############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the CFD friction coefficients at y/b = 0.40 # # 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 -0.003903480 0.000431862 -0.003901539 0.002037521 -0.003881230 0.005001361 -0.003794814 0.009086597 -0.003616824 0.014068938 -0.003481860 0.019925637 -0.003422860 0.026564283 -0.003410062 0.034001045 -0.003430580 0.042277798 -0.003422690 0.051458012 -0.003402231 0.061603136 -0.003360309 0.072789192 -0.003308353 0.085127279 -0.003269205 0.098780304 -0.003224330 0.113772549 -0.003189937 0.130205855 -0.003163093 0.148343250 -0.003130746 0.168252617 -0.003104618 0.190109059 -0.003069148 0.212127686 -0.003028485 0.232456788 -0.002982669 0.251509279 -0.002934766 0.269591421 -0.002883356 0.287000656 -0.002826501 0.304060996 -0.002778562 0.321108371 -0.002730423 0.338483542 -0.002686385 0.356487811 -0.002642784 0.375444323 -0.002598900 0.395678610 -0.002555736 0.417514771 -0.002495266 0.441277623 -0.002434047 0.467339754 -0.002301040 0.495975673 -0.002137790 0.527461112 -0.001969392 0.562236905 -0.001855525 0.600486577 -0.001767084 0.639128625 -0.001593633 0.674934864 -0.001365324 0.708154500 -0.001198694 0.738996029 -0.001100691 0.767688572 -0.001055387 0.794382036 -0.001067390 0.819217384 -0.001123232 0.842319191 -0.001209144 0.863802373 -0.001316124 0.883779049 -0.001441841 0.902343154 -0.001581214 0.919561982 -0.001733875 0.935545146 -0.001899215 0.950385869 -0.002073390 0.964127541 -0.002251230 0.976892352 -0.002469641 0.988698900 -0.002566793 0.999662936 -0.002244825 0.000000000 0.003794095 0.000694521 0.003773595 0.002502106 0.003872191 0.005409380 0.003877833 0.009264900 0.003869077 0.013965179 0.003872023 0.019538667 0.003918016 0.025929507 0.003993968 0.033177551 0.004071161 0.041332897 0.004165723 0.050449308 0.004230037 0.060596187 0.004281572 0.071852677 0.004309778 0.084329166 0.004303879 0.098177761 0.004277498 0.113401860 0.004235709 0.130112171 0.004148621 0.148554772 0.004060047 0.168788508 0.003959144 0.190983579 0.003863894 0.213317201 0.003776954 0.233913794 0.003699789 0.253188282 0.003624551 0.271455526 0.003432353 0.289022714 0.002982025 0.306219697 0.002381222 0.323389143 0.001981454 0.340876311 0.001947030 0.358979821 0.002181043 0.378031492 0.002458949 0.398357689 0.002656284 0.420282602 0.002756563 0.444133192 0.002832522 0.470286012 0.002837975 0.499018490 0.002851122 0.530614436 0.002869206 0.565523565 0.002908219 0.603950143 0.002895740 0.642823815 0.002604543 0.678907573 0.001828704 0.712377727 0.001016362 0.743407071 0.000739091 0.772202909 0.000803706 0.798887730 0.000825687 0.823607922 0.000764476 0.846503317 0.000671030 0.867701650 0.000566872 0.887334168 0.000464499 0.905515134 0.000374842 0.922323525 0.000302730 0.937880456 0.000246226 0.952295065 0.000199536 0.965617836 0.000162680 0.977976084 0.000102475 0.989398420 0.000036596 1.000000000 0.000154261