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GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il)
Reynolds number: 200,000
Max Cl/Cd: 71.72 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe134-il-200000-n5.txt
Download as CSV file: xf-goe134-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 134 (MVA H.12) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2854   0.11536   0.11192  -0.0271   1.0000   0.0217
 -10.250  -0.2869   0.11212   0.10870  -0.0286   1.0000   0.0217
 -10.000  -0.2871   0.10866   0.10526  -0.0297   1.0000   0.0218
  -9.750  -0.2865   0.10511   0.10171  -0.0307   1.0000   0.0218
  -9.500  -0.2860   0.10148   0.09811  -0.0316   1.0000   0.0218
  -9.250  -0.2858   0.09785   0.09450  -0.0325   1.0000   0.0218
  -9.000  -0.2863   0.09418   0.09087  -0.0332   1.0000   0.0218
  -8.750  -0.2790   0.09049   0.08720  -0.0317   1.0000   0.0221
  -8.500  -0.2750   0.08734   0.08408  -0.0310   1.0000   0.0225
  -8.250  -0.2747   0.08421   0.08099  -0.0307   1.0000   0.0228
  -8.000  -0.2765   0.08115   0.07796  -0.0305   1.0000   0.0231
  -7.750  -0.2796   0.07823   0.07509  -0.0300   1.0000   0.0236
  -7.500  -0.2852   0.07549   0.07241  -0.0292   1.0000   0.0243
  -7.250  -0.2950   0.07298   0.06996  -0.0280   1.0000   0.0250
  -7.000  -0.3768   0.07813   0.07484  -0.0367   1.0000   0.0218
  -6.750  -0.3759   0.07675   0.07354  -0.0317   1.0000   0.0225
  -6.500  -0.3729   0.07448   0.07130  -0.0310   1.0000   0.0234
  -6.250  -0.3349   0.06775   0.06438  -0.0440   0.9947   0.0269
  -6.000  -0.3022   0.06131   0.05770  -0.0521   0.9891   0.0271
  -5.750  -0.2705   0.05548   0.05161  -0.0580   0.9849   0.0271
  -5.500  -0.2402   0.05010   0.04591  -0.0623   0.9792   0.0272
  -5.250  -0.2200   0.04743   0.04345  -0.0644   0.9757   0.0288
  -5.000  -0.1787   0.04411   0.03953  -0.0685   0.9690   0.0342
  -4.750  -0.1460   0.03959   0.03464  -0.0717   0.9640   0.0344
  -4.500  -0.1226   0.03554   0.03063  -0.0736   0.9560   0.0357
  -4.250  -0.0836   0.03566   0.03022  -0.0755   0.9496   0.0434
  -3.750  -0.0235   0.02748   0.02127  -0.0773   0.9298   0.0342
  -3.500   0.0047   0.02476   0.01857  -0.0790   0.9191   0.0370
  -3.250   0.0368   0.02242   0.01562  -0.0791   0.9056   0.0353
  -3.000   0.0674   0.02102   0.01388  -0.0792   0.8898   0.0349
  -2.750   0.0959   0.01953   0.01218  -0.0794   0.8701   0.0357
  -2.500   0.1242   0.01854   0.01109  -0.0794   0.8472   0.0372
  -2.250   0.1526   0.01753   0.00979  -0.0791   0.8213   0.0371
  -2.000   0.1805   0.01668   0.00864  -0.0786   0.7956   0.0369
  -1.750   0.2079   0.01599   0.00770  -0.0781   0.7724   0.0370
  -1.500   0.2352   0.01543   0.00693  -0.0777   0.7522   0.0372
  -1.250   0.2624   0.01497   0.00632  -0.0774   0.7343   0.0380
  -1.000   0.2897   0.01461   0.00585  -0.0772   0.7182   0.0394
  -0.750   0.3171   0.01424   0.00537  -0.0769   0.7030   0.0399
  -0.500   0.3445   0.01390   0.00495  -0.0767   0.6884   0.0399
  -0.250   0.3720   0.01361   0.00459  -0.0766   0.6739   0.0401
   0.000   0.3996   0.01337   0.00429  -0.0765   0.6595   0.0404
   0.250   0.4272   0.01317   0.00404  -0.0765   0.6447   0.0409
   0.500   0.4549   0.01303   0.00383  -0.0764   0.6299   0.0415
   0.750   0.4826   0.01295   0.00365  -0.0764   0.6143   0.0422
   1.000   0.5103   0.01291   0.00352  -0.0763   0.5989   0.0433
   1.250   0.5380   0.01285   0.00338  -0.0763   0.5833   0.0466
   1.500   0.5656   0.01287   0.00331  -0.0762   0.5677   0.0486
   1.750   0.5931   0.01292   0.00328  -0.0761   0.5523   0.0508
   2.250   0.6412   0.01083   0.00336  -0.0746   0.5234   1.0000
   2.500   0.6684   0.01102   0.00342  -0.0745   0.5093   1.0000
   2.750   0.6956   0.01122   0.00350  -0.0744   0.4948   1.0000
   3.000   0.7226   0.01143   0.00359  -0.0743   0.4803   1.0000
   3.250   0.7496   0.01164   0.00372  -0.0742   0.4659   1.0000
   3.750   0.8034   0.01208   0.00401  -0.0740   0.4392   1.0000
   4.000   0.8303   0.01231   0.00420  -0.0739   0.4264   1.0000
   4.250   0.8570   0.01256   0.00439  -0.0738   0.4137   1.0000
   4.500   0.8835   0.01281   0.00460  -0.0737   0.4015   1.0000
   4.750   0.9099   0.01309   0.00484  -0.0736   0.3903   1.0000
   5.000   0.9364   0.01335   0.00509  -0.0735   0.3798   1.0000
   5.250   0.9627   0.01363   0.00536  -0.0733   0.3694   1.0000
   5.500   0.9887   0.01393   0.00565  -0.0731   0.3583   1.0000
   5.750   1.0142   0.01426   0.00594  -0.0729   0.3467   1.0000
   6.000   1.0400   0.01456   0.00625  -0.0727   0.3350   1.0000
   6.250   1.0655   0.01488   0.00658  -0.0725   0.3230   1.0000
   6.500   1.0908   0.01521   0.00693  -0.0722   0.3115   1.0000
   6.750   1.1156   0.01557   0.00729  -0.0719   0.3001   1.0000
   7.000   1.1404   0.01592   0.00766  -0.0716   0.2886   1.0000
   7.250   1.1655   0.01625   0.00808  -0.0713   0.2785   1.0000
   7.500   1.1899   0.01663   0.00849  -0.0709   0.2667   1.0000
   7.750   1.2135   0.01703   0.00891  -0.0704   0.2509   1.0000
   8.000   1.2366   0.01748   0.00935  -0.0699   0.2328   1.0000
   8.250   1.2587   0.01800   0.00986  -0.0693   0.2135   1.0000
   8.500   1.2799   0.01860   0.01041  -0.0685   0.1866   1.0000
   8.750   1.2988   0.01942   0.01108  -0.0675   0.1520   1.0000
   9.000   1.3157   0.02041   0.01192  -0.0662   0.1233   1.0000
   9.250   1.3319   0.02145   0.01288  -0.0648   0.1021   1.0000
   9.500   1.3485   0.02239   0.01380  -0.0634   0.0831   1.0000
   9.750   1.3616   0.02358   0.01488  -0.0616   0.0607   1.0000
  10.000   1.3717   0.02493   0.01612  -0.0594   0.0362   1.0000
  10.250   1.3759   0.02660   0.01765  -0.0564   0.0214   1.0000
  10.500   1.3826   0.02786   0.01899  -0.0535   0.0188   1.0000
  10.750   1.3866   0.02921   0.02048  -0.0504   0.0172   1.0000
  11.000   1.3893   0.03077   0.02220  -0.0474   0.0160   1.0000
  11.250   1.3940   0.03227   0.02386  -0.0450   0.0154   1.0000
  11.500   1.3975   0.03396   0.02573  -0.0428   0.0148   1.0000
  11.750   1.3994   0.03590   0.02783  -0.0408   0.0141   1.0000
  12.000   1.3995   0.03812   0.03022  -0.0391   0.0135   1.0000
  12.250   1.3979   0.04070   0.03296  -0.0378   0.0129   1.0000
  12.500   1.3943   0.04370   0.03613  -0.0370   0.0124   1.0000
  12.750   1.3886   0.04719   0.03979  -0.0367   0.0121   1.0000
  13.000   1.3807   0.05116   0.04391  -0.0368   0.0118   1.0000
  13.250   1.3708   0.05558   0.04848  -0.0372   0.0116   1.0000
  13.500   1.3599   0.06024   0.05330  -0.0379   0.0114   1.0000
  13.750   1.3520   0.06465   0.05784  -0.0387   0.0113   1.0000
  14.000   1.3455   0.06894   0.06228  -0.0395   0.0112   1.0000
  14.250   1.3386   0.07336   0.06684  -0.0405   0.0110   1.0000
  14.500   1.3318   0.07786   0.07148  -0.0415   0.0109   1.0000
  14.750   1.3250   0.08242   0.07618  -0.0427   0.0108   1.0000
  15.000   1.3185   0.08698   0.08087  -0.0439   0.0106   1.0000
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