############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the CFD friction coefficients at y/b = 0.50 # # 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 0.000000000 -0.003955102 0.000468125 -0.003866916 0.002084277 -0.003828292 0.005038781 -0.003760721 0.009131181 -0.003581172 0.014129799 -0.003459413 0.020001505 -0.003391334 0.026648927 -0.003377894 0.034089055 -0.003295852 0.042369556 -0.003267319 0.051554840 -0.003246175 0.061710641 -0.003213247 0.061710700 -0.003213251 0.072907627 -0.003174036 0.085272245 -0.003134127 0.098953165 -0.003099459 0.113975115 -0.003075046 0.130443931 -0.003051644 0.148630440 -0.003041012 0.168573543 -0.003028044 0.190490872 -0.003013277 0.212543756 -0.002988364 0.232914895 -0.002951598 0.252015471 -0.002901820 0.270132869 -0.002849624 0.287572443 -0.002798480 0.304657400 -0.002751833 0.321721375 -0.002705671 0.339114577 -0.002662700 0.357136190 -0.002622867 0.376109093 -0.002577662 0.396358848 -0.002522578 0.418205798 -0.002435380 0.441984117 -0.002301009 0.468045384 -0.002102831 0.496656924 -0.001929602 0.528112233 -0.001831518 0.562838554 -0.001796186 0.601010680 -0.001724687 0.639553428 -0.001512839 0.675236046 -0.001246774 0.708338022 -0.001072673 0.739073515 -0.000976752 0.767670870 -0.000928464 0.794287741 -0.000939520 0.794287503 -0.000939526 0.819067717 -0.000995369 0.842129290 -0.001078357 0.863587856 -0.001182928 0.883537054 -0.001306760 0.902090549 -0.001449865 0.919336379 -0.001611857 0.935337842 -0.001787365 0.950197220 -0.001975875 0.963993430 -0.002168736 0.976784408 -0.002394765 0.988657713 -0.002581509 0.999672115 -0.002431122 0.000000000 0.003906493 0.000686278 0.003969805 0.002476785 0.004147992 0.005368959 0.004201181 0.009206917 0.004213434 0.013876787 0.004226754 0.019421710 0.004248068 0.025802536 0.004242152 0.033058655 0.004155004 0.041215032 0.004179418 0.041215330 0.004178191 0.050319936 0.004206431 0.060439385 0.004261187 0.071659967 0.004283753 0.084093943 0.004294824 0.097893387 0.004269240 0.113069318 0.004224555 0.129727140 0.004156139 0.148124531 0.004069250 0.168295622 0.003986613 0.190449998 0.003901699 0.212723121 0.003828803 0.233274564 0.003751423 0.252519667 0.003678573 0.270753175 0.003620541 0.288285166 0.003571874 0.305447221 0.003501921 0.322578073 0.003311826 0.340026885 0.002911863 0.358097255 0.002420437 0.377119601 0.002116126 0.397416413 0.002140978 0.419315457 0.002370767 0.443148106 0.002639370 0.469281971 0.002799111 0.497985244 0.002889929 0.529566526 0.002947354 0.564462006 0.002992335 0.602881610 0.002914989 0.641755223 0.002395700 0.677849114 0.001509687 0.711338520 0.001007079 0.742399573 0.001056017 0.771233380 0.001183059 0.797967434 0.001168405 0.797967196 0.001168084 0.822747529 0.001073950 0.845712960 0.000941540 0.866989791 0.000797225 0.886690319 0.000656590 0.904947102 0.000532631 0.921856582 0.000430150 0.937496245 0.000354195 0.951983094 0.000295252 0.965402246 0.000248566 0.977822661 0.000161176 0.989333332 0.000033733 1.000000000 0.000072852