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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.86 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe143-il-1000000.txt
Download as CSV file: xf-goe143-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 143 (MVA H.20) 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3735   0.13092   0.12934  -0.0031   1.0000   0.0134
 -11.750  -0.3716   0.12739   0.12582  -0.0041   1.0000   0.0135
  -8.500  -0.4414   0.09213   0.09056  -0.0084   1.0000   0.0170
  -8.250  -0.4340   0.08968   0.08812  -0.0083   1.0000   0.0163
  -8.000  -0.4313   0.08585   0.08431  -0.0105   1.0000   0.0158
  -7.750  -0.4285   0.08108   0.07955  -0.0146   1.0000   0.0161
  -7.500  -0.4210   0.07501   0.07349  -0.0214   1.0000   0.0162
  -7.250  -0.4133   0.06584   0.06429  -0.0322   1.0000   0.0165
  -7.000  -0.4058   0.05584   0.05421  -0.0425   1.0000   0.0175
  -6.750  -0.3853   0.05422   0.05257  -0.0441   0.9993   0.0179
  -6.500  -0.3432   0.03343   0.03117  -0.0650   0.9946   0.0216
  -6.250  -0.3107   0.03256   0.03025  -0.0672   0.9916   0.0221
  -6.000  -0.2787   0.03249   0.03017  -0.0686   0.9871   0.0226
  -5.750  -0.2499   0.01600   0.01229  -0.0756   0.9815   0.0276
  -5.500  -0.2193   0.01623   0.01254  -0.0760   0.9733   0.0281
  -5.250  -0.1902   0.01665   0.01300  -0.0761   0.9633   0.0287
  -5.000  -0.1634   0.01674   0.01308  -0.0757   0.9511   0.0294
  -4.750  -0.1383   0.01492   0.01095  -0.0753   0.9369   0.0306
  -4.500  -0.1128   0.01379   0.00958  -0.0748   0.9205   0.0317
  -4.250  -0.0868   0.01331   0.00893  -0.0742   0.9015   0.0323
  -4.000  -0.0604   0.01309   0.00856  -0.0736   0.8820   0.0327
  -3.750  -0.0345   0.01080   0.00589  -0.0735   0.8648   0.0342
  -3.500  -0.0073   0.01062   0.00563  -0.0732   0.8486   0.0350
  -3.250   0.0203   0.01044   0.00536  -0.0730   0.8336   0.0358
  -3.000   0.0480   0.01006   0.00487  -0.0728   0.8201   0.0364
  -2.750   0.0759   0.00970   0.00441  -0.0726   0.8072   0.0371
  -2.500   0.1040   0.00937   0.00400  -0.0725   0.7942   0.0380
  -2.250   0.1321   0.00908   0.00363  -0.0724   0.7811   0.0388
  -2.000   0.1602   0.00886   0.00334  -0.0723   0.7674   0.0397
  -1.750   0.1884   0.00879   0.00321  -0.0721   0.7517   0.0404
  -1.500   0.2164   0.00842   0.00274  -0.0720   0.7345   0.0414
  -1.250   0.2444   0.00799   0.00222  -0.0720   0.7151   0.0430
  -1.000   0.2725   0.00786   0.00201  -0.0719   0.6910   0.0443
  -0.750   0.3004   0.00781   0.00187  -0.0718   0.6631   0.0458
  -0.500   0.3283   0.00782   0.00175  -0.0717   0.6307   0.0474
  -0.250   0.3560   0.00788   0.00165  -0.0715   0.5928   0.0490
   0.000   0.3837   0.00801   0.00162  -0.0714   0.5517   0.0504
   0.250   0.4115   0.00804   0.00150  -0.0714   0.5191   0.0523
   0.500   0.4397   0.00802   0.00137  -0.0714   0.4921   0.0561
   0.750   0.4677   0.00808   0.00135  -0.0713   0.4689   0.0593
   1.000   0.4958   0.00814   0.00134  -0.0713   0.4498   0.0621
   1.250   0.5240   0.00817   0.00132  -0.0713   0.4336   0.0671
   1.500   0.5521   0.00822   0.00135  -0.0713   0.4176   0.0786
   1.750   0.5802   0.00825   0.00140  -0.0713   0.4021   0.1058
   2.000   0.6084   0.00796   0.00148  -0.0716   0.3880   0.2930
   2.250   0.6313   0.00645   0.00163  -0.0708   0.3770   1.0000
   2.500   0.6594   0.00658   0.00169  -0.0708   0.3656   1.0000
   3.000   0.7154   0.00686   0.00184  -0.0707   0.3417   1.0000
   3.250   0.7433   0.00701   0.00192  -0.0706   0.3286   1.0000
   3.500   0.7711   0.00717   0.00202  -0.0706   0.3149   1.0000
   3.750   0.7988   0.00734   0.00212  -0.0705   0.3002   1.0000
   4.000   0.8264   0.00754   0.00225  -0.0705   0.2844   1.0000
   4.250   0.8536   0.00777   0.00239  -0.0704   0.2654   1.0000
   4.500   0.8805   0.00807   0.00256  -0.0702   0.2380   1.0000
   4.750   0.9055   0.00872   0.00288  -0.0700   0.1782   1.0000
   5.000   0.9307   0.00931   0.00323  -0.0697   0.1360   1.0000
   5.250   0.9572   0.00964   0.00348  -0.0695   0.1215   1.0000
   5.500   0.9838   0.00994   0.00373  -0.0693   0.1128   1.0000
   5.750   1.0108   0.01017   0.00395  -0.0692   0.1074   1.0000
   6.000   1.0374   0.01044   0.00419  -0.0690   0.1020   1.0000
   6.250   1.0640   0.01069   0.00443  -0.0688   0.0965   1.0000
   6.500   1.0908   0.01091   0.00465  -0.0687   0.0918   1.0000
   6.750   1.1169   0.01122   0.00491  -0.0685   0.0838   1.0000
   7.000   1.1424   0.01162   0.00520  -0.0682   0.0657   1.0000
   7.250   1.1636   0.01273   0.00608  -0.0674   0.0241   1.0000
   7.500   1.1883   0.01324   0.00663  -0.0669   0.0202   1.0000
   7.750   1.2134   0.01366   0.00708  -0.0665   0.0183   1.0000
   8.000   1.2373   0.01425   0.00771  -0.0659   0.0163   1.0000
   8.250   1.2614   0.01478   0.00830  -0.0654   0.0153   1.0000
   8.500   1.2857   0.01523   0.00880  -0.0649   0.0145   1.0000
   8.750   1.3096   0.01573   0.00934  -0.0644   0.0136   1.0000
   9.000   1.3326   0.01632   0.00996  -0.0638   0.0127   1.0000
   9.250   1.3523   0.01735   0.01110  -0.0627   0.0117   1.0000
   9.500   1.3754   0.01785   0.01165  -0.0621   0.0114   1.0000
   9.750   1.3975   0.01845   0.01231  -0.0614   0.0109   1.0000
  10.000   1.4188   0.01911   0.01302  -0.0606   0.0104   1.0000
  10.250   1.4395   0.01980   0.01377  -0.0597   0.0100   1.0000
  10.500   1.4591   0.02055   0.01457  -0.0587   0.0096   1.0000
  10.750   1.4756   0.02158   0.01568  -0.0573   0.0092   1.0000
  11.000   1.4798   0.02372   0.01799  -0.0544   0.0087   1.0000
  11.250   1.4984   0.02435   0.01868  -0.0534   0.0086   1.0000
  11.500   1.5148   0.02513   0.01953  -0.0520   0.0084   1.0000
  11.750   1.5285   0.02604   0.02051  -0.0504   0.0081   1.0000
  12.000   1.5369   0.02707   0.02163  -0.0479   0.0079   1.0000
  12.250   1.5426   0.02826   0.02292  -0.0454   0.0077   1.0000
  12.500   1.5473   0.02964   0.02439  -0.0431   0.0075   1.0000
  12.750   1.5513   0.03121   0.02605  -0.0412   0.0073   1.0000
  13.000   1.5544   0.03301   0.02794  -0.0397   0.0072   1.0000
  13.250   1.5569   0.03506   0.03008  -0.0386   0.0070   1.0000
  13.500   1.5576   0.03750   0.03262  -0.0379   0.0069   1.0000
  13.750   1.5559   0.04039   0.03561  -0.0376   0.0068   1.0000
  14.000   1.5512   0.04388   0.03921  -0.0378   0.0067   1.0000
  14.250   1.5433   0.04802   0.04347  -0.0385   0.0066   1.0000
  14.500   1.5320   0.05289   0.04848  -0.0398   0.0065   1.0000
  14.750   1.5182   0.05829   0.05401  -0.0414   0.0065   1.0000
  15.000   1.5011   0.06428   0.06014  -0.0432   0.0064   1.0000
  15.250   1.4820   0.07054   0.06654  -0.0450   0.0063   1.0000
  15.500   1.4637   0.07674   0.07287  -0.0468   0.0063   1.0000
  15.750   1.4532   0.08216   0.07841  -0.0489   0.0063   1.0000
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