############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the CFD pressure coefficients at y/b = 0.60 # # 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 0.999716043 0.199053138 0.988664150 0.225564361 0.976752698 0.241425619 0.963935494 0.253018588 0.950108945 0.259707093 0.935233951 0.262915164 0.935233712 0.262927979 0.919224799 0.262530327 0.901988089 0.259034783 0.883452117 0.252550811 0.863526464 0.243391320 0.842106938 0.231388330 0.819088042 0.215958521 0.794359326 0.195999742 0.767809868 0.168324888 0.739304245 0.132203400 0.708650410 0.086192802 0.675677299 0.020411883 0.640106916 -0.064606689 0.640105486 -0.064522818 0.601721942 -0.155290470 0.563648462 -0.243774071 0.528999805 -0.334656239 0.497594386 -0.439848483 0.469001055 -0.551129460 0.442954063 -0.634450376 0.419191480 -0.667337418 0.397337347 -0.659541667 0.377077520 -0.632745206 0.358087718 -0.601520300 0.340048343 -0.571147859 0.322634995 -0.542255104 0.305549592 -0.513727069 0.305549443 -0.513747334 0.288438320 -0.484120041 0.270968169 -0.451149553 0.252814680 -0.413709313 0.233675137 -0.372665495 0.213258073 -0.329481989 0.191143408 -0.288583785 0.169178486 -0.255370438 0.149170101 -0.230917171 0.130941898 -0.214626223 0.114421122 -0.203531668 0.099349692 -0.191994935 0.085625514 -0.177643716 0.073223904 -0.159972727 0.061986897 -0.137255356 0.051797517 -0.108251356 0.042584024 -0.073318198 0.034275401 -0.025238449 0.026809175 0.031522870 0.026811328 0.031329516 0.020137168 0.094388306 0.014235691 0.177386299 0.009211075 0.283544391 0.005102620 0.422331929 0.002138141 0.543630302 0.000491208 0.616195679 0.000000000 0.586825132 0.000000000 0.586825132 0.000690367 0.471108466 0.002481105 0.327697158 0.005349955 0.164701447 0.009157614 0.019594196 0.013805647 -0.110284388 0.019327149 -0.228751123 0.025657691 -0.336894959 0.025656909 -0.336844295 0.032826517 -0.447074056 0.040914312 -0.557759702 0.049965393 -0.648850381 0.060047131 -0.728553772 0.071232110 -0.802904665 0.083629347 -0.870430112 0.097386301 -0.929003119 0.112523593 -0.978888214 0.129141226 -1.019754648 0.147491053 -1.047555447 0.167635143 -1.059187293 0.189741388 -1.058266044 0.211981967 -1.050376177 0.232498467 -1.039140701 0.251708776 -1.026002169 0.269915491 -1.011761069 0.287418038 -0.997225344 0.287412018 -0.997186422 0.304552943 -0.983076096 0.321661055 -0.969748497 0.339092702 -0.957390130 0.357146055 -0.944060564 0.376149803 -0.918819427 0.396428704 -0.861846924 0.418308288 -0.770065427 0.442114741 -0.674575269 0.468229890 -0.608766377 0.496924400 -0.580268383 0.528490007 -0.581826270 0.563369751 -0.593679488 0.601790488 -0.574307978 0.640633166 -0.466998011 0.640624583 -0.468024671 0.676744819 -0.310237318 0.710234046 -0.220114633 0.741337359 -0.194851950 0.770204306 -0.178034738 0.796977997 -0.155468345 0.821807563 -0.126944467 0.844830275 -0.095721878 0.866173089 -0.063093849 0.885955572 -0.030582998 0.904297173 0.000234357 0.921293676 0.027801815 0.937028646 0.051914722 0.937026858 0.052028406 0.951610446 0.071305543 0.965130866 0.088292226 0.977642596 0.098471843 0.989247501 0.110481359 1.000000000 0.108528227