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FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il)
Reynolds number: 200,000
Max Cl/Cd: 70.31 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66s171-il-200000.txt
Download as CSV file: xf-fx66s171-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-171 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3828   0.05460   0.05065  -0.1083   0.8547   0.0383
 -10.250  -0.3926   0.05013   0.04589  -0.1108   0.8226   0.0371
 -10.000  -0.4120   0.04684   0.04230  -0.1101   0.8004   0.0361
  -9.750  -0.4366   0.04261   0.03761  -0.1081   0.7846   0.0340
  -9.500  -0.4581   0.03888   0.03294  -0.1048   0.7722   0.0314
  -9.250  -0.4495   0.03667   0.03037  -0.1036   0.7602   0.0313
  -9.000  -0.4386   0.03416   0.02752  -0.1024   0.7497   0.0313
  -8.500  -0.4083   0.02888   0.02176  -0.1009   0.7316   0.0329
  -8.250  -0.3881   0.02783   0.02057  -0.1004   0.7237   0.0345
  -8.000  -0.3675   0.02651   0.01905  -0.0996   0.7155   0.0361
  -7.750  -0.3455   0.02511   0.01737  -0.0989   0.7092   0.0372
  -7.500  -0.3228   0.02399   0.01604  -0.0981   0.7018   0.0387
  -7.250  -0.3012   0.02230   0.01425  -0.0973   0.6961   0.0409
  -7.000  -0.2792   0.02148   0.01344  -0.0968   0.6900   0.0441
  -6.750  -0.2558   0.02090   0.01272  -0.0962   0.6841   0.0484
  -6.500  -0.2356   0.01975   0.01156  -0.0953   0.6796   0.0528
  -6.250  -0.2126   0.01921   0.01097  -0.0948   0.6739   0.0590
  -6.000  -0.1921   0.01829   0.01006  -0.0940   0.6687   0.0664
  -5.750  -0.1699   0.01756   0.00928  -0.0935   0.6645   0.0777
  -5.500  -0.1479   0.01680   0.00857  -0.0930   0.6599   0.0983
  -5.250  -0.1294   0.01539   0.00765  -0.0925   0.6555   0.1814
  -5.000  -0.1107   0.01429   0.00733  -0.0919   0.6517   0.3667
  -4.750  -0.0840   0.01446   0.00751  -0.0916   0.6484   0.4242
  -4.500  -0.0573   0.01470   0.00772  -0.0913   0.6440   0.4537
  -4.250  -0.0301   0.01499   0.00788  -0.0910   0.6398   0.4767
  -4.000  -0.0026   0.01525   0.00805  -0.0907   0.6361   0.4937
  -3.750   0.0253   0.01551   0.00817  -0.0906   0.6332   0.5083
  -3.500   0.0520   0.01573   0.00835  -0.0903   0.6293   0.5221
  -3.250   0.0788   0.01594   0.00857  -0.0899   0.6255   0.5345
  -3.000   0.1060   0.01611   0.00872  -0.0896   0.6221   0.5462
  -2.750   0.1338   0.01626   0.00878  -0.0894   0.6194   0.5574
  -2.500   0.1618   0.01644   0.00881  -0.0895   0.6168   0.5683
  -2.250   0.1880   0.01649   0.00895  -0.0892   0.6133   0.5752
  -2.000   0.2156   0.01653   0.00888  -0.0893   0.6098   0.5830
  -1.750   0.2433   0.01651   0.00884  -0.0893   0.6068   0.5880
  -1.500   0.2716   0.01655   0.00880  -0.0895   0.6044   0.5940
  -1.250   0.3006   0.01664   0.00873  -0.0899   0.6022   0.6001
  -1.000   0.3268   0.01670   0.00887  -0.0898   0.5993   0.6047
  -0.750   0.3539   0.01679   0.00895  -0.0899   0.5962   0.6104
  -0.500   0.3817   0.01685   0.00895  -0.0901   0.5933   0.6160
  -0.250   0.4095   0.01689   0.00898  -0.0902   0.5906   0.6211
   0.000   0.4381   0.01698   0.00897  -0.0905   0.5883   0.6275
   0.250   0.4659   0.01712   0.00909  -0.0907   0.5860   0.6327
   0.500   0.4915   0.01727   0.00933  -0.0905   0.5830   0.6379
   0.750   0.5184   0.01741   0.00945  -0.0907   0.5797   0.6439
   1.000   0.5460   0.01743   0.00948  -0.0907   0.5764   0.6490
   1.250   0.5746   0.01746   0.00947  -0.0909   0.5737   0.6549
   1.500   0.6033   0.01762   0.00956  -0.0913   0.5713   0.6619
   1.750   0.6271   0.01781   0.00991  -0.0908   0.5678   0.6685
   2.250   0.6798   0.01815   0.01035  -0.0908   0.5620   0.6829
   2.500   0.7079   0.01827   0.01046  -0.0910   0.5596   0.6909
   2.750   0.7363   0.01836   0.01056  -0.0912   0.5574   0.6981
   3.000   0.7619   0.01863   0.01089  -0.0912   0.5545   0.7070
   3.250   0.7850   0.01888   0.01130  -0.0907   0.5507   0.7152
   3.500   0.8107   0.01906   0.01156  -0.0905   0.5477   0.7258
   3.750   0.8377   0.01919   0.01175  -0.0905   0.5451   0.7381
   4.000   0.8654   0.01927   0.01190  -0.0906   0.5430   0.7513
   4.250   0.8930   0.01945   0.01213  -0.0907   0.5409   0.7668
   4.500   0.9112   0.01987   0.01281  -0.0895   0.5367   0.7857
   4.750   0.9334   0.02002   0.01315  -0.0886   0.5332   0.8110
   5.000   0.9574   0.01998   0.01328  -0.0878   0.5303   0.8536
   5.250   0.9989   0.01986   0.01332  -0.0905   0.5280   1.0000
   5.500   1.0283   0.02022   0.01365  -0.0914   0.5254   1.0000
   5.750   1.0471   0.02087   0.01442  -0.0905   0.5205   1.0000
   6.000   1.0728   0.02116   0.01474  -0.0906   0.5170   1.0000
   6.250   1.1017   0.02131   0.01489  -0.0910   0.5143   1.0000
   6.500   1.1329   0.02143   0.01497  -0.0917   0.5120   1.0000
   6.750   1.1501   0.02217   0.01587  -0.0905   0.5076   1.0000
   7.000   1.1708   0.02272   0.01652  -0.0898   0.5035   1.0000
   7.250   1.1971   0.02296   0.01682  -0.0898   0.5003   1.0000
   7.500   1.2279   0.02302   0.01688  -0.0904   0.4978   1.0000
   7.750   1.2538   0.02341   0.01732  -0.0904   0.4948   1.0000
   8.000   1.2646   0.02436   0.01850  -0.0883   0.4894   1.0000
   8.250   1.2889   0.02466   0.01888  -0.0880   0.4858   1.0000
   8.500   1.3208   0.02459   0.01883  -0.0887   0.4830   1.0000
   8.750   1.3476   0.02479   0.01909  -0.0887   0.4795   1.0000
   9.000   1.3565   0.02564   0.02015  -0.0863   0.4734   1.0000
   9.250   1.3974   0.02439   0.01886  -0.0876   0.4680   1.0000
   9.500   1.4210   0.02297   0.01744  -0.0861   0.4556   1.0000
   9.750   1.4416   0.02171   0.01616  -0.0842   0.4419   1.0000
  10.000   1.4580   0.02129   0.01580  -0.0821   0.4311   1.0000
  10.250   1.4766   0.02100   0.01554  -0.0804   0.4214   1.0000
  10.500   1.4814   0.02126   0.01596  -0.0769   0.4104   1.0000
  10.750   1.4841   0.02154   0.01634  -0.0730   0.3990   1.0000
  11.000   1.4865   0.02196   0.01680  -0.0693   0.3861   1.0000
  11.250   1.4845   0.02269   0.01755  -0.0655   0.3702   1.0000
  11.500   1.4787   0.02388   0.01873  -0.0618   0.3520   1.0000
  11.750   1.4681   0.02568   0.02050  -0.0584   0.3303   1.0000
  12.000   1.4519   0.02822   0.02293  -0.0552   0.3072   1.0000
  12.250   1.4323   0.03151   0.02615  -0.0528   0.2786   1.0000
  12.500   1.4076   0.03559   0.03008  -0.0506   0.2495   1.0000
  12.750   1.3804   0.04021   0.03455  -0.0490   0.2191   1.0000
  13.000   1.3534   0.04509   0.03928  -0.0477   0.1934   1.0000
  13.250   1.3263   0.05028   0.04433  -0.0469   0.1656   1.0000
  13.500   1.2990   0.05585   0.04972  -0.0464   0.1376   1.0000
  13.750   1.2736   0.06150   0.05518  -0.0463   0.1086   1.0000
  14.000   1.2492   0.06729   0.06076  -0.0465   0.0812   1.0000
  14.250   1.2294   0.07278   0.06610  -0.0469   0.0631   1.0000
  14.500   1.2140   0.07793   0.07117  -0.0473   0.0510   1.0000
  14.750   1.2017   0.08281   0.07602  -0.0479   0.0443   1.0000
  15.000   1.1968   0.08684   0.08012  -0.0485   0.0398   1.0000
  15.250   1.1904   0.09112   0.08442  -0.0492   0.0365   1.0000
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