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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.65 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe140-il-1000000.txt
Download as CSV file: xf-goe140-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3035   0.09522   0.09373  -0.0190   1.0000   0.0141
  -8.000  -0.2967   0.09247   0.09100  -0.0203   1.0000   0.0146
  -7.750  -0.2914   0.08962   0.08817  -0.0216   1.0000   0.0156
  -7.500  -0.2791   0.08491   0.08347  -0.0294   0.9880   0.0164
  -7.250  -0.1966   0.06443   0.06279  -0.0378   0.8741   0.0167
  -7.000  -0.1888   0.06160   0.05987  -0.0385   0.8501   0.0169
  -6.750  -0.1785   0.05885   0.05704  -0.0401   0.8303   0.0172
  -6.500  -0.1669   0.05570   0.05382  -0.0427   0.8128   0.0175
  -6.250  -0.1535   0.05235   0.05040  -0.0459   0.7966   0.0181
  -6.000  -0.1377   0.04867   0.04664  -0.0498   0.7815   0.0193
  -5.750  -0.1084   0.04258   0.04042  -0.0608   0.7700   0.0206
  -5.500  -0.0867   0.03803   0.03574  -0.0651   0.7560   0.0207
  -4.500  -0.0115   0.04021   0.03734  -0.0791   0.7254   0.0223
  -4.250   0.0164   0.03798   0.03496  -0.0811   0.7054   0.0234
  -4.000   0.0545   0.03543   0.03212  -0.0835   0.6857   0.0259
  -3.750   0.0852   0.03271   0.02917  -0.0851   0.6662   0.0261
  -3.500   0.1165   0.02655   0.02260  -0.0882   0.6500   0.0268
  -3.250   0.1433   0.02520   0.02110  -0.0891   0.6294   0.0272
  -3.000   0.1708   0.02409   0.01983  -0.0897   0.6102   0.0278
  -2.750   0.1990   0.02295   0.01851  -0.0904   0.5921   0.0285
  -2.500   0.2282   0.02169   0.01707  -0.0910   0.5744   0.0296
  -2.250   0.2592   0.02096   0.01613  -0.0909   0.5563   0.0326
  -2.000   0.2894   0.02002   0.01495  -0.0911   0.5383   0.0331
  -1.750   0.3208   0.01618   0.01066  -0.0926   0.5228   0.0348
  -1.500   0.3491   0.01571   0.01008  -0.0929   0.5057   0.0356
  -1.000   0.4100   0.01251   0.00626  -0.0934   0.4762   0.0320
  -0.750   0.4393   0.01141   0.00493  -0.0936   0.4627   0.0315
  -0.500   0.4683   0.01072   0.00408  -0.0938   0.4500   0.0314
  -0.250   0.4970   0.01027   0.00351  -0.0939   0.4380   0.0316
   0.000   0.5257   0.01003   0.00318  -0.0940   0.4267   0.0323
   0.250   0.5543   0.00988   0.00296  -0.0941   0.4159   0.0327
   0.500   0.5829   0.00978   0.00282  -0.0943   0.4067   0.0331
   0.750   0.6116   0.00956   0.00251  -0.0945   0.3976   0.0336
   1.000   0.6405   0.00940   0.00228  -0.0947   0.3881   0.0343
   1.250   0.6692   0.00933   0.00216  -0.0948   0.3789   0.0353
   1.500   0.6977   0.00933   0.00212  -0.0950   0.3703   0.0373
   1.750   0.7263   0.00932   0.00209  -0.0951   0.3635   0.0394
   2.000   0.7547   0.00937   0.00209  -0.0952   0.3560   0.0419
   2.250   0.7833   0.00937   0.00216  -0.0953   0.3497   0.0603
   2.500   0.8115   0.00946   0.00224  -0.0954   0.3428   0.0748
   2.750   0.8397   0.00953   0.00230  -0.0955   0.3368   0.0820
   3.000   0.8679   0.00960   0.00236  -0.0956   0.3306   0.0877
   3.250   0.8959   0.00970   0.00245  -0.0957   0.3243   0.0955
   3.500   0.9242   0.00973   0.00254  -0.0959   0.3184   0.1181
   4.000   0.9749   0.00841   0.00290  -0.0954   0.3013   1.0000
   4.250   1.0026   0.00858   0.00301  -0.0955   0.2939   1.0000
   4.500   1.0304   0.00872   0.00312  -0.0956   0.2868   1.0000
   4.750   1.0580   0.00891   0.00325  -0.0956   0.2781   1.0000
   5.000   1.0854   0.00910   0.00340  -0.0956   0.2689   1.0000
   5.250   1.1127   0.00930   0.00354  -0.0956   0.2579   1.0000
   5.500   1.1396   0.00954   0.00372  -0.0956   0.2447   1.0000
   5.750   1.1656   0.00992   0.00396  -0.0955   0.2228   1.0000
   6.000   1.1843   0.01136   0.00478  -0.0946   0.1227   1.0000
   6.500   1.2256   0.01363   0.00648  -0.0929   0.0157   1.0000
   6.750   1.2512   0.01397   0.00685  -0.0926   0.0144   1.0000
   7.000   1.2763   0.01434   0.00727  -0.0923   0.0135   1.0000
   7.250   1.3009   0.01477   0.00775  -0.0919   0.0125   1.0000
   7.500   1.3245   0.01531   0.00834  -0.0913   0.0117   1.0000
   7.750   1.3460   0.01610   0.00923  -0.0905   0.0109   1.0000
   8.000   1.3688   0.01666   0.00984  -0.0898   0.0106   1.0000
   8.250   1.3915   0.01719   0.01042  -0.0892   0.0103   1.0000
   8.500   1.4134   0.01779   0.01107  -0.0884   0.0099   1.0000
   8.750   1.4344   0.01843   0.01175  -0.0876   0.0093   1.0000
   9.000   1.4541   0.01915   0.01253  -0.0866   0.0088   1.0000
   9.250   1.4718   0.02001   0.01346  -0.0853   0.0085   1.0000
   9.500   1.4849   0.02119   0.01471  -0.0834   0.0082   1.0000
   9.750   1.4882   0.02297   0.01661  -0.0801   0.0079   1.0000
  10.000   1.4908   0.02448   0.01821  -0.0767   0.0078   1.0000
  10.250   1.5001   0.02532   0.01911  -0.0742   0.0077   1.0000
  10.500   1.5058   0.02648   0.02036  -0.0715   0.0076   1.0000
  10.750   1.5100   0.02790   0.02186  -0.0690   0.0074   1.0000
  11.000   1.5134   0.02955   0.02360  -0.0670   0.0073   1.0000
  11.250   1.5154   0.03155   0.02569  -0.0653   0.0071   1.0000
  11.500   1.5153   0.03398   0.02821  -0.0641   0.0070   1.0000
  11.750   1.5153   0.03664   0.03096  -0.0633   0.0069   1.0000
  12.000   1.5140   0.03961   0.03402  -0.0628   0.0068   1.0000
  12.250   1.5123   0.04278   0.03729  -0.0626   0.0067   1.0000
  12.500   1.5108   0.04603   0.04062  -0.0626   0.0065   1.0000
  12.750   1.5093   0.04936   0.04404  -0.0627   0.0064   1.0000
  13.000   1.5077   0.05276   0.04752  -0.0630   0.0063   1.0000
  13.250   1.5052   0.05627   0.05110  -0.0633   0.0061   1.0000
  13.500   1.5022   0.05990   0.05480  -0.0636   0.0060   1.0000
  13.750   1.4983   0.06361   0.05858  -0.0640   0.0059   1.0000
  14.000   1.4941   0.06734   0.06238  -0.0643   0.0058   1.0000
  14.250   1.4903   0.07098   0.06608  -0.0645   0.0058   1.0000
  14.500   1.4874   0.07435   0.06949  -0.0644   0.0057   1.0000
  14.750   1.4868   0.07703   0.07220  -0.0634   0.0056   1.0000
  15.000   1.4944   0.07758   0.07273  -0.0597   0.0055   1.0000
  15.250   1.5089   0.07750   0.07266  -0.0553   0.0054   1.0000
  15.500   1.5007   0.08230   0.07761  -0.0572   0.0054   1.0000
  15.750   1.4959   0.08659   0.08203  -0.0588   0.0053   1.0000
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