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FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-150/20 (fx78k150-il)
Reynolds number: 500,000
Max Cl/Cd: 114.73 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k150-il-500000.txt
Download as CSV file: xf-fx78k150-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-150/20                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.0864   0.10475   0.10143  -0.0955   0.7414   0.0234
 -12.750  -0.0846   0.10111   0.09780  -0.0972   0.7408   0.0234
 -12.500  -0.0905   0.09545   0.09216  -0.0989   0.7402   0.0239
 -12.250  -0.0881   0.09186   0.08856  -0.1001   0.7394   0.0240
 -12.000  -0.0867   0.08807   0.08477  -0.1014   0.7388   0.0241
 -11.750  -0.0895   0.08343   0.08014  -0.1032   0.7382   0.0240
 -11.500  -0.0753   0.08271   0.07939  -0.1028   0.7373   0.0251
 -11.250  -0.2891   0.05359   0.05014  -0.1297   0.7419   0.0133
 -11.000  -0.3473   0.04387   0.04015  -0.1353   0.7405   0.0135
 -10.750  -0.3674   0.04065   0.03675  -0.1336   0.7390   0.0134
 -10.500  -0.3952   0.03737   0.03325  -0.1297   0.7377   0.0134
 -10.250  -0.4125   0.03524   0.03093  -0.1250   0.7366   0.0135
 -10.000  -0.4335   0.03300   0.02845  -0.1191   0.7355   0.0136
  -9.750  -0.4410   0.03083   0.02599  -0.1148   0.7344   0.0135
  -9.500  -0.4460   0.02852   0.02347  -0.1109   0.7333   0.0140
  -9.250  -0.4425   0.02657   0.02128  -0.1078   0.7322   0.0142
  -9.000  -0.4308   0.02544   0.02000  -0.1058   0.7310   0.0144
  -8.750  -0.4122   0.02528   0.01982  -0.1047   0.7296   0.0152
  -8.500  -0.3956   0.02457   0.01898  -0.1032   0.7281   0.0161
  -8.250  -0.3822   0.02287   0.01700  -0.1012   0.7268   0.0164
  -8.000  -0.3629   0.02218   0.01612  -0.1000   0.7257   0.0174
  -7.750  -0.3435   0.02120   0.01493  -0.0988   0.7247   0.0177
  -7.500  -0.3273   0.01912   0.01261  -0.0972   0.7237   0.0185
  -7.250  -0.3059   0.01858   0.01205  -0.0965   0.7228   0.0199
  -7.000  -0.2832   0.01816   0.01154  -0.0958   0.7219   0.0214
  -6.750  -0.2595   0.01778   0.01106  -0.0952   0.7209   0.0229
  -6.500  -0.2389   0.01697   0.01015  -0.0942   0.7200   0.0251
  -6.250  -0.2163   0.01672   0.00991  -0.0935   0.7187   0.0273
  -6.000  -0.1933   0.01645   0.00959  -0.0929   0.7175   0.0296
  -5.750  -0.1724   0.01590   0.00900  -0.0919   0.7162   0.0327
  -5.500  -0.1493   0.01566   0.00877  -0.0913   0.7149   0.0361
  -5.250  -0.1252   0.01548   0.00854  -0.0908   0.7136   0.0391
  -5.000  -0.1038   0.01497   0.00800  -0.0898   0.7123   0.0431
  -4.750  -0.0796   0.01474   0.00776  -0.0893   0.7110   0.0476
  -4.500  -0.0542   0.01462   0.00759  -0.0891   0.7099   0.0519
  -4.250  -0.0317   0.01423   0.00721  -0.0883   0.7089   0.0589
  -4.000  -0.0064   0.01410   0.00702  -0.0880   0.7081   0.0640
  -3.750   0.0167   0.01378   0.00672  -0.0873   0.7072   0.0736
  -3.500   0.0409   0.01358   0.00652  -0.0868   0.7063   0.0850
  -3.250   0.0649   0.01343   0.00640  -0.0863   0.7054   0.1009
  -3.000   0.0862   0.01324   0.00636  -0.0854   0.7039   0.1309
  -2.750   0.1060   0.01298   0.00634  -0.0842   0.7021   0.1889
  -2.500   0.1245   0.01263   0.00634  -0.0829   0.7005   0.2780
  -2.250   0.1407   0.01217   0.00631  -0.0811   0.6990   0.3970
  -2.000   0.1490   0.01145   0.00623  -0.0775   0.6976   0.5734
  -1.750   0.1569   0.01095   0.00644  -0.0730   0.6962   0.7641
  -1.500   0.1792   0.01114   0.00666  -0.0716   0.6950   0.8174
  -1.250   0.2025   0.01127   0.00672  -0.0706   0.6940   0.8367
  -1.000   0.2276   0.01140   0.00682  -0.0699   0.6932   0.8500
  -0.750   0.2541   0.01155   0.00693  -0.0694   0.6923   0.8617
  -0.500   0.2804   0.01169   0.00705  -0.0690   0.6915   0.8718
  -0.250   0.3016   0.01190   0.00723  -0.0677   0.6901   0.8805
   0.000   0.3233   0.01213   0.00753  -0.0665   0.6876   0.8902
   0.250   0.3451   0.01232   0.00774  -0.0652   0.6857   0.9011
   0.500   0.3675   0.01241   0.00784  -0.0640   0.6840   0.9123
   0.750   0.3905   0.01246   0.00789  -0.0628   0.6826   0.9231
   1.000   0.4199   0.01246   0.00790  -0.0629   0.6814   0.9341
   1.250   0.4484   0.01243   0.00785  -0.0631   0.6804   0.9411
   1.500   0.4808   0.01239   0.00778  -0.0642   0.6795   0.9443
   1.750   0.5103   0.01235   0.00771  -0.0649   0.6786   0.9464
   2.000   0.5387   0.01231   0.00764  -0.0653   0.6777   0.9486
   2.250   0.5650   0.01233   0.00764  -0.0653   0.6767   0.9509
   2.500   0.5814   0.01257   0.00798  -0.0637   0.6730   0.9540
   2.750   0.6098   0.01264   0.00807  -0.0643   0.6708   0.9555
   3.000   0.6398   0.01264   0.00809  -0.0652   0.6691   0.9569
   3.250   0.6709   0.01260   0.00805  -0.0663   0.6676   0.9584
   3.500   0.7017   0.01255   0.00802  -0.0672   0.6664   0.9598
   3.750   0.7332   0.01244   0.00791  -0.0683   0.6653   0.9610
   4.000   0.7648   0.01234   0.00781  -0.0693   0.6642   0.9624
   4.250   0.7959   0.01228   0.00776  -0.0703   0.6632   0.9638
   4.500   0.8169   0.01249   0.00807  -0.0696   0.6599   0.9664
   4.750   0.8467   0.01260   0.00825  -0.0707   0.6569   0.9676
   5.000   0.8798   0.01258   0.00830  -0.0722   0.6548   0.9687
   5.250   0.9138   0.01253   0.00829  -0.0739   0.6532   0.9697
   5.500   0.9529   0.01187   0.00762  -0.0760   0.6506   0.9700
   5.750   0.9862   0.01111   0.00690  -0.0769   0.6420   0.9712
   6.000   1.0240   0.01035   0.00609  -0.0787   0.6353   0.9716
   6.250   1.0522   0.00993   0.00575  -0.0789   0.6227   0.9736
   6.500   1.0811   0.00966   0.00551  -0.0794   0.6064   0.9756
   6.750   1.1060   0.00964   0.00548  -0.0793   0.5697   0.9784
   7.000   1.1009   0.01153   0.00669  -0.0752   0.4455   0.9866
   7.250   1.0753   0.01409   0.00896  -0.0693   0.3843   1.0000
   7.500   1.0532   0.01741   0.01195  -0.0654   0.3219   1.0000
   7.750   1.0247   0.02114   0.01517  -0.0607   0.2334   1.0000
   8.000   1.0001   0.02463   0.01812  -0.0564   0.1365   1.0000
   8.250   0.9760   0.02818   0.02106  -0.0521   0.0365   1.0000
   8.500   0.9842   0.02962   0.02247  -0.0507   0.0258   1.0000
   8.750   0.9947   0.03092   0.02378  -0.0497   0.0217   1.0000
   9.000   1.0009   0.03261   0.02555  -0.0482   0.0190   1.0000
   9.250   1.0139   0.03382   0.02679  -0.0474   0.0168   1.0000
   9.500   1.0250   0.03517   0.02819  -0.0465   0.0161   1.0000
   9.750   1.0351   0.03664   0.02971  -0.0456   0.0158   1.0000
  10.000   1.0385   0.03865   0.03176  -0.0441   0.0147   1.0000
  10.250   1.0422   0.04066   0.03385  -0.0426   0.0139   1.0000
  10.500   1.0478   0.04250   0.03574  -0.0412   0.0142   1.0000
  10.750   1.0578   0.04399   0.03729  -0.0402   0.0140   1.0000
  11.000   1.0691   0.04540   0.03876  -0.0393   0.0129   1.0000
  11.250   1.0788   0.04688   0.04031  -0.0381   0.0127   1.0000
  11.500   1.0897   0.04820   0.04168  -0.0370   0.0127   1.0000
  11.750   1.1029   0.04945   0.04297  -0.0364   0.0120   1.0000
  12.000   1.1154   0.05078   0.04430  -0.0359   0.0112   1.0000
  12.250   1.1301   0.05156   0.04515  -0.0339   0.0115   1.0000
  12.500   1.1434   0.05271   0.04629  -0.0332   0.0108   1.0000
  12.750   1.1751   0.05230   0.04593  -0.0308   0.0103   1.0000
  13.000   1.1880   0.05360   0.04730  -0.0304   0.0107   1.0000
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