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GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il)
Reynolds number: 500,000
Max Cl/Cd: 96.13 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe134-il-500000.txt
Download as CSV file: xf-goe134-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3827   0.08663   0.08446  -0.0253   1.0000   0.0183
  -7.500  -0.3883   0.08415   0.08202  -0.0249   1.0000   0.0184
  -7.250  -0.3904   0.08126   0.07917  -0.0258   1.0000   0.0187
  -7.000  -0.3930   0.07838   0.07631  -0.0264   1.0000   0.0190
  -6.750  -0.3946   0.07539   0.07333  -0.0271   1.0000   0.0193
  -6.500  -0.3942   0.07221   0.07015  -0.0279   1.0000   0.0198
  -6.250  -0.3564   0.06439   0.06216  -0.0409   0.9971   0.0214
  -6.000  -0.3154   0.05645   0.05389  -0.0509   0.9943   0.0216
  -5.750  -0.2963   0.05096   0.04838  -0.0543   0.9912   0.0220
  -5.500  -0.2691   0.04784   0.04522  -0.0575   0.9883   0.0224
  -5.250  -0.2371   0.04446   0.04173  -0.0614   0.9858   0.0231
  -5.000  -0.2007   0.04058   0.03766  -0.0658   0.9838   0.0245
  -4.750  -0.1558   0.03638   0.03272  -0.0686   0.9796   0.0268
  -4.500  -0.1281   0.03103   0.02737  -0.0720   0.9760   0.0276
  -4.250  -0.0946   0.02884   0.02510  -0.0746   0.9723   0.0284
  -4.000  -0.0640   0.02679   0.02288  -0.0759   0.9650   0.0299
  -3.750  -0.0268   0.02646   0.02200  -0.0759   0.9571   0.0331
  -3.500  -0.0036   0.02205   0.01745  -0.0766   0.9451   0.0346
  -3.250   0.0222   0.02071   0.01604  -0.0764   0.9311   0.0359
  -3.000   0.0483   0.01961   0.01475  -0.0759   0.9148   0.0382
  -2.750   0.0757   0.01841   0.01308  -0.0751   0.8956   0.0426
  -2.500   0.1007   0.01709   0.01173  -0.0747   0.8703   0.0443
  -2.250   0.1266   0.01649   0.01094  -0.0742   0.8397   0.0480
  -1.250  -0.0539   0.01759   0.01520  -0.0298   0.8725   0.0382
  -0.500   0.3212   0.01175   0.00479  -0.0720   0.6908   0.0493
  -0.250   0.3496   0.01106   0.00398  -0.0717   0.6772   0.0438
   0.000   0.3779   0.01084   0.00368  -0.0716   0.6632   0.0427
   0.250   0.4061   0.01061   0.00341  -0.0716   0.6489   0.0423
   0.500   0.4343   0.01040   0.00314  -0.0717   0.6341   0.0422
   0.750   0.4625   0.01015   0.00285  -0.0718   0.6194   0.0433
   1.000   0.4909   0.01003   0.00267  -0.0718   0.6043   0.0435
   1.250   0.5192   0.00996   0.00253  -0.0719   0.5884   0.0438
   1.500   0.5474   0.00992   0.00243  -0.0720   0.5720   0.0448
   1.750   0.5755   0.00993   0.00236  -0.0720   0.5557   0.0465
   2.000   0.6036   0.00998   0.00233  -0.0721   0.5401   0.0489
   2.250   0.6316   0.01004   0.00233  -0.0721   0.5246   0.0532
   2.500   0.6523   0.00789   0.00245  -0.0710   0.5108   1.0000
   2.750   0.6802   0.00805   0.00250  -0.0710   0.4953   1.0000
   3.000   0.7079   0.00823   0.00257  -0.0710   0.4794   1.0000
   3.250   0.7355   0.00841   0.00266  -0.0711   0.4637   1.0000
   3.500   0.7632   0.00860   0.00276  -0.0711   0.4485   1.0000
   3.750   0.7907   0.00879   0.00289  -0.0711   0.4337   1.0000
   4.000   0.8182   0.00899   0.00302  -0.0712   0.4194   1.0000
   4.250   0.8456   0.00920   0.00316  -0.0712   0.4048   1.0000
   4.500   0.8728   0.00942   0.00331  -0.0712   0.3894   1.0000
   4.750   0.9000   0.00965   0.00349  -0.0712   0.3753   1.0000
   5.000   0.9272   0.00987   0.00367  -0.0712   0.3632   1.0000
   5.250   0.9542   0.01010   0.00386  -0.0712   0.3507   1.0000
   5.500   0.9810   0.01034   0.00406  -0.0712   0.3365   1.0000
   5.750   1.0078   0.01060   0.00428  -0.0712   0.3245   1.0000
   6.000   1.0345   0.01085   0.00450  -0.0711   0.3146   1.0000
   6.250   1.0614   0.01106   0.00474  -0.0711   0.3047   1.0000
   6.500   1.0879   0.01132   0.00497  -0.0711   0.2933   1.0000
   6.750   1.1141   0.01159   0.00522  -0.0710   0.2818   1.0000
   7.000   1.1402   0.01187   0.00547  -0.0709   0.2695   1.0000
   7.250   1.1663   0.01214   0.00574  -0.0708   0.2561   1.0000
   7.500   1.1921   0.01243   0.00602  -0.0706   0.2427   1.0000
   7.750   1.2176   0.01275   0.00633  -0.0704   0.2285   1.0000
   8.000   1.2424   0.01314   0.00667  -0.0702   0.2115   1.0000
   8.250   1.2666   0.01359   0.00706  -0.0698   0.1873   1.0000
   8.500   1.2877   0.01438   0.00761  -0.0691   0.1455   1.0000
   8.750   1.3076   0.01527   0.00832  -0.0682   0.1140   1.0000
   9.000   1.3277   0.01611   0.00903  -0.0673   0.0911   1.0000
   9.250   1.3456   0.01713   0.00987  -0.0661   0.0604   1.0000
   9.500   1.3591   0.01855   0.01101  -0.0642   0.0268   1.0000
   9.750   1.3765   0.01950   0.01196  -0.0628   0.0208   1.0000
  10.000   1.3931   0.02046   0.01299  -0.0612   0.0185   1.0000
  10.250   1.4100   0.02132   0.01397  -0.0597   0.0174   1.0000
  10.500   1.4253   0.02222   0.01498  -0.0580   0.0166   1.0000
  10.750   1.4380   0.02324   0.01610  -0.0559   0.0157   1.0000
  11.000   1.4465   0.02442   0.01737  -0.0533   0.0150   1.0000
  11.250   1.4459   0.02590   0.01896  -0.0492   0.0143   1.0000
  11.500   1.4402   0.02783   0.02103  -0.0449   0.0138   1.0000
  11.750   1.4462   0.02914   0.02246  -0.0426   0.0136   1.0000
  12.000   1.4495   0.03076   0.02420  -0.0403   0.0133   1.0000
  12.250   1.4511   0.03266   0.02621  -0.0382   0.0130   1.0000
  12.500   1.4514   0.03483   0.02850  -0.0364   0.0127   1.0000
  12.750   1.4509   0.03728   0.03108  -0.0351   0.0125   1.0000
  13.000   1.4497   0.04003   0.03394  -0.0342   0.0122   1.0000
  13.250   1.4478   0.04304   0.03707  -0.0337   0.0120   1.0000
  13.500   1.4453   0.04629   0.04044  -0.0335   0.0118   1.0000
  13.750   1.4419   0.04973   0.04400  -0.0335   0.0116   1.0000
  14.000   1.4377   0.05333   0.04770  -0.0337   0.0114   1.0000
  14.250   1.4329   0.05706   0.05154  -0.0339   0.0113   1.0000
  14.500   1.4271   0.06091   0.05547  -0.0342   0.0111   1.0000
  14.750   1.4207   0.06483   0.05948  -0.0345   0.0109   1.0000
  15.000   1.4138   0.06875   0.06348  -0.0344   0.0107   1.0000
  15.250   1.4055   0.07248   0.06729  -0.0333   0.0105   1.0000
  15.500   1.4007   0.07662   0.07158  -0.0343   0.0103   1.0000
  15.750   1.3962   0.08096   0.07606  -0.0358   0.0102   1.0000
  16.000   1.3909   0.08537   0.08062  -0.0372   0.0101   1.0000
  16.250   1.3853   0.08989   0.08528  -0.0386   0.0100   1.0000
  16.500   1.3792   0.09459   0.09012  -0.0402   0.0099   1.0000
  16.750   1.3725   0.09947   0.09514  -0.0419   0.0099   1.0000
  17.000   1.3648   0.10456   0.10038  -0.0438   0.0098   1.0000
  17.250   1.3568   0.10984   0.10580  -0.0459   0.0097   1.0000
  17.500   1.3482   0.11537   0.11147  -0.0484   0.0097   1.0000
  17.750   1.3389   0.12116   0.11741  -0.0511   0.0096   1.0000
  18.000   1.3291   0.12715   0.12354  -0.0541   0.0096   1.0000
  18.250   1.3186   0.13344   0.12998  -0.0574   0.0095   1.0000
  18.500   1.3077   0.14002   0.13672  -0.0610   0.0095   1.0000
  18.750   1.2963   0.14694   0.14378  -0.0651   0.0095   1.0000
  19.000   1.2841   0.15429   0.15128  -0.0696   0.0095   1.0000
  19.250   1.2713   0.16201   0.15915  -0.0744   0.0096   1.0000
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