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GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 592 AIRFOIL (goe592-il)
Reynolds number: 200,000
Max Cl/Cd: 76.16 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe592-il-200000-n5.txt
Download as CSV file: xf-goe592-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 592 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.0776   0.10778   0.10344  -0.1287   0.9256   0.0452
 -11.750   0.0803   0.10493   0.10058  -0.1303   0.9184   0.0453
 -11.500   0.0923   0.10182   0.09744  -0.1324   0.9136   0.0453
 -11.250   0.1018   0.09879   0.09438  -0.1342   0.9083   0.0453
 -11.000   0.1068   0.09491   0.09049  -0.1347   0.9013   0.0408
 -10.750   0.1270   0.09374   0.08930  -0.1354   0.8963   0.0439
 -10.500   0.1338   0.09103   0.08658  -0.1364   0.8901   0.0434
 -10.250   0.1391   0.08846   0.08399  -0.1372   0.8829   0.0437
 -10.000   0.1467   0.08543   0.08092  -0.1388   0.8774   0.0428
  -9.750   0.1434   0.08199   0.07747  -0.1397   0.8690   0.0413
  -9.500   0.1477   0.07917   0.07462  -0.1407   0.8621   0.0413
  -9.250   0.1541   0.07689   0.07232  -0.1413   0.8554   0.0416
  -9.000   0.1602   0.07493   0.07036  -0.1415   0.8478   0.0424
  -8.750   0.1659   0.07243   0.06781  -0.1425   0.8418   0.0429
  -8.500   0.1653   0.06997   0.06537  -0.1426   0.8333   0.0431
  -8.250   0.1659   0.06721   0.06258  -0.1433   0.8260   0.0430
  -8.000   0.1627   0.06455   0.05992  -0.1435   0.8179   0.0430
  -7.750   0.1567   0.06188   0.05723  -0.1435   0.8097   0.0431
  -7.500   0.1507   0.05904   0.05437  -0.1444   0.8023   0.0433
  -7.250   0.1466   0.05540   0.05071  -0.1467   0.7941   0.0440
  -6.750   0.1175   0.03736   0.03210  -0.1585   0.7780   0.0456
  -6.500   0.1347   0.03515   0.02971  -0.1591   0.7727   0.0461
  -6.250   0.1526   0.03350   0.02792  -0.1591   0.7671   0.0468
  -6.000   0.1523   0.02625   0.01986  -0.1594   0.7605   0.0495
  -5.750   0.1683   0.02298   0.01595  -0.1590   0.7556   0.0511
  -5.500   0.1929   0.02247   0.01534  -0.1586   0.7506   0.0519
  -5.250   0.2150   0.02182   0.01458  -0.1578   0.7445   0.0528
  -5.000   0.2393   0.02091   0.01341  -0.1574   0.7395   0.0545
  -4.750   0.2648   0.01967   0.01175  -0.1572   0.7353   0.0567
  -4.500   0.2875   0.01944   0.01153  -0.1563   0.7291   0.0577
  -4.250   0.3127   0.01906   0.01106  -0.1558   0.7237   0.0590
  -4.000   0.3397   0.01849   0.01028  -0.1557   0.7193   0.0608
  -3.750   0.3642   0.01792   0.00948  -0.1550   0.7142   0.0631
  -3.500   0.3886   0.01773   0.00932  -0.1544   0.7085   0.0646
  -3.250   0.4153   0.01748   0.00898  -0.1541   0.7037   0.0667
  -3.000   0.4428   0.01711   0.00842  -0.1539   0.6994   0.0692
  -2.750   0.4660   0.01683   0.00810  -0.1530   0.6937   0.0712
  -2.500   0.4915   0.01665   0.00792  -0.1526   0.6885   0.0733
  -2.250   0.5190   0.01642   0.00759  -0.1524   0.6842   0.0761
  -2.000   0.5443   0.01626   0.00731  -0.1518   0.6793   0.0788
  -1.750   0.5680   0.01602   0.00713  -0.1511   0.6739   0.0811
  -1.500   0.5940   0.01586   0.00694  -0.1507   0.6691   0.0837
  -1.250   0.6220   0.01571   0.00669  -0.1506   0.6651   0.0868
  -1.000   0.6449   0.01557   0.00656  -0.1496   0.6598   0.0893
  -0.750   0.6688   0.01543   0.00646  -0.1489   0.6548   0.0920
  -0.500   0.6950   0.01534   0.00634  -0.1485   0.6502   0.0953
  -0.250   0.7221   0.01526   0.00620  -0.1483   0.6461   0.0985
   0.000   0.7439   0.01519   0.00618  -0.1471   0.6408   0.1013
   0.250   0.7679   0.01514   0.00616  -0.1464   0.6358   0.1052
   0.500   0.7941   0.01510   0.00608  -0.1460   0.6314   0.1095
   0.750   0.8193   0.01508   0.00605  -0.1455   0.6271   0.1139
   1.000   0.8410   0.01509   0.00613  -0.1444   0.6219   0.1197
   1.250   0.8649   0.01510   0.00615  -0.1436   0.6169   0.1275
   1.500   0.8912   0.01509   0.00614  -0.1433   0.6126   0.1397
   1.750   0.9138   0.01511   0.00624  -0.1423   0.6078   0.1588
   2.000   0.9347   0.01511   0.00638  -0.1411   0.6025   0.1955
   2.250   0.9574   0.01500   0.00649  -0.1402   0.5977   0.2788
   2.750   1.0295   0.01406   0.00696  -0.1440   0.5879   1.0000
   3.000   1.0504   0.01424   0.00709  -0.1427   0.5825   1.0000
   3.250   1.0744   0.01440   0.00716  -0.1419   0.5776   1.0000
   3.500   1.0957   0.01460   0.00731  -0.1407   0.5727   1.0000
   3.750   1.1139   0.01481   0.00752  -0.1389   0.5667   1.0000
   4.000   1.1352   0.01500   0.00764  -0.1377   0.5614   1.0000
   4.250   1.1569   0.01519   0.00778  -0.1366   0.5564   1.0000
   4.500   1.1707   0.01543   0.00804  -0.1340   0.5500   1.0000
   4.750   1.1895   0.01564   0.00820  -0.1324   0.5440   1.0000
   5.000   1.2081   0.01587   0.00839  -0.1308   0.5381   1.0000
   5.250   1.2221   0.01616   0.00870  -0.1283   0.5309   1.0000
   5.500   1.2411   0.01639   0.00887  -0.1268   0.5245   1.0000
   5.750   1.2561   0.01672   0.00921  -0.1247   0.5179   1.0000
   6.000   1.2723   0.01703   0.00952  -0.1228   0.5111   1.0000
   6.250   1.2897   0.01733   0.00978  -0.1211   0.5044   1.0000
   6.500   1.3021   0.01773   0.01020  -0.1187   0.4959   1.0000
   6.750   1.3191   0.01807   0.01048  -0.1170   0.4886   1.0000
   7.000   1.3310   0.01855   0.01100  -0.1146   0.4802   1.0000
   7.250   1.3468   0.01896   0.01136  -0.1129   0.4728   1.0000
   7.500   1.3596   0.01947   0.01190  -0.1108   0.4647   1.0000
   7.750   1.3731   0.01997   0.01237  -0.1087   0.4563   1.0000
   8.000   1.3852   0.02056   0.01299  -0.1066   0.4476   1.0000
   8.250   1.3977   0.02115   0.01354  -0.1046   0.4391   1.0000
   8.500   1.4102   0.02178   0.01421  -0.1027   0.4312   1.0000
   8.750   1.4221   0.02246   0.01488  -0.1007   0.4229   1.0000
   9.000   1.4333   0.02320   0.01564  -0.0987   0.4142   1.0000
   9.250   1.4427   0.02402   0.01643  -0.0965   0.4045   1.0000
   9.500   1.4525   0.02489   0.01733  -0.0945   0.3949   1.0000
   9.750   1.4613   0.02582   0.01824  -0.0925   0.3859   1.0000
  10.000   1.4691   0.02685   0.01930  -0.0904   0.3751   1.0000
  10.250   1.4763   0.02795   0.02040  -0.0883   0.3648   1.0000
  10.500   1.4809   0.02924   0.02164  -0.0860   0.3532   1.0000
  10.750   1.4870   0.03052   0.02295  -0.0841   0.3414   1.0000
  11.000   1.4926   0.03188   0.02432  -0.0822   0.3309   1.0000
  11.500   1.5016   0.03492   0.02736  -0.0785   0.3087   1.0000
  11.750   1.5050   0.03661   0.02905  -0.0767   0.2976   1.0000
  12.000   1.5065   0.03851   0.03092  -0.0749   0.2863   1.0000
  12.250   1.5094   0.04037   0.03280  -0.0733   0.2747   1.0000
  12.500   1.5117   0.04234   0.03478  -0.0718   0.2636   1.0000
  12.750   1.5119   0.04455   0.03698  -0.0703   0.2527   1.0000
  13.000   1.5121   0.04683   0.03926  -0.0689   0.2411   1.0000
  13.250   1.5123   0.04919   0.04162  -0.0676   0.2292   1.0000
  13.500   1.5105   0.05179   0.04421  -0.0664   0.2170   1.0000
  13.750   1.5070   0.05465   0.04705  -0.0652   0.2043   1.0000
  14.000   1.5033   0.05760   0.04999  -0.0642   0.1911   1.0000
  14.250   1.4985   0.06075   0.05312  -0.0632   0.1766   1.0000
  14.500   1.4926   0.06411   0.05645  -0.0624   0.1615   1.0000
  14.750   1.4863   0.06761   0.05992  -0.0617   0.1485   1.0000
  15.000   1.4794   0.07124   0.06353  -0.0611   0.1374   1.0000
  15.250   1.4756   0.07459   0.06689  -0.0607   0.1292   1.0000
  15.500   1.4705   0.07815   0.07045  -0.0604   0.1231   1.0000
  15.750   1.4692   0.08130   0.07365  -0.0603   0.1182   1.0000
  16.000   1.4666   0.08464   0.07702  -0.0602   0.1141   1.0000
  16.250   1.4636   0.08808   0.08049  -0.0602   0.1107   1.0000
  16.500   1.4650   0.09097   0.08346  -0.0602   0.1078   1.0000
  16.750   1.4656   0.09398   0.08654  -0.0603   0.1051   1.0000
  17.000   1.4653   0.09712   0.08973  -0.0605   0.1027   1.0000
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