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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 500,000
Max Cl/Cd: 108.21 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe115-il-500000.txt
Download as CSV file: xf-goe115-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3819   0.08605   0.08387  -0.0395   1.0000   0.0205
  -8.750  -0.3836   0.08228   0.08012  -0.0408   1.0000   0.0207
  -8.500  -0.3890   0.07753   0.07543  -0.0430   1.0000   0.0224
  -6.750  -0.3153   0.02695   0.02311  -0.0958   0.9503   0.0214
  -6.250  -0.2592   0.02159   0.01690  -0.0979   0.9268   0.0223
  -5.500  -0.1862   0.01618   0.01057  -0.0969   0.8845   0.0257
  -5.250  -0.1614   0.01549   0.00983  -0.0965   0.8707   0.0282
  -5.000  -0.1364   0.01453   0.00868  -0.0958   0.8571   0.0293
  -4.750  -0.1112   0.01371   0.00771  -0.0951   0.8439   0.0303
  -4.500  -0.0855   0.01317   0.00701  -0.0946   0.8310   0.0315
  -4.250  -0.0606   0.01239   0.00609  -0.0939   0.8183   0.0333
  -4.000  -0.0365   0.01149   0.00509  -0.0932   0.8055   0.0342
  -3.750  -0.0117   0.01088   0.00438  -0.0926   0.7926   0.0354
  -3.500   0.0137   0.01043   0.00383  -0.0921   0.7795   0.0372
  -3.250   0.0394   0.01009   0.00338  -0.0916   0.7662   0.0388
  -3.000   0.0655   0.00982   0.00299  -0.0912   0.7526   0.0397
  -2.750   0.0919   0.00961   0.00266  -0.0908   0.7392   0.0406
  -2.500   0.1184   0.00944   0.00236  -0.0904   0.7262   0.0415
  -2.250   0.1452   0.00931   0.00212  -0.0901   0.7140   0.0428
  -2.000   0.1721   0.00921   0.00192  -0.0899   0.7029   0.0449
  -1.750   0.1991   0.00913   0.00177  -0.0896   0.6930   0.0501
  -1.500   0.2243   0.00864   0.00157  -0.0893   0.6839   0.1553
  -1.250   0.2504   0.00838   0.00157  -0.0891   0.6754   0.2439
  -1.000   0.2775   0.00841   0.00160  -0.0889   0.6680   0.2715
  -0.750   0.3050   0.00844   0.00162  -0.0888   0.6604   0.2863
  -0.500   0.3323   0.00852   0.00165  -0.0886   0.6540   0.3021
  -0.250   0.3597   0.00853   0.00170  -0.0886   0.6471   0.3149
   0.000   0.3868   0.00858   0.00172  -0.0884   0.6407   0.3243
   0.250   0.4142   0.00860   0.00175  -0.0883   0.6343   0.3337
   0.500   0.4414   0.00864   0.00178  -0.0882   0.6286   0.3439
   0.750   0.4686   0.00866   0.00182  -0.0881   0.6234   0.3506
   1.000   0.4960   0.00867   0.00186  -0.0880   0.6178   0.3595
   1.250   0.5231   0.00869   0.00192  -0.0879   0.6133   0.3728
   1.500   0.5503   0.00870   0.00199  -0.0877   0.6087   0.3863
   1.750   0.5774   0.00868   0.00204  -0.0876   0.6035   0.3978
   2.000   0.6043   0.00868   0.00211  -0.0875   0.5988   0.4169
   2.250   0.6307   0.00858   0.00222  -0.0873   0.5944   0.4670
   2.500   0.6776   0.00743   0.00240  -0.0916   0.5892   1.0000
   2.750   0.7044   0.00754   0.00249  -0.0914   0.5850   1.0000
   3.000   0.7311   0.00767   0.00261  -0.0911   0.5805   1.0000
   3.250   0.7572   0.00772   0.00268  -0.0907   0.5718   1.0000
   3.500   0.7827   0.00778   0.00273  -0.0902   0.5600   1.0000
   3.750   0.8080   0.00784   0.00279  -0.0896   0.5459   1.0000
   4.000   0.8334   0.00792   0.00288  -0.0890   0.5321   1.0000
   4.250   0.8583   0.00802   0.00296  -0.0884   0.5138   1.0000
   4.500   0.8830   0.00816   0.00307  -0.0877   0.4901   1.0000
   4.750   0.9029   0.00859   0.00322  -0.0862   0.4129   1.0000
   5.000   0.9007   0.01113   0.00438  -0.0817   0.1626   1.0000
   5.250   0.9081   0.01297   0.00560  -0.0785   0.0349   1.0000
   5.500   0.9295   0.01350   0.00618  -0.0773   0.0286   1.0000
   5.750   0.9480   0.01428   0.00700  -0.0756   0.0241   1.0000
   6.000   0.9684   0.01484   0.00762  -0.0743   0.0221   1.0000
   6.250   0.9879   0.01546   0.00830  -0.0729   0.0205   1.0000
   6.500   1.0062   0.01614   0.00904  -0.0713   0.0191   1.0000
   6.750   1.0223   0.01695   0.00990  -0.0694   0.0181   1.0000
   7.000   1.0307   0.01832   0.01134  -0.0663   0.0170   1.0000
   7.250   1.0402   0.01967   0.01278  -0.0633   0.0162   1.0000
   7.500   1.0583   0.02026   0.01342  -0.0618   0.0154   1.0000
   7.750   1.0721   0.02125   0.01448  -0.0595   0.0148   1.0000
   8.000   1.0860   0.02240   0.01570  -0.0574   0.0144   1.0000
   8.250   1.1022   0.02357   0.01694  -0.0556   0.0138   1.0000
   8.500   1.1222   0.02506   0.01849  -0.0545   0.0135   1.0000
   8.750   1.1457   0.02670   0.02022  -0.0540   0.0131   1.0000
   9.000   1.1787   0.02998   0.02373  -0.0547   0.0133   1.0000
  15.250   0.7779   0.16310   0.16126  -0.0727   0.0178   1.0000
  15.500   0.7814   0.16558   0.16376  -0.0739   0.0172   1.0000
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