Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 83-W-227 (fx83w227-il)
Reynolds number: 200,000
Max Cl/Cd: 56.25 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx83w227-il-200000.txt
Download as CSV file: xf-fx83w227-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-227                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.7466   0.08217   0.07758  -0.0942   1.0000   0.0800
 -16.500  -0.8187   0.07281   0.06795  -0.0963   1.0000   0.0797
 -16.250  -0.8676   0.06741   0.06236  -0.0956   1.0000   0.0797
 -16.000  -0.9100   0.06351   0.05830  -0.0935   1.0000   0.0798
 -15.750  -0.9420   0.05948   0.05403  -0.0931   0.9986   0.0802
 -15.500  -0.9592   0.05471   0.04889  -0.0966   0.9938   0.0811
 -15.250  -0.9442   0.05210   0.04620  -0.0989   0.9900   0.0825
 -15.000  -0.9163   0.05084   0.04498  -0.1013   0.9862   0.0840
 -14.750  -0.8982   0.04897   0.04302  -0.1040   0.9827   0.0857
 -14.500  -0.8884   0.04691   0.04080  -0.1055   0.9769   0.0872
 -14.250  -0.8806   0.04454   0.03817  -0.1071   0.9717   0.0888
 -14.000  -0.8787   0.04252   0.03586  -0.1074   0.9648   0.0900
 -13.750  -0.8525   0.04067   0.03396  -0.1092   0.9606   0.0918
 -13.500  -0.8185   0.03958   0.03291  -0.1118   0.9579   0.0938
 -13.250  -0.7993   0.03839   0.03164  -0.1125   0.9521   0.0957
 -13.000  -0.7823   0.03705   0.03015  -0.1131   0.9459   0.0978
 -12.750  -0.7608   0.03558   0.02843  -0.1147   0.9426   0.0998
 -12.500  -0.7373   0.03425   0.02705  -0.1151   0.9364   0.1019
 -12.250  -0.7059   0.03331   0.02618  -0.1167   0.9319   0.1043
 -12.000  -0.6747   0.03223   0.02504  -0.1188   0.9289   0.1072
 -11.750  -0.6430   0.03098   0.02360  -0.1212   0.9268   0.1102
 -11.500  -0.6247   0.03001   0.02253  -0.1205   0.9190   0.1124
 -11.250  -0.5854   0.02899   0.02161  -0.1233   0.9160   0.1158
 -11.000  -0.5509   0.02803   0.02058  -0.1258   0.9130   0.1198
 -10.750  -0.5188   0.02702   0.01936  -0.1279   0.9102   0.1234
 -10.500  -0.4883   0.02611   0.01858  -0.1288   0.9038   0.1273
 -10.250  -0.4618   0.02539   0.01784  -0.1294   0.8977   0.1314
 -10.000  -0.4306   0.02455   0.01683  -0.1311   0.8937   0.1362
  -9.750  -0.4016   0.02374   0.01613  -0.1318   0.8876   0.1411
  -9.500  -0.3805   0.02317   0.01553  -0.1313   0.8800   0.1459
  -9.250  -0.3470   0.02234   0.01461  -0.1330   0.8756   0.1522
  -9.000  -0.3339   0.02192   0.01425  -0.1309   0.8667   0.1572
  -8.750  -0.3113   0.02140   0.01364  -0.1305   0.8601   0.1636
  -8.500  -0.2816   0.02065   0.01293  -0.1316   0.8553   0.1713
  -8.250  -0.2767   0.02044   0.01271  -0.1277   0.8453   0.1769
  -8.000  -0.2526   0.01984   0.01209  -0.1276   0.8396   0.1856
  -7.750  -0.2427   0.01957   0.01183  -0.1247   0.8319   0.1931
  -7.500  -0.2289   0.01918   0.01143  -0.1224   0.8244   0.2019
  -7.250  -0.2067   0.01871   0.01092  -0.1218   0.8192   0.2135
  -7.000  -0.2069   0.01856   0.01086  -0.1169   0.8105   0.2217
  -6.750  -0.1933   0.01827   0.01054  -0.1144   0.8040   0.2346
  -6.500  -0.1739   0.01785   0.01013  -0.1132   0.7993   0.2507
  -6.250  -0.1802   0.01780   0.01020  -0.1069   0.7904   0.2618
  -6.000  -0.1670   0.01744   0.00990  -0.1044   0.7846   0.2811
  -5.750  -0.1464   0.01705   0.00953  -0.1033   0.7802   0.3070
  -5.500  -0.1500   0.01701   0.00962  -0.0974   0.7720   0.3264
  -5.250  -0.1388   0.01669   0.00941  -0.0944   0.7662   0.3540
  -5.000  -0.1186   0.01633   0.00913  -0.0931   0.7620   0.3879
  -4.750  -0.1158   0.01627   0.00921  -0.0884   0.7551   0.4142
  -4.500  -0.1043   0.01611   0.00914  -0.0852   0.7489   0.4445
  -4.250  -0.0825   0.01588   0.00899  -0.0840   0.7445   0.4775
  -4.000  -0.0630   0.01581   0.00898  -0.0823   0.7397   0.5064
  -3.750  -0.0562   0.01588   0.00915  -0.0782   0.7327   0.5293
  -3.500  -0.0342   0.01582   0.00911  -0.0769   0.7277   0.5538
  -3.250  -0.0043   0.01578   0.00901  -0.0771   0.7239   0.5775
  -3.000   0.0084   0.01592   0.00921  -0.0740   0.7179   0.5946
  -2.750   0.0249   0.01600   0.00932  -0.0716   0.7119   0.6110
  -2.500   0.0533   0.01600   0.00928  -0.0715   0.7074   0.6279
  -2.250   0.0873   0.01602   0.00921  -0.0725   0.7038   0.6442
  -2.000   0.0929   0.01623   0.00949  -0.0681   0.6970   0.6566
  -1.750   0.1155   0.01630   0.00956  -0.0669   0.6915   0.6689
  -1.500   0.1456   0.01628   0.00945  -0.0671   0.6873   0.6828
  -1.250   0.1757   0.01641   0.00958  -0.0674   0.6830   0.6941
  -1.000   0.1830   0.01655   0.00976  -0.0633   0.6764   0.7053
  -0.750   0.2095   0.01662   0.00982  -0.0628   0.6714   0.7171
  -0.500   0.2452   0.01664   0.00977  -0.0641   0.6674   0.7287
  -0.250   0.2602   0.01679   0.00994  -0.0615   0.6619   0.7401
   0.000   0.2761   0.01689   0.01008  -0.0590   0.6559   0.7493
   0.250   0.3046   0.01690   0.01004  -0.0590   0.6513   0.7600
   0.500   0.3438   0.01690   0.00995  -0.0611   0.6474   0.7689
   0.750   0.3484   0.01705   0.01019  -0.0565   0.6408   0.7784
   1.000   0.3666   0.01705   0.01017  -0.0546   0.6354   0.7877
   1.250   0.4022   0.01705   0.01013  -0.0560   0.6311   0.7955
   1.500   0.4268   0.01707   0.01006  -0.0555   0.6266   0.8055
   1.750   0.4351   0.01719   0.01030  -0.0517   0.6201   0.8133
   2.000   0.4576   0.01715   0.01022  -0.0506   0.6150   0.8230
   2.250   0.4972   0.01714   0.01014  -0.0529   0.6109   0.8302
   2.500   0.5089   0.01727   0.01033  -0.0498   0.6054   0.8399
   2.750   0.5205   0.01730   0.01040  -0.0467   0.5994   0.8497
   3.000   0.5544   0.01731   0.01037  -0.0479   0.5946   0.8579
   3.250   0.5940   0.01734   0.01028  -0.0503   0.5907   0.8664
   3.500   0.5947   0.01756   0.01066  -0.0452   0.5843   0.8768
   3.750   0.6155   0.01761   0.01071  -0.0439   0.5789   0.8870
   4.000   0.6633   0.01771   0.01074  -0.0479   0.5744   0.8925
   4.250   0.6807   0.01789   0.01093  -0.0461   0.5693   0.9039
   4.500   0.7053   0.01821   0.01133  -0.0458   0.5632   0.9112
   4.750   0.7377   0.01832   0.01139  -0.0469   0.5583   0.9207
   5.000   0.7966   0.01852   0.01147  -0.0533   0.5539   0.9232
   5.250   0.8118   0.01898   0.01207  -0.0514   0.5474   0.9323
   5.500   0.8445   0.01922   0.01231  -0.0528   0.5419   0.9402
   5.750   0.9012   0.01943   0.01242  -0.0588   0.5373   0.9419
   6.000   0.9334   0.01984   0.01288  -0.0603   0.5318   0.9485
   6.250   0.9600   0.02014   0.01323  -0.0608   0.5257   0.9570
   6.500   1.0082   0.02032   0.01336  -0.0652   0.5207   0.9608
   6.750   1.0510   0.02061   0.01359  -0.0686   0.5160   0.9669
   7.000   1.0747   0.02099   0.01409  -0.0689   0.5097   0.9758
   7.250   1.1136   0.02117   0.01427  -0.0718   0.5043   0.9824
   7.500   1.1695   0.02135   0.01434  -0.0777   0.4997   0.9842
   7.750   1.1938   0.02176   0.01489  -0.0783   0.4936   0.9941
   8.000   1.2316   0.02199   0.01515  -0.0813   0.4878   1.0000
   8.250   1.2288   0.02190   0.01500  -0.0764   0.4840   1.0000
   8.500   1.2374   0.02200   0.01503  -0.0735   0.4801   1.0000
   8.750   1.1953   0.02230   0.01541  -0.0614   0.4759   1.0000
   9.000   1.1904   0.02264   0.01577  -0.0561   0.4712   1.0000
   9.250   1.2103   0.02276   0.01584  -0.0550   0.4667   1.0000
   9.500   1.2467   0.02292   0.01591  -0.0568   0.4626   1.0000
   9.750   1.2197   0.02368   0.01680  -0.0479   0.4578   1.0000
  10.000   1.2215   0.02419   0.01734  -0.0441   0.4530   1.0000
  10.250   1.2463   0.02433   0.01744  -0.0438   0.4486   1.0000
  10.500   1.2790   0.02450   0.01755  -0.0449   0.4444   1.0000
  10.750   1.2544   0.02558   0.01877  -0.0373   0.4393   1.0000
  11.000   1.2600   0.02616   0.01939  -0.0343   0.4343   1.0000
  11.250   1.2906   0.02614   0.01931  -0.0350   0.4298   1.0000
  11.500   1.3042   0.02670   0.01989  -0.0333   0.4253   1.0000
  11.750   1.2858   0.02799   0.02131  -0.0273   0.4198   1.0000
  12.000   1.2995   0.02844   0.02176  -0.0258   0.4149   1.0000
  12.250   1.3401   0.02817   0.02140  -0.0277   0.4105   1.0000
  12.500   1.3219   0.02971   0.02308  -0.0223   0.4054   1.0000
  12.750   1.3155   0.03093   0.02439  -0.0185   0.3998   1.0000
  13.000   1.3427   0.03086   0.02427  -0.0186   0.3948   1.0000
  13.250   1.3516   0.03162   0.02505  -0.0168   0.3895   1.0000
  13.500   1.3310   0.03355   0.02711  -0.0120   0.3831   1.0000
  13.750   1.3552   0.03341   0.02689  -0.0118   0.3768   1.0000
  14.000   1.3512   0.03484   0.02839  -0.0090   0.3708   1.0000
  14.250   1.3400   0.03668   0.03033  -0.0058   0.3644   1.0000
  14.500   1.3659   0.03654   0.03012  -0.0057   0.3588   1.0000
  14.750   1.3538   0.03869   0.03239  -0.0028   0.3527   1.0000
  15.000   1.3476   0.04057   0.03435  -0.0005   0.3463   1.0000
  15.250   1.3760   0.04027   0.03396  -0.0006   0.3410   1.0000
  15.500   1.3559   0.04329   0.03713   0.0023   0.3348   1.0000
  15.750   1.3533   0.04518   0.03908   0.0039   0.3284   1.0000
  16.000   1.3881   0.04434   0.03813   0.0034   0.3229   1.0000
  16.250   1.3512   0.04901   0.04303   0.0065   0.3158   1.0000
  16.500   1.3590   0.05023   0.04425   0.0073   0.3093   1.0000
  16.750   1.3615   0.05199   0.04605   0.0083   0.3030   1.0000
  17.000   1.3462   0.05541   0.04958   0.0097   0.2955   1.0000
  17.250   1.3702   0.05523   0.04929   0.0098   0.2890   1.0000
  17.500   1.3389   0.06038   0.05464   0.0113   0.2809   1.0000
  17.750   1.3581   0.06062   0.05478   0.0115   0.2737   1.0000
  18.000   1.3304   0.06576   0.06011   0.0125   0.2655   1.0000
  18.250   1.3438   0.06660   0.06086   0.0128   0.2578   1.0000
  18.500   1.3186   0.07175   0.06617   0.0132   0.2489   1.0000
  18.750   1.3283   0.07301   0.06734   0.0135   0.2404   1.0000
  19.000   1.3050   0.07820   0.07267   0.0136   0.2310   1.0000
  19.250   1.3028   0.08095   0.07539   0.0136   0.2221   1.0000
<< Back to FX 83-W-227 (fx83w227-il)

Polar data table (+)

Polar graphs


<< Back to FX 83-W-227 (fx83w227-il)