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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 500,000
Max Cl/Cd: 94.94 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe143-il-500000.txt
Download as CSV file: xf-goe143-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4211   0.09809   0.09585  -0.0053   1.0000   0.0250
  -8.250  -0.4216   0.09405   0.09185  -0.0115   1.0000   0.0262
  -8.000  -0.4192   0.09005   0.08788  -0.0156   1.0000   0.0263
  -7.750  -0.4098   0.08559   0.08344  -0.0205   1.0000   0.0264
  -7.500  -0.4032   0.07958   0.07744  -0.0258   1.0000   0.0266
  -7.250  -0.3954   0.07671   0.07458  -0.0246   1.0000   0.0270
  -7.000  -0.3835   0.07426   0.07213  -0.0251   1.0000   0.0275
  -6.750  -0.3710   0.07147   0.06935  -0.0270   1.0000   0.0281
  -6.500  -0.3586   0.06854   0.06642  -0.0294   1.0000   0.0294
  -6.250  -0.3337   0.06234   0.06011  -0.0406   1.0000   0.0326
  -6.000  -0.3217   0.05800   0.05570  -0.0430   1.0000   0.0327
  -5.750  -0.2974   0.04982   0.04740  -0.0502   0.9969   0.0335
  -5.500  -0.2678   0.04783   0.04539  -0.0529   0.9942   0.0343
  -5.250  -0.2355   0.04559   0.04310  -0.0563   0.9902   0.0362
  -5.000  -0.1801   0.04012   0.03714  -0.0647   0.9862   0.0407
  -4.500  -0.1185   0.03123   0.02801  -0.0724   0.9757   0.0434
  -4.250  -0.0844   0.02937   0.02603  -0.0748   0.9699   0.0456
  -4.000  -0.0474   0.02883   0.02510  -0.0754   0.9590   0.0508
  -3.750  -0.0206   0.02279   0.01860  -0.0776   0.9476   0.0525
  -3.500   0.0052   0.02143   0.01721  -0.0776   0.9342   0.0536
  -3.250   0.0307   0.02029   0.01596  -0.0773   0.9194   0.0550
  -3.000   0.0599   0.01699   0.01209  -0.0767   0.9048   0.0491
  -2.750   0.0866   0.01512   0.00989  -0.0763   0.8891   0.0485
  -2.500   0.1134   0.01377   0.00827  -0.0757   0.8733   0.0485
  -2.250   0.1403   0.01279   0.00707  -0.0752   0.8576   0.0488
  -2.000   0.1675   0.01214   0.00622  -0.0747   0.8422   0.0496
  -1.750   0.1948   0.01202   0.00597  -0.0742   0.8267   0.0507
  -1.500   0.2221   0.01096   0.00473  -0.0739   0.8117   0.0519
  -1.250   0.2493   0.01022   0.00390  -0.0736   0.7966   0.0532
  -1.000   0.2767   0.00986   0.00348  -0.0733   0.7804   0.0547
  -0.750   0.3043   0.00962   0.00318  -0.0730   0.7629   0.0565
  -0.500   0.3318   0.00942   0.00291  -0.0727   0.7442   0.0586
  -0.250   0.3595   0.00928   0.00271  -0.0725   0.7217   0.0612
   0.000   0.3870   0.00919   0.00251  -0.0722   0.6958   0.0629
   0.250   0.4143   0.00895   0.00214  -0.0719   0.6639   0.0661
   0.500   0.4414   0.00896   0.00201  -0.0716   0.6261   0.0699
   0.750   0.4685   0.00905   0.00194  -0.0714   0.5874   0.0743
   1.000   0.4958   0.00911   0.00187  -0.0712   0.5539   0.0806
   1.250   0.5232   0.00923   0.00187  -0.0710   0.5231   0.0895
   1.500   0.5508   0.00924   0.00184  -0.0709   0.4971   0.1118
   1.750   0.5730   0.00725   0.00196  -0.0702   0.4782   1.0000
   2.000   0.6006   0.00746   0.00200  -0.0700   0.4589   1.0000
   2.250   0.6283   0.00764   0.00207  -0.0699   0.4410   1.0000
   2.500   0.6559   0.00783   0.00215  -0.0698   0.4244   1.0000
   2.750   0.6835   0.00801   0.00224  -0.0697   0.4107   1.0000
   3.000   0.7111   0.00819   0.00234  -0.0696   0.3980   1.0000
   3.250   0.7388   0.00835   0.00245  -0.0695   0.3855   1.0000
   3.500   0.7664   0.00852   0.00257  -0.0694   0.3733   1.0000
   3.750   0.7940   0.00869   0.00270  -0.0693   0.3610   1.0000
   4.000   0.8214   0.00887   0.00284  -0.0692   0.3483   1.0000
   4.250   0.8487   0.00907   0.00299  -0.0690   0.3345   1.0000
   4.500   0.8759   0.00928   0.00314  -0.0689   0.3189   1.0000
   4.750   0.9029   0.00951   0.00332  -0.0688   0.3005   1.0000
   5.000   0.9295   0.00980   0.00352  -0.0686   0.2762   1.0000
   5.250   0.9548   0.01029   0.00377  -0.0683   0.2307   1.0000
   5.500   0.9787   0.01104   0.00418  -0.0679   0.1726   1.0000
   5.750   1.0035   0.01162   0.00461  -0.0676   0.1446   1.0000
   6.000   1.0291   0.01205   0.00497  -0.0673   0.1323   1.0000
   6.250   1.0545   0.01248   0.00535  -0.0670   0.1233   1.0000
   6.500   1.0805   0.01280   0.00568  -0.0667   0.1164   1.0000
   6.750   1.1059   0.01320   0.00606  -0.0664   0.1097   1.0000
   7.000   1.1319   0.01348   0.00636  -0.0662   0.1035   1.0000
   7.250   1.1573   0.01383   0.00669  -0.0659   0.0936   1.0000
   7.500   1.1811   0.01443   0.00708  -0.0654   0.0615   1.0000
   7.750   1.2001   0.01580   0.00825  -0.0643   0.0273   1.0000
   8.000   1.2238   0.01639   0.00895  -0.0636   0.0250   1.0000
   8.250   1.2459   0.01718   0.00982  -0.0628   0.0226   1.0000
   8.500   1.2658   0.01826   0.01103  -0.0617   0.0206   1.0000
   8.750   1.2879   0.01896   0.01181  -0.0609   0.0197   1.0000
   9.000   1.3085   0.01979   0.01273  -0.0600   0.0186   1.0000
   9.250   1.3279   0.02073   0.01375  -0.0589   0.0177   1.0000
   9.500   1.3452   0.02183   0.01491  -0.0576   0.0169   1.0000
   9.750   1.3551   0.02365   0.01685  -0.0554   0.0159   1.0000
  10.000   1.3703   0.02481   0.01811  -0.0539   0.0154   1.0000
  10.250   1.3862   0.02580   0.01920  -0.0524   0.0149   1.0000
  10.500   1.3993   0.02701   0.02050  -0.0506   0.0144   1.0000
  10.750   1.4102   0.02830   0.02189  -0.0487   0.0140   1.0000
  11.000   1.4173   0.02964   0.02331  -0.0462   0.0136   1.0000
  11.250   1.4226   0.03107   0.02484  -0.0436   0.0133   1.0000
  11.500   1.4269   0.03267   0.02653  -0.0413   0.0130   1.0000
  11.750   1.4301   0.03450   0.02844  -0.0393   0.0127   1.0000
  12.000   1.4321   0.03659   0.03061  -0.0375   0.0125   1.0000
  12.250   1.4326   0.03905   0.03313  -0.0359   0.0122   1.0000
  12.500   1.4318   0.04223   0.03638  -0.0339   0.0119   1.0000
  12.750   1.4323   0.04495   0.03925  -0.0327   0.0117   1.0000
  13.000   1.4327   0.04738   0.04185  -0.0323   0.0115   1.0000
  13.250   1.4324   0.05015   0.04478  -0.0321   0.0113   1.0000
  13.500   1.4308   0.05325   0.04804  -0.0321   0.0111   1.0000
  13.750   1.4277   0.05670   0.05166  -0.0323   0.0110   1.0000
  14.000   1.4231   0.06049   0.05561  -0.0327   0.0108   1.0000
  14.250   1.4169   0.06460   0.05988  -0.0335   0.0108   1.0000
  14.500   1.4092   0.06907   0.06451  -0.0346   0.0107   1.0000
  14.750   1.3999   0.07389   0.06950  -0.0361   0.0106   1.0000
  15.000   1.3891   0.07910   0.07488  -0.0380   0.0106   1.0000
  15.250   1.3772   0.08470   0.08064  -0.0403   0.0105   1.0000
  15.500   1.3642   0.09065   0.08676  -0.0429   0.0105   1.0000
  15.750   1.3501   0.09704   0.09330  -0.0459   0.0105   1.0000
  16.000   1.3353   0.10383   0.10026  -0.0494   0.0105   1.0000
  16.250   1.3194   0.11101   0.10760  -0.0532   0.0106   1.0000
  16.500   1.3032   0.11856   0.11531  -0.0575   0.0106   1.0000
  16.750   1.2863   0.12660   0.12351  -0.0622   0.0107   1.0000
  17.000   1.2693   0.13500   0.13205  -0.0673   0.0107   1.0000
  17.250   1.2516   0.14389   0.14109  -0.0728   0.0109   1.0000
  17.500   1.2342   0.15319   0.15053  -0.0788   0.0110   1.0000
  17.750   1.2162   0.16321   0.16068  -0.0853   0.0111   1.0000
  18.000   1.1976   0.17397   0.17156  -0.0924   0.0113   1.0000
  18.250   1.1785   0.18530   0.18298  -0.0996   0.0115   1.0000
  18.500   1.1729   0.19193   0.18965  -0.1032   0.0119   1.0000
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