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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 50,000
Max Cl/Cd: 18.04 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w121-il-50000-n5.txt
Download as CSV file: xf-fx77w121-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-121                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3096   0.11476   0.10844  -0.0191   0.7287   0.0993
  -9.250  -0.3163   0.11320   0.10688  -0.0229   0.7182   0.1007
  -9.000  -0.3217   0.11110   0.10479  -0.0267   0.7089   0.1011
  -8.750  -0.2945   0.10492   0.09847  -0.0237   0.6978   0.1038
  -8.500  -0.2846   0.10156   0.09505  -0.0242   0.6895   0.1065
  -8.250  -0.2812   0.09873   0.09221  -0.0259   0.6823   0.1117
  -8.000  -0.2922   0.09682   0.09037  -0.0305   0.6764   0.1151
  -7.750  -0.2821   0.09265   0.08618  -0.0304   0.6703   0.1184
  -7.500  -0.2714   0.08959   0.08309  -0.0303   0.6637   0.1253
  -7.000  -0.2720   0.08367   0.07721  -0.0339   0.6538   0.1348
  -6.750  -0.2638   0.08063   0.07412  -0.0349   0.6485   0.1382
  -6.500  -0.2574   0.07235   0.06557  -0.0431   0.6460   0.0683
  -6.000  -0.2411   0.06348   0.05625  -0.0472   0.6384   0.0564
  -5.750  -0.2290   0.06011   0.05277  -0.0474   0.6341   0.0552
  -5.500  -0.2167   0.05667   0.04912  -0.0475   0.6306   0.0541
  -5.250  -0.2031   0.05334   0.04547  -0.0474   0.6276   0.0532
  -5.000  -0.1879   0.05021   0.04206  -0.0473   0.6237   0.0526
  -4.750  -0.1716   0.04737   0.03887  -0.0468   0.6201   0.0532
  -4.500  -0.1542   0.04468   0.03571  -0.0459   0.6168   0.0548
  -4.250  -0.1356   0.04221   0.03265  -0.0447   0.6139   0.0562
  -4.000  -0.1152   0.03992   0.02988  -0.0436   0.6103   0.0567
  -3.750  -0.0933   0.03793   0.02744  -0.0426   0.6065   0.0572
  -3.500  -0.0704   0.03592   0.02510  -0.0419   0.6032   0.0589
  -3.250  -0.0466   0.03459   0.02357  -0.0414   0.6003   0.0635
  -3.000  -0.0204   0.03324   0.02180  -0.0408   0.5979   0.0674
  -2.750   0.0080   0.03199   0.02019  -0.0407   0.5944   0.0701
  -2.500   0.0365   0.03092   0.01898  -0.0408   0.5910   0.0753
  -2.250   0.0673   0.03012   0.01795  -0.0412   0.5879   0.0837
  -2.000   0.1016   0.02920   0.01680  -0.0421   0.5851   0.0905
  -1.750   0.1311   0.02865   0.01612  -0.0424   0.5826   0.1051
  -1.500   0.1576   0.02829   0.01575  -0.0425   0.5794   0.1211
  -1.250   0.2850   0.02444   0.01460  -0.0616   0.5753   1.0000
  -1.000   0.3085   0.02482   0.01459  -0.0610   0.5726   1.0000
  -0.750   0.3318   0.02517   0.01460  -0.0603   0.5702   1.0000
  -0.500   0.3552   0.02560   0.01471  -0.0597   0.5678   1.0000
  -0.250   0.3776   0.02627   0.01523  -0.0595   0.5646   1.0000
   0.000   0.4000   0.02690   0.01569  -0.0592   0.5618   1.0000
   0.250   0.4225   0.02748   0.01607  -0.0587   0.5591   1.0000
   0.500   0.4452   0.02799   0.01639  -0.0581   0.5565   1.0000
   0.750   0.4682   0.02846   0.01668  -0.0574   0.5543   1.0000
   1.000   0.4890   0.02931   0.01745  -0.0571   0.5513   1.0000
   1.250   0.5088   0.03030   0.01839  -0.0568   0.5481   1.0000
   1.500   0.5291   0.03113   0.01914  -0.0563   0.5449   1.0000
   1.750   0.5504   0.03183   0.01974  -0.0557   0.5422   1.0000
   2.000   0.5727   0.03240   0.02020  -0.0549   0.5399   1.0000
   2.250   0.5914   0.03343   0.02120  -0.0544   0.5368   1.0000
   2.500   0.6060   0.03489   0.02269  -0.0540   0.5325   1.0000
   2.750   0.6241   0.03588   0.02365  -0.0533   0.5288   1.0000
   3.000   0.6451   0.03656   0.02427  -0.0525   0.5260   1.0000
   3.250   0.6683   0.03704   0.02469  -0.0516   0.5238   1.0000
   3.500   0.6713   0.03953   0.02730  -0.0511   0.5174   1.0000
   3.750   0.6875   0.04067   0.02843  -0.0502   0.5135   1.0000
   4.000   0.7080   0.04140   0.02914  -0.0493   0.5107   1.0000
   4.250   0.7168   0.04321   0.03098  -0.0484   0.5058   1.0000
   4.500   0.7215   0.04530   0.03315  -0.0474   0.4997   1.0000
   4.750   0.7412   0.04610   0.03394  -0.0465   0.4964   1.0000
   5.000   0.7662   0.04646   0.03429  -0.0456   0.4941   1.0000
   5.250   0.7483   0.05037   0.03829  -0.0443   0.4842   1.0000
   5.500   0.7705   0.05093   0.03886  -0.0434   0.4809   1.0000
   6.000   0.7741   0.05537   0.04337  -0.0412   0.4674   1.0000
   6.250   0.8011   0.05557   0.04364  -0.0402   0.4648   1.0000
   6.750   0.7982   0.06028   0.04842  -0.0377   0.4507   1.0000
   7.250   0.8011   0.06457   0.05278  -0.0356   0.4367   1.0000
   7.750   0.8089   0.06867   0.05698  -0.0340   0.4227   1.0000
   8.250   0.8185   0.07278   0.06125  -0.0326   0.4086   1.0000
   8.500   0.8454   0.07295   0.06153  -0.0317   0.4055   1.0000
   8.750   0.8294   0.07687   0.06549  -0.0316   0.3948   1.0000
   9.000   0.8542   0.07722   0.06599  -0.0307   0.3913   1.0000
   9.250   0.8410   0.08108   0.06990  -0.0307   0.3811   1.0000
   9.500   0.8636   0.08165   0.07059  -0.0299   0.3776   1.0000
   9.750   0.8526   0.08544   0.07444  -0.0301   0.3679   1.0000
  10.000   0.8753   0.08591   0.07505  -0.0293   0.3641   1.0000
  10.250   0.8644   0.08988   0.07909  -0.0297   0.3548   1.0000
  10.500   0.8858   0.09048   0.07983  -0.0289   0.3508   1.0000
  10.750   0.8762   0.09445   0.08387  -0.0294   0.3416   1.0000
  11.000   0.8957   0.09523   0.08481  -0.0286   0.3373   1.0000
  11.250   0.8876   0.09920   0.08890  -0.0292   0.3287   1.0000
  11.500   0.9050   0.10014   0.09001  -0.0286   0.3238   1.0000
  11.750   0.8996   0.10393   0.09388  -0.0291   0.3157   1.0000
  12.000   0.9136   0.10530   0.09542  -0.0287   0.3104   1.0000
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