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GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 200,000
Max Cl/Cd: 75.19 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe407-il-200000-n5.txt
Download as CSV file: xf-goe407-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 407 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3175   0.10387   0.10031  -0.0308   1.0000   0.0328
  -8.750  -0.3260   0.10169   0.09819  -0.0315   1.0000   0.0330
  -8.500  -0.3298   0.09898   0.09552  -0.0336   0.9989   0.0332
  -8.250  -0.3170   0.09429   0.09085  -0.0387   0.9947   0.0335
  -8.000  -0.2969   0.09073   0.08728  -0.0386   0.9925   0.0340
  -7.750  -0.2801   0.08748   0.08403  -0.0412   0.9882   0.0350
  -7.500  -0.2650   0.08393   0.08048  -0.0456   0.9828   0.0358
  -7.250  -0.2510   0.08029   0.07684  -0.0500   0.9749   0.0368
  -7.000  -0.2341   0.07607   0.07259  -0.0561   0.9650   0.0386
  -6.750  -0.2129   0.07045   0.06682  -0.0682   0.9509   0.0398
  -6.250  -0.1278   0.04995   0.04657  -0.0693   0.9039   0.0427
  -6.000  -0.1098   0.04593   0.04247  -0.0731   0.8910   0.0442
  -5.750  -0.1512   0.05805   0.05434  -0.0721   0.9049   0.0432
  -5.500  -0.1275   0.05455   0.05072  -0.0754   0.8917   0.0451
  -5.250  -0.0904   0.04912   0.04476  -0.0828   0.8780   0.0476
  -5.000  -0.0627   0.04560   0.04125  -0.0854   0.8694   0.0482
  -4.750  -0.0307   0.04315   0.03874  -0.0883   0.8593   0.0495
  -4.500   0.0037   0.04058   0.03599  -0.0916   0.8478   0.0527
  -4.250   0.0321   0.03320   0.02783  -0.0931   0.8353   0.0403
  -4.000   0.0617   0.03136   0.02586  -0.0946   0.8241   0.0387
  -3.750   0.0873   0.02901   0.02322  -0.0949   0.8122   0.0377
  -3.500   0.1098   0.02672   0.02060  -0.0941   0.8003   0.0370
  -3.250   0.1326   0.02471   0.01825  -0.0931   0.7896   0.0374
  -3.000   0.1554   0.02290   0.01607  -0.0920   0.7786   0.0377
  -2.750   0.1764   0.02129   0.01412  -0.0904   0.7655   0.0372
  -2.500   0.1983   0.01985   0.01234  -0.0889   0.7520   0.0369
  -2.250   0.2211   0.01863   0.01079  -0.0876   0.7390   0.0367
  -2.000   0.2456   0.01761   0.00947  -0.0866   0.7283   0.0369
  -1.750   0.2698   0.01678   0.00842  -0.0856   0.7180   0.0371
  -1.500   0.2952   0.01608   0.00752  -0.0848   0.7089   0.0373
  -1.250   0.3207   0.01554   0.00682  -0.0841   0.7000   0.0381
  -1.000   0.3462   0.01512   0.00625  -0.0834   0.6914   0.0392
  -0.750   0.3719   0.01474   0.00575  -0.0827   0.6829   0.0398
  -0.500   0.3970   0.01429   0.00525  -0.0820   0.6745   0.0401
  -0.250   0.4218   0.01391   0.00482  -0.0813   0.6662   0.0407
   0.000   0.4460   0.01363   0.00453  -0.0804   0.6580   0.0413
   0.250   0.4703   0.01341   0.00429  -0.0795   0.6500   0.0423
   0.500   0.4941   0.01324   0.00411  -0.0785   0.6414   0.0433
   0.750   0.5183   0.01313   0.00395  -0.0776   0.6330   0.0445
   1.000   0.5420   0.01303   0.00383  -0.0766   0.6242   0.0461
   1.250   0.5661   0.01298   0.00375  -0.0757   0.6159   0.0497
   1.500   0.5897   0.01292   0.00372  -0.0747   0.6068   0.0545
   1.750   0.6135   0.01289   0.00367  -0.0737   0.5981   0.0623
   2.000   0.6363   0.01282   0.00365  -0.0725   0.5878   0.0845
   2.250   0.6578   0.01254   0.00372  -0.0713   0.5781   0.2146
   2.750   0.8499   0.01159   0.00424  -0.1020   0.5392   1.0000
   3.000   0.8716   0.01173   0.00432  -0.1006   0.5227   1.0000
   3.250   0.8921   0.01191   0.00439  -0.0990   0.5023   1.0000
   3.500   0.9120   0.01213   0.00448  -0.0973   0.4792   1.0000
   3.750   0.9302   0.01242   0.00461  -0.0953   0.4551   1.0000
   4.000   0.9490   0.01272   0.00478  -0.0935   0.4340   1.0000
   4.250   0.9683   0.01303   0.00498  -0.0917   0.4176   1.0000
   4.500   0.9880   0.01333   0.00521  -0.0901   0.4044   1.0000
   4.750   1.0077   0.01364   0.00546  -0.0885   0.3927   1.0000
   5.000   1.0280   0.01392   0.00571  -0.0870   0.3813   1.0000
   5.250   1.0477   0.01424   0.00598  -0.0854   0.3704   1.0000
   5.750   1.0868   0.01486   0.00656  -0.0822   0.3497   1.0000
   6.000   1.1058   0.01518   0.00686  -0.0806   0.3404   1.0000
   6.250   1.1251   0.01549   0.00717  -0.0790   0.3316   1.0000
   6.500   1.1443   0.01581   0.00751  -0.0773   0.3241   1.0000
   6.750   1.1629   0.01614   0.00784  -0.0756   0.3153   1.0000
   7.000   1.1815   0.01647   0.00819  -0.0739   0.3078   1.0000
   7.250   1.1995   0.01680   0.00857  -0.0721   0.2997   1.0000
   7.500   1.2169   0.01715   0.00894  -0.0702   0.2908   1.0000
   7.750   1.2328   0.01754   0.00933  -0.0681   0.2813   1.0000
   8.000   1.2498   0.01788   0.00972  -0.0661   0.2720   1.0000
   8.250   1.2643   0.01829   0.01014  -0.0637   0.2631   1.0000
   8.500   1.2782   0.01865   0.01057  -0.0612   0.2528   1.0000
   8.750   1.2903   0.01905   0.01099  -0.0584   0.2414   1.0000
   9.000   1.3004   0.01953   0.01146  -0.0553   0.2264   1.0000
   9.250   1.3093   0.02008   0.01198  -0.0521   0.2078   1.0000
   9.500   1.3163   0.02077   0.01261  -0.0487   0.1841   1.0000
   9.750   1.3195   0.02171   0.01339  -0.0450   0.1533   1.0000
  10.000   1.3234   0.02271   0.01428  -0.0415   0.1364   1.0000
  10.250   1.3280   0.02374   0.01526  -0.0383   0.1253   1.0000
  10.500   1.3330   0.02478   0.01630  -0.0353   0.1173   1.0000
  10.750   1.3402   0.02575   0.01732  -0.0327   0.1110   1.0000
  11.000   1.3443   0.02695   0.01855  -0.0300   0.1054   1.0000
  11.250   1.3532   0.02790   0.01961  -0.0279   0.1011   1.0000
  11.500   1.3605   0.02900   0.02079  -0.0258   0.0956   1.0000
  11.750   1.3639   0.03043   0.02225  -0.0235   0.0906   1.0000
  12.000   1.3736   0.03149   0.02341  -0.0220   0.0841   1.0000
  12.250   1.3778   0.03300   0.02497  -0.0202   0.0778   1.0000
  12.500   1.3841   0.03442   0.02644  -0.0187   0.0685   1.0000
  12.750   1.3881   0.03608   0.02816  -0.0172   0.0610   1.0000
  13.000   1.3872   0.03825   0.03029  -0.0156   0.0486   1.0000
  13.250   1.3840   0.04074   0.03276  -0.0142   0.0388   1.0000
  13.500   1.3806   0.04335   0.03539  -0.0131   0.0321   1.0000
  13.750   1.3750   0.04630   0.03837  -0.0121   0.0274   1.0000
  14.000   1.3705   0.04926   0.04139  -0.0113   0.0249   1.0000
  14.250   1.3660   0.05233   0.04456  -0.0107   0.0232   1.0000
  14.500   1.3594   0.05574   0.04806  -0.0104   0.0219   1.0000
  14.750   1.3542   0.05911   0.05155  -0.0102   0.0208   1.0000
  15.000   1.3486   0.06264   0.05521  -0.0102   0.0200   1.0000
  15.250   1.3427   0.06630   0.05901  -0.0104   0.0193   1.0000
  15.500   1.3347   0.07040   0.06322  -0.0109   0.0187   1.0000
  15.750   1.3260   0.07474   0.06769  -0.0117   0.0183   1.0000
  16.000   1.3165   0.07933   0.07242  -0.0127   0.0179   1.0000
  16.250   1.3037   0.08459   0.07780  -0.0140   0.0175   1.0000
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