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GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il)
Reynolds number: 200,000
Max Cl/Cd: 81.77 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe239-il-200000.txt
Download as CSV file: xf-goe239-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 239 (MVA H.31) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2910   0.11025   0.10689  -0.0325   1.0000   0.0538
  -9.000  -0.2991   0.10911   0.10580  -0.0299   1.0000   0.0550
  -8.750  -0.3055   0.10756   0.10429  -0.0285   0.9997   0.0564
  -8.500  -0.3017   0.10343   0.10018  -0.0414   0.9930   0.0598
  -8.250  -0.2950   0.09804   0.09481  -0.0487   0.9863   0.0604
  -8.000  -0.2678   0.09402   0.09076  -0.0464   0.9862   0.0616
  -7.750  -0.2435   0.09083   0.08754  -0.0485   0.9840   0.0634
  -7.500  -0.2285   0.08780   0.08452  -0.0515   0.9780   0.0664
  -7.250  -0.2097   0.07960   0.07630  -0.0764   0.9645   0.0715
  -7.000  -0.1931   0.07671   0.07342  -0.0718   0.9625   0.0727
  -6.750  -0.1664   0.07403   0.07071  -0.0728   0.9600   0.0746
  -6.500  -0.1392   0.07058   0.06723  -0.0778   0.9555   0.0780
  -6.250  -0.1023   0.06157   0.05812  -0.0985   0.9468   0.0855
  -6.000  -0.0738   0.05991   0.05646  -0.0979   0.9450   0.0878
  -5.750  -0.0470   0.05694   0.05345  -0.1017   0.9386   0.0919
  -5.500   0.0240   0.03101   0.02607  -0.1405   0.9319   0.0733
  -5.250   0.0675   0.02650   0.02099  -0.1457   0.9294   0.0685
  -5.000   0.0990   0.02377   0.01781  -0.1475   0.9222   0.0679
  -4.750   0.1366   0.02194   0.01555  -0.1496   0.9171   0.0695
  -4.500   0.1758   0.02033   0.01356  -0.1518   0.9130   0.0705
  -4.250   0.2040   0.01934   0.01231  -0.1516   0.9033   0.0713
  -4.000   0.2384   0.01751   0.01032  -0.1529   0.8975   0.0735
  -3.750   0.2654   0.01685   0.00964  -0.1525   0.8871   0.0767
  -3.500   0.2967   0.01614   0.00880  -0.1527   0.8791   0.0800
  -3.250   0.3246   0.01556   0.00810  -0.1522   0.8676   0.0829
  -3.000   0.3522   0.01470   0.00723  -0.1518   0.8556   0.0871
  -2.750   0.3805   0.01419   0.00670  -0.1514   0.8434   0.0942
  -2.500   0.4091   0.01354   0.00603  -0.1511   0.8305   0.1031
  -2.250   0.4373   0.01298   0.00545  -0.1508   0.8153   0.1174
  -2.000   0.4651   0.01238   0.00503  -0.1506   0.7973   0.1566
  -1.750   0.4925   0.01218   0.00502  -0.1502   0.7769   0.2499
  -1.500   0.5199   0.01225   0.00498  -0.1496   0.7564   0.2854
  -1.250   0.5473   0.01233   0.00495  -0.1492   0.7368   0.3078
  -1.000   0.5746   0.01245   0.00494  -0.1487   0.7175   0.3257
  -0.750   0.6020   0.01256   0.00493  -0.1484   0.7001   0.3415
  -0.500   0.6295   0.01268   0.00492  -0.1481   0.6849   0.3564
  -0.250   0.6571   0.01281   0.00490  -0.1479   0.6718   0.3706
   0.000   0.6846   0.01288   0.00492  -0.1477   0.6593   0.3841
   0.250   0.7121   0.01293   0.00493  -0.1475   0.6482   0.3973
   0.500   0.7398   0.01300   0.00493  -0.1474   0.6387   0.4116
   0.750   0.7673   0.01302   0.00496  -0.1473   0.6289   0.4285
   1.000   0.7949   0.01307   0.00500  -0.1472   0.6199   0.4477
   1.250   0.8224   0.01307   0.00505  -0.1470   0.6111   0.4696
   1.500   0.8495   0.01306   0.00516  -0.1469   0.6029   0.5025
   1.750   0.8759   0.01291   0.00532  -0.1466   0.5953   0.5915
   2.000   0.8964   0.01237   0.00533  -0.1445   0.5886   1.0000
   2.250   0.9243   0.01260   0.00546  -0.1445   0.5813   1.0000
   2.500   0.9525   0.01291   0.00563  -0.1445   0.5750   1.0000
   2.750   0.9798   0.01313   0.00584  -0.1444   0.5681   1.0000
   3.000   1.0076   0.01342   0.00603  -0.1443   0.5617   1.0000
   3.250   1.0348   0.01369   0.00629  -0.1442   0.5549   1.0000
   3.500   1.0619   0.01395   0.00651  -0.1440   0.5477   1.0000
   3.750   1.0893   0.01427   0.00676  -0.1439   0.5412   1.0000
   4.000   1.1157   0.01451   0.00704  -0.1436   0.5338   1.0000
   4.250   1.1434   0.01484   0.00728  -0.1435   0.5274   1.0000
   4.500   1.1691   0.01509   0.00761  -0.1431   0.5198   1.0000
   4.750   1.1959   0.01538   0.00786  -0.1429   0.5128   1.0000
   5.000   1.2219   0.01568   0.00820  -0.1426   0.5053   1.0000
   5.250   1.2479   0.01593   0.00846  -0.1422   0.4974   1.0000
   5.500   1.2735   0.01623   0.00879  -0.1418   0.4895   1.0000
   5.750   1.2986   0.01644   0.00902  -0.1412   0.4804   1.0000
   6.000   1.3230   0.01667   0.00930  -0.1406   0.4708   1.0000
   6.250   1.3480   0.01687   0.00945  -0.1400   0.4614   1.0000
   6.500   1.3705   0.01700   0.00970  -0.1390   0.4496   1.0000
   6.750   1.3935   0.01718   0.00992  -0.1380   0.4383   1.0000
   7.000   1.4168   0.01738   0.01011  -0.1372   0.4279   1.0000
   7.250   1.4391   0.01760   0.01042  -0.1362   0.4164   1.0000
   7.500   1.4616   0.01789   0.01077  -0.1353   0.4056   1.0000
   7.750   1.4835   0.01819   0.01108  -0.1342   0.3949   1.0000
   8.000   1.5045   0.01852   0.01140  -0.1330   0.3833   1.0000
   8.250   1.5248   0.01887   0.01184  -0.1318   0.3709   1.0000
   8.500   1.5451   0.01930   0.01231  -0.1305   0.3598   1.0000
   8.750   1.5643   0.01977   0.01278  -0.1291   0.3488   1.0000
   9.000   1.5813   0.02027   0.01328  -0.1274   0.3354   1.0000
   9.500   1.6102   0.02144   0.01445  -0.1232   0.3063   1.0000
   9.750   1.6226   0.02208   0.01513  -0.1208   0.2917   1.0000
  10.000   1.6327   0.02273   0.01584  -0.1179   0.2779   1.0000
  10.250   1.6411   0.02352   0.01668  -0.1150   0.2629   1.0000
  10.500   1.6472   0.02449   0.01765  -0.1119   0.2459   1.0000
  10.750   1.6523   0.02561   0.01879  -0.1089   0.2233   1.0000
  11.000   1.6510   0.02723   0.02033  -0.1055   0.1910   1.0000
  11.250   1.6380   0.02989   0.02268  -0.1014   0.1409   1.0000
  11.500   1.6223   0.03310   0.02566  -0.0975   0.1133   1.0000
  11.750   1.6108   0.03623   0.02873  -0.0945   0.0966   1.0000
  12.000   1.6025   0.03927   0.03177  -0.0921   0.0842   1.0000
  12.250   1.5949   0.04243   0.03495  -0.0902   0.0756   1.0000
  12.500   1.5843   0.04606   0.03863  -0.0885   0.0696   1.0000
  12.750   1.5747   0.04980   0.04244  -0.0872   0.0646   1.0000
  13.000   1.5584   0.05449   0.04717  -0.0863   0.0610   1.0000
  13.250   1.5501   0.05848   0.05130  -0.0857   0.0572   1.0000
  13.500   1.5391   0.06295   0.05585  -0.0854   0.0540   1.0000
  13.750   1.5234   0.06802   0.06093  -0.0851   0.0515   1.0000
  14.000   1.5178   0.07193   0.06498  -0.0848   0.0488   1.0000
  14.250   1.5125   0.07584   0.06898  -0.0847   0.0462   1.0000
  14.500   1.5065   0.07977   0.07294  -0.0846   0.0441   1.0000
  14.750   1.5011   0.08318   0.07632  -0.0837   0.0420   1.0000
  15.000   1.5008   0.08657   0.07987  -0.0837   0.0402   1.0000
  15.250   1.5001   0.08993   0.08334  -0.0838   0.0383   1.0000
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