############################################################################## # # TA1 External Aerodynamics AC1-02 RAE M2155 Wing # # File contains the CFD pressure coefficients at y/b = 0.30 # # 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 = Cp %Column2Units = %Column2Type = Real %End of Metadata 0.999721885 0.285058051 0.988846242 0.300345600 0.977079988 0.324430704 0.964384437 0.334386200 0.950661242 0.341683000 0.935859561 0.342365623 0.919897079 0.339212298 0.902668834 0.331304669 0.884109080 0.319180727 0.864128649 0.302093565 0.842603087 0.279681981 0.819431484 0.250661194 0.794498801 0.213469595 0.767678976 0.165478662 0.738822103 0.106660351 0.707772434 0.037585076 0.674367547 -0.046862267 0.638341904 -0.129595697 0.599546790 -0.188996240 0.561157346 -0.228166118 0.526298344 -0.253534704 0.494750023 -0.269504577 0.466089129 -0.277425706 0.439997256 -0.280862033 0.416214317 -0.274609745 0.394378811 -0.266799241 0.374154806 -0.256280929 0.355215728 -0.243288100 0.337236553 -0.228537574 0.319892436 -0.212054014 0.302881300 -0.193761781 0.285859883 -0.173031211 0.268494070 -0.149313211 0.250454932 -0.123281412 0.231444791 -0.095002748 0.211175263 -0.063775614 0.189239562 -0.031478141 0.167444766 -0.002428120 0.147621855 0.021866584 0.129543692 0.042269088 0.113175116 0.058623806 0.098245718 0.072811894 0.084647119 0.088817172 0.072361156 0.108322613 0.061234720 0.130883366 0.051143937 0.156551048 0.042011082 0.184564412 0.033765376 0.214525253 0.026346521 0.261019081 0.019715078 0.311840385 0.013864133 0.382757246 0.008931443 0.481491089 0.004928852 0.589357853 0.002026288 0.674967170 0.000402676 0.692351282 0.000000000 0.612209857 0.000000000 0.598300695 0.000754477 0.450663358 0.002615817 0.283063143 0.005571924 0.110350043 0.009455206 -0.039241966 0.014173750 -0.171940416 0.019769102 -0.292342693 0.026178753 -0.407567441 0.033429354 -0.529573381 0.041604366 -0.661199689 0.050761238 -0.787801147 0.060970105 -0.904440701 0.072311021 -1.008945704 0.084883980 -1.098814130 0.098833650 -1.172357917 0.114155710 -1.230936050 0.130953997 -1.273002505 0.149501070 -1.296078444 0.169812679 -1.304184914 0.192103893 -1.298253417 0.214499384 -1.258814931 0.235156596 -1.145807505 0.254492342 -0.979716659 0.272807151 -0.846249580 0.290414512 -0.770829856 0.307647645 -0.729458213 0.324845850 -0.708178878 0.342361212 -0.696841598 0.360494316 -0.686806917 0.379573226 -0.669021666 0.399924219 -0.632668674 0.421871603 -0.574685574 0.445744634 -0.504789531 0.471913636 -0.442897409 0.500630319 -0.402177095 0.532219708 -0.378707737 0.567094266 -0.363614351 0.605479777 -0.349896669 0.644252598 -0.337019444 0.680260241 -0.325307190 0.713618934 -0.313618928 0.744575560 -0.301580429 0.773279488 -0.287438214 0.799858034 -0.265779912 0.824466765 -0.234455645 0.847248554 -0.197615713 0.868331611 -0.158099547 0.887837112 -0.118051216 0.905904055 -0.078776747 0.922633171 -0.042259518 0.938104510 -0.008526668 0.952438414 0.020102084 0.965723693 0.046930291 0.978019178 0.064621948 0.989433169 0.088803276 1.000000000 0.091756344