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FX 84-W-140 (fx84w140-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-140 (fx84w140-il)
Reynolds number: 200,000
Max Cl/Cd: 79.68 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w140-il-200000-n5.txt
Download as CSV file: xf-fx84w140-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-140                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2563   0.08836   0.08452  -0.0815   0.9134   0.0230
 -10.750  -0.2684   0.08148   0.07764  -0.0852   0.9034   0.0231
 -10.500  -0.4320   0.04574   0.04159  -0.1097   0.8818   0.0219
 -10.250  -0.4720   0.04076   0.03625  -0.1089   0.8683   0.0218
 -10.000  -0.4884   0.03712   0.03223  -0.1073   0.8589   0.0220
  -9.750  -0.4929   0.03404   0.02872  -0.1058   0.8520   0.0225
  -9.500  -0.4896   0.03127   0.02552  -0.1045   0.8451   0.0230
  -9.250  -0.4810   0.02881   0.02258  -0.1032   0.8389   0.0238
  -9.000  -0.4658   0.02726   0.02075  -0.1022   0.8341   0.0245
  -8.750  -0.4454   0.02651   0.01994  -0.1018   0.8281   0.0253
  -8.500  -0.4252   0.02564   0.01892  -0.1012   0.8229   0.0263
  -8.000  -0.3841   0.02325   0.01598  -0.0999   0.8130   0.0286
  -7.750  -0.3623   0.02217   0.01473  -0.0994   0.8079   0.0296
  -7.500  -0.3391   0.02148   0.01395  -0.0990   0.8038   0.0307
  -7.250  -0.3152   0.02088   0.01325  -0.0987   0.7987   0.0323
  -7.000  -0.2909   0.02017   0.01235  -0.0983   0.7937   0.0343
  -6.750  -0.2670   0.01941   0.01149  -0.0979   0.7893   0.0358
  -6.500  -0.2423   0.01885   0.01086  -0.0976   0.7852   0.0375
  -6.250  -0.2172   0.01833   0.01027  -0.0973   0.7800   0.0397
  -6.000  -0.1920   0.01779   0.00959  -0.0970   0.7754   0.0422
  -5.750  -0.1668   0.01730   0.00906  -0.0967   0.7716   0.0447
  -5.500  -0.1413   0.01688   0.00859  -0.0965   0.7665   0.0477
  -5.250  -0.1157   0.01644   0.00807  -0.0962   0.7617   0.0510
  -5.000  -0.0899   0.01604   0.00764  -0.0960   0.7577   0.0546
  -4.750  -0.0636   0.01571   0.00721  -0.0958   0.7535   0.0588
  -4.500  -0.0380   0.01532   0.00685  -0.0957   0.7483   0.0637
  -4.250  -0.0116   0.01502   0.00649  -0.0955   0.7438   0.0693
  -4.000   0.0148   0.01468   0.00612  -0.0953   0.7401   0.0762
  -3.750   0.0412   0.01444   0.00585  -0.0952   0.7349   0.0843
  -3.500   0.0677   0.01417   0.00559  -0.0951   0.7299   0.0946
  -3.250   0.0945   0.01390   0.00532  -0.0950   0.7258   0.1077
  -3.000   0.1212   0.01367   0.00511  -0.0949   0.7213   0.1243
  -2.750   0.1476   0.01344   0.00495  -0.0949   0.7161   0.1458
  -2.500   0.1743   0.01319   0.00476  -0.0948   0.7116   0.1755
  -2.250   0.2011   0.01291   0.00457  -0.0948   0.7079   0.2157
  -1.750   0.2522   0.01220   0.00438  -0.0946   0.6978   0.3601
  -1.500   0.2767   0.01169   0.00429  -0.0942   0.6938   0.4873
  -1.250   0.3000   0.01135   0.00438  -0.0933   0.6891   0.6083
  -1.000   0.3241   0.01123   0.00447  -0.0923   0.6841   0.6858
  -0.750   0.3492   0.01119   0.00451  -0.0915   0.6797   0.7355
  -0.500   0.3745   0.01120   0.00453  -0.0906   0.6755   0.7716
  -0.250   0.3992   0.01124   0.00461  -0.0898   0.6702   0.8004
   0.000   0.4239   0.01127   0.00464  -0.0889   0.6655   0.8244
   0.250   0.4491   0.01130   0.00462  -0.0880   0.6617   0.8469
   0.500   0.4722   0.01136   0.00471  -0.0869   0.6561   0.8686
   0.750   0.4939   0.01140   0.00477  -0.0852   0.6512   0.8964
   1.000   0.5184   0.01141   0.00475  -0.0839   0.6470   0.9208
   1.250   0.5466   0.01146   0.00478  -0.0839   0.6417   0.9356
   1.500   0.5770   0.01150   0.00480  -0.0845   0.6364   0.9466
   1.750   0.6098   0.01153   0.00477  -0.0856   0.6319   0.9567
   2.000   0.6447   0.01160   0.00481  -0.0873   0.6265   0.9652
   2.250   0.6794   0.01166   0.00486  -0.0889   0.6210   0.9741
   2.500   0.7152   0.01172   0.00487  -0.0908   0.6164   0.9826
   2.750   0.7517   0.01181   0.00495  -0.0929   0.6110   0.9910
   3.000   0.7849   0.01190   0.00504  -0.0944   0.6053   1.0000
   3.250   0.8064   0.01201   0.00510  -0.0934   0.6007   1.0000
   3.500   0.8283   0.01215   0.00524  -0.0925   0.5952   1.0000
   3.750   0.8518   0.01229   0.00538  -0.0919   0.5895   1.0000
   4.000   0.8773   0.01241   0.00546  -0.0917   0.5846   1.0000
   4.250   0.9013   0.01258   0.00567  -0.0912   0.5783   1.0000
   4.500   0.9265   0.01273   0.00581  -0.0909   0.5723   1.0000
   4.750   0.9521   0.01288   0.00597  -0.0907   0.5666   1.0000
   5.000   0.9765   0.01306   0.00619  -0.0903   0.5599   1.0000
   5.250   1.0024   0.01322   0.00632  -0.0901   0.5541   1.0000
   5.500   1.0266   0.01342   0.00659  -0.0897   0.5475   1.0000
   5.750   1.0515   0.01361   0.00680  -0.0894   0.5411   1.0000
   6.000   1.0759   0.01381   0.00702  -0.0889   0.5341   1.0000
   6.250   1.0995   0.01401   0.00725  -0.0884   0.5256   1.0000
   6.500   1.1229   0.01423   0.00751  -0.0878   0.5176   1.0000
   6.750   1.1463   0.01445   0.00777  -0.0872   0.5098   1.0000
   7.000   1.1689   0.01470   0.00807  -0.0865   0.5017   1.0000
   7.250   1.1912   0.01495   0.00835  -0.0857   0.4929   1.0000
   7.500   1.2101   0.01522   0.00865  -0.0844   0.4797   1.0000
   7.750   1.2256   0.01554   0.00892  -0.0824   0.4613   1.0000
   8.000   1.2384   0.01594   0.00929  -0.0801   0.4404   1.0000
   8.250   1.2490   0.01638   0.00970  -0.0774   0.4213   1.0000
   8.500   1.2580   0.01691   0.01019  -0.0746   0.4027   1.0000
   8.750   1.2655   0.01757   0.01079  -0.0717   0.3820   1.0000
   9.000   1.2718   0.01835   0.01151  -0.0688   0.3595   1.0000
   9.250   1.2762   0.01930   0.01238  -0.0659   0.3362   1.0000
   9.500   1.2787   0.02044   0.01343  -0.0630   0.3102   1.0000
   9.750   1.2796   0.02177   0.01465  -0.0602   0.2831   1.0000
  10.000   1.2784   0.02335   0.01611  -0.0574   0.2549   1.0000
  10.250   1.2760   0.02513   0.01775  -0.0547   0.2260   1.0000
  10.500   1.2732   0.02707   0.01956  -0.0522   0.1989   1.0000
  10.750   1.2700   0.02917   0.02152  -0.0500   0.1719   1.0000
  11.000   1.2665   0.03140   0.02363  -0.0479   0.1454   1.0000
  11.250   1.2637   0.03370   0.02580  -0.0461   0.1220   1.0000
  11.500   1.2618   0.03601   0.02803  -0.0445   0.1017   1.0000
  11.750   1.2619   0.03826   0.03024  -0.0432   0.0873   1.0000
  12.000   1.2627   0.04055   0.03250  -0.0421   0.0755   1.0000
  12.250   1.2647   0.04279   0.03474  -0.0411   0.0667   1.0000
  12.500   1.2664   0.04515   0.03711  -0.0403   0.0598   1.0000
  12.750   1.2698   0.04741   0.03942  -0.0396   0.0542   1.0000
  13.000   1.2717   0.04990   0.04194  -0.0390   0.0498   1.0000
  13.250   1.2756   0.05224   0.04436  -0.0386   0.0462   1.0000
  13.500   1.2769   0.05493   0.04708  -0.0382   0.0431   1.0000
  13.750   1.2794   0.05755   0.04979  -0.0379   0.0407   1.0000
  14.000   1.2828   0.06012   0.05245  -0.0378   0.0384   1.0000
  14.250   1.2846   0.06293   0.05532  -0.0377   0.0365   1.0000
  14.500   1.2835   0.06617   0.05860  -0.0377   0.0348   1.0000
  14.750   1.2874   0.06885   0.06140  -0.0378   0.0332   1.0000
  15.000   1.2902   0.07170   0.06437  -0.0380   0.0318   1.0000
  15.250   1.2920   0.07472   0.06748  -0.0382   0.0305   1.0000
  15.500   1.2923   0.07802   0.07084  -0.0387   0.0294   1.0000
  15.750   1.2915   0.08147   0.07435  -0.0391   0.0285   1.0000
  16.000   1.2948   0.08443   0.07743  -0.0396   0.0275   1.0000
  16.250   1.2974   0.08752   0.08063  -0.0401   0.0264   1.0000
  16.500   1.2994   0.09073   0.08394  -0.0408   0.0254   1.0000
  16.750   1.3010   0.09404   0.08734  -0.0415   0.0246   1.0000
  17.000   1.3015   0.09752   0.09089  -0.0424   0.0239   1.0000
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