.057601370 0.904334664 -0.033152539 0.921244264 -0.011312265 0.936918855 0.008630672 0.951469541 0.026201151 0.964989424 0.043968949 0.977522373 0.057367131 0.989186943 0.076114051 1.000000000 0.084029540