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USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: USA 27 AIRFOIL (usa27-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.12 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa27-il-1000000-n5.txt
Download as CSV file: xf-usa27-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 27 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2642   0.09868   0.09696  -0.0581   0.9897   0.0107
 -10.250  -0.2544   0.09517   0.09345  -0.0609   0.9880   0.0110
  -9.750  -0.2527   0.08261   0.08089  -0.0706   0.9833   0.0127
  -9.500  -0.2417   0.07988   0.07816  -0.0731   0.9786   0.0128
  -9.250  -0.2284   0.07687   0.07516  -0.0765   0.9750   0.0130
  -9.000  -0.2187   0.07398   0.07227  -0.0791   0.9685   0.0132
  -8.750  -0.2089   0.07040   0.06867  -0.0832   0.9608   0.0134
  -8.500  -0.2046   0.06621   0.06446  -0.0880   0.9466   0.0137
  -8.250  -0.2270   0.05002   0.04807  -0.1030   0.9247   0.0157
  -8.000  -0.2128   0.04648   0.04441  -0.1055   0.9117   0.0159
  -7.750  -0.1978   0.04285   0.04064  -0.1075   0.8959   0.0160
  -7.500  -0.1834   0.03857   0.03618  -0.1093   0.8787   0.0163
  -7.250  -0.1769   0.03040   0.02759  -0.1110   0.8641   0.0169
  -7.000  -0.1681   0.02568   0.02242  -0.1102   0.8500   0.0176
  -6.750  -0.1635   0.02014   0.01612  -0.1077   0.8373   0.0188
  -6.500  -0.1448   0.01853   0.01412  -0.1063   0.8227   0.0191
  -6.250  -0.1262   0.01698   0.01230  -0.1050   0.8089   0.0194
  -6.000  -0.1034   0.01640   0.01159  -0.1042   0.7950   0.0196
  -5.750  -0.0799   0.01595   0.01103  -0.1035   0.7809   0.0198
  -5.500  -0.0567   0.01551   0.01046  -0.1026   0.7632   0.0200
  -5.250  -0.0346   0.01501   0.00976  -0.1015   0.7364   0.0202
  -5.000  -0.0138   0.01462   0.00914  -0.1001   0.6990   0.0204
  -4.750   0.0075   0.01423   0.00853  -0.0988   0.6674   0.0206
  -4.500   0.0302   0.01379   0.00791  -0.0978   0.6465   0.0207
  -4.250   0.0539   0.01335   0.00731  -0.0969   0.6310   0.0209
  -4.000   0.0781   0.01291   0.00674  -0.0962   0.6188   0.0211
  -3.500   0.1281   0.01207   0.00568  -0.0949   0.6005   0.0215
  -3.000   0.1791   0.01139   0.00485  -0.0939   0.5848   0.0220
  -2.500   0.2302   0.01084   0.00415  -0.0928   0.5668   0.0224
  -2.250   0.2555   0.01061   0.00386  -0.0923   0.5568   0.0227
  -2.000   0.2808   0.01042   0.00360  -0.0917   0.5455   0.0229
  -1.750   0.3064   0.01026   0.00339  -0.0912   0.5340   0.0231
  -1.500   0.3318   0.01016   0.00323  -0.0906   0.5205   0.0233
  -1.250   0.3567   0.01009   0.00309  -0.0900   0.5031   0.0234
  -1.000   0.3797   0.00990   0.00278  -0.0890   0.4805   0.0238
  -0.750   0.4030   0.00983   0.00261  -0.0881   0.4559   0.0241
  -0.250   0.4511   0.00983   0.00243  -0.0866   0.4189   0.0247
   0.000   0.4761   0.00981   0.00236  -0.0860   0.4061   0.0249
   0.250   0.5015   0.00979   0.00230  -0.0855   0.3969   0.0252
   0.500   0.5267   0.00979   0.00225  -0.0849   0.3885   0.0256
   0.750   0.5525   0.00977   0.00222  -0.0845   0.3816   0.0262
   1.000   0.5780   0.00978   0.00220  -0.0840   0.3742   0.0268
   1.250   0.6037   0.00978   0.00218  -0.0836   0.3684   0.0272
   1.500   0.6294   0.00980   0.00217  -0.0832   0.3614   0.0277
   1.750   0.6548   0.00985   0.00218  -0.0827   0.3540   0.0282
   2.000   0.6805   0.00989   0.00220  -0.0823   0.3468   0.0286
   2.250   0.7058   0.00994   0.00222  -0.0818   0.3402   0.0295
   2.500   0.7317   0.00997   0.00225  -0.0815   0.3355   0.0308
   2.750   0.7575   0.01003   0.00229  -0.0811   0.3303   0.0321
   3.000   0.7830   0.01010   0.00235  -0.0807   0.3253   0.0339
   3.250   0.8075   0.00998   0.00244  -0.0801   0.3217   0.1529
   3.500   0.8322   0.00988   0.00257  -0.0797   0.3180   0.2488
   3.750   0.8572   0.00987   0.00270  -0.0792   0.3136   0.3153
   4.000   0.8818   0.00991   0.00284  -0.0787   0.3084   0.3731
   4.250   0.9034   0.00876   0.00315  -0.0777   0.3050   0.9625
   4.500   0.9492   0.00898   0.00336  -0.0818   0.2997   0.9856
   4.750   1.0049   0.00928   0.00359  -0.0883   0.2910   0.9956
   5.000   1.0402   0.00949   0.00374  -0.0903   0.2800   0.9977
   5.250   1.0737   0.00975   0.00392  -0.0919   0.2654   0.9994
   5.500   1.0976   0.01002   0.00410  -0.0913   0.2490   1.0000
   5.750   1.1138   0.01036   0.00432  -0.0891   0.2248   1.0000
   6.000   1.1236   0.01101   0.00472  -0.0858   0.1834   1.0000
   6.250   1.1371   0.01146   0.00505  -0.0831   0.1639   1.0000
   6.500   1.1541   0.01174   0.00529  -0.0811   0.1551   1.0000
   6.750   1.1714   0.01201   0.00553  -0.0791   0.1478   1.0000
   7.000   1.1883   0.01231   0.00578  -0.0771   0.1387   1.0000
   7.250   1.2035   0.01267   0.00607  -0.0748   0.1254   1.0000
   7.500   1.2041   0.01362   0.00672  -0.0698   0.0793   1.0000
   7.750   1.1995   0.01499   0.00780  -0.0641   0.0184   1.0000
   8.000   1.2164   0.01537   0.00819  -0.0623   0.0155   1.0000
   8.250   1.2341   0.01573   0.00857  -0.0607   0.0138   1.0000
   8.500   1.2520   0.01610   0.00897  -0.0591   0.0128   1.0000
   8.750   1.2693   0.01651   0.00940  -0.0576   0.0118   1.0000
   9.000   1.2857   0.01699   0.00990  -0.0559   0.0109   1.0000
   9.250   1.3019   0.01748   0.01043  -0.0542   0.0102   1.0000
   9.500   1.3186   0.01795   0.01093  -0.0527   0.0098   1.0000
   9.750   1.3349   0.01846   0.01148  -0.0512   0.0094   1.0000
  10.000   1.3504   0.01901   0.01206  -0.0496   0.0089   1.0000
  10.250   1.3654   0.01961   0.01269  -0.0480   0.0084   1.0000
  10.500   1.3792   0.02030   0.01341  -0.0463   0.0079   1.0000
  10.750   1.3913   0.02109   0.01425  -0.0445   0.0075   1.0000
  11.000   1.4051   0.02181   0.01501  -0.0429   0.0073   1.0000
  11.250   1.4180   0.02260   0.01585  -0.0413   0.0071   1.0000
  11.500   1.4300   0.02346   0.01677  -0.0397   0.0068   1.0000
  11.750   1.4414   0.02439   0.01775  -0.0382   0.0066   1.0000
  12.000   1.4522   0.02540   0.01881  -0.0366   0.0064   1.0000
  12.250   1.4622   0.02649   0.01995  -0.0351   0.0062   1.0000
  12.500   1.4712   0.02769   0.02120  -0.0336   0.0060   1.0000
  12.750   1.4789   0.02903   0.02261  -0.0322   0.0058   1.0000
  13.000   1.4843   0.03061   0.02425  -0.0306   0.0056   1.0000
  13.250   1.4867   0.03252   0.02624  -0.0291   0.0054   1.0000
  13.500   1.4929   0.03417   0.02797  -0.0280   0.0053   1.0000
  13.750   1.4980   0.03600   0.02987  -0.0270   0.0052   1.0000
  14.000   1.5017   0.03803   0.03198  -0.0261   0.0051   1.0000
  14.250   1.5042   0.04029   0.03433  -0.0254   0.0049   1.0000
  14.500   1.5054   0.04281   0.03694  -0.0249   0.0048   1.0000
  14.750   1.5054   0.04558   0.03980  -0.0246   0.0047   1.0000
  15.000   1.5045   0.04854   0.04286  -0.0244   0.0047   1.0000
  15.250   1.5020   0.05179   0.04620  -0.0244   0.0046   1.0000
  15.500   1.4987   0.05521   0.04971  -0.0246   0.0045   1.0000
  15.750   1.4935   0.05892   0.05352  -0.0248   0.0044   1.0000
  16.000   1.4873   0.06281   0.05751  -0.0252   0.0044   1.0000
  16.250   1.4796   0.06701   0.06181  -0.0258   0.0043   1.0000
  16.500   1.4712   0.07141   0.06631  -0.0266   0.0043   1.0000
  16.750   1.4612   0.07609   0.07110  -0.0275   0.0042   1.0000
  17.000   1.4506   0.08094   0.07605  -0.0285   0.0042   1.0000
  17.250   1.4394   0.08599   0.08120  -0.0297   0.0041   1.0000
  17.500   1.4272   0.09124   0.08656  -0.0311   0.0041   1.0000
  17.750   1.4148   0.09653   0.09195  -0.0325   0.0041   1.0000
  18.000   1.4022   0.10193   0.09744  -0.0340   0.0040   1.0000
  18.250   1.3897   0.10737   0.10298  -0.0357   0.0040   1.0000
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