############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the CFD friction coefficients at y/b = 0.95 # # Mach number : 0.806 # Reynolds number : 4.1 x 10^6 # Angle of incidence : 2.50 (deg) ############################################################################## %AC = 1-02 %Column1Name = x/c %Column1Units = %Column1Type = Real %Column2Name = Cf %Column2Units = %Column2Type = Real %End of Metadata 0.000000000 -0.004413729 0.000442055 -0.004561075 0.002082888 -0.005016505 0.005072972 -0.005103006 0.009198061 -0.004816155 0.014235514 -0.004434895 0.020156752 -0.004181053 0.020157561 -0.004179812 0.026852313 -0.004073208 0.034342378 -0.003883831 0.042676028 -0.003738880 0.051912677 -0.003611545 0.062119648 -0.003492648 0.073376544 -0.003372105 0.085799761 -0.003290233 0.099540748 -0.003202936 0.114631146 -0.003138981 0.131173164 -0.003115007 0.149429947 -0.003089833 0.169460446 -0.003068228 0.191460013 -0.003016267 0.191460490 -0.003016512 0.213600680 -0.002987681 0.234043688 -0.002948653 0.253197491 -0.002908617 0.271364033 -0.002851577 0.288840860 -0.002786042 0.305955380 -0.002726215 0.323043913 -0.002660097 0.340447247 -0.002590828 0.358467996 -0.002512230 0.377427578 -0.002433122 0.397644877 -0.002359245 0.419438601 -0.002292773 0.443135172 -0.002225948 0.469092727 -0.002152542 0.497574419 -0.002075986 0.497576833 -0.002075781 0.528861940 -0.002001603 0.563388884 -0.001923527 0.601354063 -0.001816699 0.639698684 -0.001663085 0.675289094 -0.001508601 0.708319187 -0.001406008 0.739041328 -0.001369964 0.767643273 -0.001387878 0.794262648 -0.001439561 0.819034636 -0.001507342 0.842079759 -0.001589424 0.863512158 -0.001684966 0.883451402 -0.001794805 0.901996076 -0.001920411 0.919221342 -0.002059968 0.935229301 -0.002215420 0.950110137 -0.002378778 0.963918269 -0.002555628 0.963917971 -0.002555720 0.976754308 -0.002745618 0.988660872 -0.002920355 0.999716759 -0.002990907 0.000000000 0.004646534 0.000767541 0.004639860 0.002595820 0.004817361 0.005491777 0.004805796 0.009310593 0.004865487 0.013943448 0.004885844 0.019434903 0.004855329 0.019434903 0.004854464 0.025765259 0.004933343 0.032933228 0.004964523 0.041000482 0.004913312 0.050030634 0.004799173 0.060087293 0.004701963 0.071241021 0.004655856 0.083604828 0.004616641 0.097328216 0.004546311 0.112434924 0.004483061 0.129029244 0.004387209 0.147361755 0.004300358 0.167486697 0.004156749 0.189582810 0.003700730 0.189582810 0.003701357 0.211819053 0.002419160 0.232338428 0.000768470 0.251547635 -0.000146308 0.269756943 -0.000186002 0.287266225 0.000072973 0.304410279 0.000230130 0.321527213 0.000270524 0.338964641 0.000296693 0.357023507 0.000382957 0.376031041 0.000535165 0.396318406 0.000731142 0.418213516 0.000956145 0.442038447 0.001186212 0.468179554 0.001388116 0.496904373 0.001549153 0.528506458 0.001644556 0.528506458 0.001644355 0.563423753 0.001665258 0.601866364 0.001616353 0.640738726 0.001507068 0.676850796 0.001378019 0.710347474 0.001237756 0.741436779 0.001086529 0.770300627 0.000926256 0.797068954 0.000758583 0.821890712 0.000596038 0.844905496 0.000450138 0.866237760 0.000329326 0.886012852 0.000235633 0.904350519 0.000170037 0.921326339 0.000122690 0.937052071 0.000088451 0.951634884 0.000048634 0.965131223 0.000009825 0.965130925 0.000009053 0.977649271 -0.000077319 0.989242733 -0.000186990 0.999999940 -0.000137564