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GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 593 AIRFOIL (goe593-il)
Reynolds number: 200,000
Max Cl/Cd: 69.9 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe593-il-200000-n5.txt
Download as CSV file: xf-goe593-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 593 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3975   0.09044   0.08695  -0.0419   1.0000   0.0237
  -9.500  -0.4052   0.08192   0.07847  -0.0492   0.9962   0.0244
  -9.000  -0.5328   0.03391   0.02873  -0.0856   0.9573   0.0253
  -8.750  -0.5085   0.03240   0.02713  -0.0866   0.9531   0.0260
  -8.500  -0.4839   0.03128   0.02590  -0.0872   0.9486   0.0268
  -8.250  -0.4636   0.02967   0.02405  -0.0870   0.9423   0.0280
  -8.000  -0.4396   0.02728   0.02116  -0.0878   0.9385   0.0296
  -7.750  -0.4195   0.02525   0.01865  -0.0872   0.9326   0.0308
  -7.500  -0.3937   0.02420   0.01755  -0.0874   0.9277   0.0319
  -7.250  -0.3630   0.02331   0.01655  -0.0885   0.9246   0.0333
  -7.000  -0.3302   0.02219   0.01517  -0.0899   0.9222   0.0352
  -6.750  -0.3079   0.02120   0.01392  -0.0889   0.9150   0.0364
  -6.500  -0.2773   0.02011   0.01267  -0.0898   0.9109   0.0380
  -6.250  -0.2434   0.01931   0.01183  -0.0913   0.9079   0.0396
  -6.000  -0.2140   0.01857   0.01099  -0.0917   0.9029   0.0410
  -5.750  -0.1861   0.01790   0.01019  -0.0917   0.8967   0.0427
  -5.500  -0.1525   0.01724   0.00937  -0.0928   0.8926   0.0445
  -5.250  -0.1220   0.01645   0.00854  -0.0935   0.8875   0.0462
  -5.000  -0.0959   0.01592   0.00798  -0.0932   0.8801   0.0477
  -4.750  -0.0627   0.01538   0.00739  -0.0943   0.8753   0.0499
  -4.500  -0.0364   0.01500   0.00694  -0.0939   0.8676   0.0524
  -4.250  -0.0072   0.01454   0.00642  -0.0941   0.8610   0.0549
  -4.000   0.0214   0.01410   0.00598  -0.0942   0.8542   0.0580
  -3.750   0.0480   0.01378   0.00561  -0.0939   0.8459   0.0619
  -3.500   0.0772   0.01344   0.00526  -0.0941   0.8390   0.0682
  -3.250   0.1028   0.01316   0.00500  -0.0935   0.8300   0.0787
  -3.000   0.1309   0.01289   0.00477  -0.0935   0.8221   0.0955
  -2.750   0.1577   0.01269   0.00456  -0.0931   0.8128   0.1132
  -2.500   0.1841   0.01250   0.00437  -0.0927   0.8030   0.1296
  -2.250   0.2125   0.01230   0.00415  -0.0927   0.7932   0.1478
  -2.000   0.2375   0.01212   0.00398  -0.0919   0.7808   0.1669
  -1.750   0.2624   0.01190   0.00383  -0.0913   0.7686   0.1962
  -1.500   0.2868   0.01159   0.00372  -0.0905   0.7571   0.2591
  -1.250   0.3104   0.01120   0.00359  -0.0897   0.7468   0.3480
  -1.000   0.3288   0.01068   0.00357  -0.0878   0.7358   0.5002
  -0.750   0.3481   0.01026   0.00356  -0.0858   0.7259   0.6331
  -0.500   0.3727   0.00993   0.00361  -0.0845   0.7157   0.7672
  -0.250   0.4296   0.00988   0.00372  -0.0900   0.7040   0.8918
   0.000   0.4836   0.00997   0.00372  -0.0952   0.6918   0.9407
   0.250   0.5273   0.01008   0.00371  -0.0984   0.6793   0.9639
   0.500   0.5720   0.01022   0.00371  -0.1018   0.6667   0.9851
   0.750   0.6233   0.01031   0.00369  -0.1069   0.6527   1.0000
   1.000   0.6435   0.01040   0.00370  -0.1053   0.6406   1.0000
   1.250   0.6637   0.01050   0.00371  -0.1037   0.6280   1.0000
   1.500   0.6840   0.01061   0.00374  -0.1021   0.6154   1.0000
   1.750   0.7042   0.01074   0.00378  -0.1005   0.6023   1.0000
   2.000   0.7241   0.01087   0.00384  -0.0988   0.5882   1.0000
   2.250   0.7438   0.01101   0.00390  -0.0971   0.5732   1.0000
   2.500   0.7631   0.01117   0.00398  -0.0953   0.5568   1.0000
   2.750   0.7820   0.01135   0.00407  -0.0934   0.5392   1.0000
   3.000   0.8008   0.01154   0.00417  -0.0916   0.5210   1.0000
   3.250   0.8193   0.01174   0.00429  -0.0896   0.5023   1.0000
   3.500   0.8374   0.01198   0.00444  -0.0876   0.4831   1.0000
   3.750   0.8548   0.01224   0.00459  -0.0855   0.4641   1.0000
   4.000   0.8719   0.01252   0.00477  -0.0833   0.4457   1.0000
   4.250   0.8889   0.01282   0.00498  -0.0812   0.4282   1.0000
   4.500   0.9063   0.01313   0.00520  -0.0792   0.4124   1.0000
   4.750   0.9242   0.01343   0.00543  -0.0772   0.3983   1.0000
   5.000   0.9426   0.01372   0.00569  -0.0754   0.3858   1.0000
   5.250   0.9610   0.01403   0.00596  -0.0736   0.3743   1.0000
   5.500   0.9788   0.01436   0.00624  -0.0718   0.3639   1.0000
   5.750   0.9973   0.01467   0.00653  -0.0701   0.3534   1.0000
   6.000   1.0158   0.01500   0.00684  -0.0683   0.3443   1.0000
   6.250   1.0336   0.01535   0.00716  -0.0665   0.3354   1.0000
   6.500   1.0516   0.01567   0.00749  -0.0648   0.3260   1.0000
   6.750   1.0673   0.01605   0.00783  -0.0626   0.3172   1.0000
   7.000   1.0841   0.01637   0.00817  -0.0606   0.3073   1.0000
   7.250   1.1004   0.01674   0.00853  -0.0586   0.2995   1.0000
   7.500   1.1172   0.01710   0.00891  -0.0567   0.2911   1.0000
   7.750   1.1336   0.01749   0.00931  -0.0548   0.2835   1.0000
   8.000   1.1504   0.01786   0.00972  -0.0530   0.2757   1.0000
   8.250   1.1664   0.01828   0.01015  -0.0511   0.2683   1.0000
   8.500   1.1824   0.01869   0.01059  -0.0492   0.2595   1.0000
   8.750   1.1978   0.01913   0.01107  -0.0473   0.2508   1.0000
   9.000   1.2127   0.01960   0.01157  -0.0454   0.2424   1.0000
   9.250   1.2287   0.02006   0.01209  -0.0437   0.2350   1.0000
   9.500   1.2433   0.02058   0.01264  -0.0418   0.2272   1.0000
   9.750   1.2585   0.02109   0.01323  -0.0401   0.2195   1.0000
  10.000   1.2713   0.02171   0.01388  -0.0381   0.2105   1.0000
  10.250   1.2852   0.02230   0.01454  -0.0363   0.1997   1.0000
  10.500   1.2970   0.02302   0.01529  -0.0344   0.1867   1.0000
  10.750   1.3069   0.02386   0.01613  -0.0323   0.1704   1.0000
  11.000   1.3137   0.02491   0.01714  -0.0300   0.1494   1.0000
  11.250   1.3156   0.02634   0.01846  -0.0274   0.1253   1.0000
  11.500   1.3167   0.02794   0.01995  -0.0249   0.1064   1.0000
  11.750   1.3177   0.02963   0.02159  -0.0226   0.0930   1.0000
  12.000   1.3198   0.03130   0.02326  -0.0205   0.0841   1.0000
  12.250   1.3208   0.03312   0.02509  -0.0187   0.0776   1.0000
  12.500   1.3248   0.03478   0.02682  -0.0171   0.0723   1.0000
  12.750   1.3258   0.03675   0.02883  -0.0156   0.0680   1.0000
  13.000   1.3272   0.03877   0.03094  -0.0143   0.0652   1.0000
  13.250   1.3310   0.04064   0.03294  -0.0133   0.0624   1.0000
  13.500   1.3323   0.04283   0.03521  -0.0123   0.0594   1.0000
  13.750   1.3307   0.04537   0.03782  -0.0115   0.0569   1.0000
  14.000   1.3285   0.04809   0.04062  -0.0109   0.0549   1.0000
  14.250   1.3313   0.05037   0.04305  -0.0104   0.0525   1.0000
  14.500   1.3314   0.05304   0.04584  -0.0102   0.0502   1.0000
  14.750   1.3289   0.05609   0.04897  -0.0101   0.0479   1.0000
  15.000   1.3229   0.05965   0.05263  -0.0102   0.0462   1.0000
  15.250   1.3223   0.06268   0.05580  -0.0104   0.0442   1.0000
  15.500   1.3207   0.06592   0.05918  -0.0108   0.0421   1.0000
  15.750   1.3166   0.06959   0.06295  -0.0114   0.0402   1.0000
  16.000   1.3093   0.07380   0.06723  -0.0124   0.0383   1.0000
  16.250   1.3058   0.07759   0.07116  -0.0132   0.0362   1.0000
  16.500   1.3012   0.08164   0.07533  -0.0143   0.0340   1.0000
  16.750   1.2939   0.08616   0.07995  -0.0157   0.0326   1.0000
  17.000   1.2853   0.09097   0.08484  -0.0173   0.0312   1.0000
  17.250   1.2796   0.09538   0.08939  -0.0187   0.0295   1.0000
  17.500   1.2729   0.10003   0.09416  -0.0204   0.0279   1.0000
  17.750   1.2641   0.10513   0.09933  -0.0224   0.0266   1.0000
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