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GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il)
Reynolds number: 200,000
Max Cl/Cd: 70.12 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe143-il-200000-n5.txt
Download as CSV file: xf-goe143-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4110   0.09288   0.08940  -0.0114   1.0000   0.0217
  -8.000  -0.4099   0.08876   0.08533  -0.0142   1.0000   0.0225
  -7.750  -0.4094   0.08430   0.08092  -0.0178   1.0000   0.0228
  -7.500  -0.4045   0.07866   0.07530  -0.0241   1.0000   0.0231
  -7.250  -0.3953   0.07429   0.07095  -0.0283   1.0000   0.0236
  -7.000  -0.3825   0.07247   0.06913  -0.0287   1.0000   0.0242
  -6.750  -0.3697   0.07007   0.06674  -0.0304   1.0000   0.0253
  -6.500  -0.3575   0.06653   0.06319  -0.0336   1.0000   0.0268
  -6.250  -0.3450   0.06160   0.05822  -0.0382   1.0000   0.0279
  -6.000  -0.3299   0.05497   0.05147  -0.0442   1.0000   0.0288
  -5.750  -0.3077   0.04977   0.04611  -0.0490   0.9983   0.0305
  -5.500  -0.2733   0.04831   0.04460  -0.0524   0.9927   0.0325
  -5.250  -0.2301   0.04238   0.03837  -0.0604   0.9860   0.0343
  -5.000  -0.1839   0.03322   0.02843  -0.0687   0.9780   0.0378
  -4.750  -0.1503   0.03060   0.02561  -0.0717   0.9694   0.0387
  -4.500  -0.1165   0.02907   0.02394  -0.0740   0.9622   0.0398
  -4.250  -0.0849   0.02752   0.02222  -0.0755   0.9520   0.0418
  -4.000  -0.0520   0.02483   0.01915  -0.0773   0.9420   0.0429
  -3.750  -0.0190   0.02236   0.01628  -0.0786   0.9319   0.0437
  -3.500   0.0122   0.02037   0.01391  -0.0794   0.9197   0.0446
  -3.250   0.0423   0.01895   0.01215  -0.0797   0.9061   0.0461
  -3.000   0.0719   0.01799   0.01087  -0.0798   0.8917   0.0472
  -2.750   0.1006   0.01702   0.00964  -0.0797   0.8769   0.0476
  -2.500   0.1284   0.01564   0.00803  -0.0796   0.8620   0.0485
  -2.250   0.1556   0.01485   0.00709  -0.0792   0.8465   0.0496
  -2.000   0.1827   0.01429   0.00642  -0.0787   0.8311   0.0506
  -1.750   0.2096   0.01383   0.00584  -0.0783   0.8152   0.0519
  -1.500   0.2366   0.01342   0.00533  -0.0778   0.7991   0.0532
  -1.250   0.2636   0.01310   0.00491  -0.0774   0.7823   0.0553
  -1.000   0.2907   0.01284   0.00456  -0.0769   0.7643   0.0579
  -0.750   0.3177   0.01256   0.00418  -0.0765   0.7450   0.0596
  -0.500   0.3446   0.01224   0.00378  -0.0760   0.7243   0.0610
  -0.250   0.3715   0.01194   0.00346  -0.0757   0.7009   0.0636
   0.000   0.3984   0.01181   0.00325  -0.0753   0.6757   0.0664
   0.250   0.4253   0.01175   0.00307  -0.0748   0.6492   0.0699
   0.500   0.4521   0.01173   0.00294  -0.0745   0.6223   0.0750
   0.750   0.4790   0.01175   0.00288  -0.0742   0.5961   0.0817
   1.000   0.5060   0.01178   0.00281  -0.0738   0.5716   0.0893
   1.250   0.5331   0.01182   0.00276  -0.0736   0.5486   0.1023
   1.500   0.5599   0.01183   0.00274  -0.0733   0.5248   0.1311
   2.000   0.6083   0.01023   0.00288  -0.0718   0.4782   1.0000
   2.250   0.6350   0.01049   0.00296  -0.0715   0.4564   1.0000
   2.500   0.6618   0.01075   0.00306  -0.0713   0.4378   1.0000
   2.750   0.6887   0.01099   0.00318  -0.0710   0.4199   1.0000
   3.000   0.7155   0.01123   0.00332  -0.0708   0.4023   1.0000
   3.250   0.7423   0.01147   0.00347  -0.0706   0.3858   1.0000
   3.500   0.7692   0.01170   0.00364  -0.0704   0.3716   1.0000
   3.750   0.7961   0.01194   0.00383  -0.0702   0.3591   1.0000
   4.000   0.8228   0.01218   0.00402  -0.0700   0.3463   1.0000
   4.250   0.8495   0.01243   0.00423  -0.0697   0.3326   1.0000
   4.750   0.9024   0.01296   0.00472  -0.0693   0.3020   1.0000
   5.000   0.9286   0.01326   0.00498  -0.0690   0.2838   1.0000
   5.250   0.9544   0.01361   0.00528  -0.0687   0.2615   1.0000
   5.500   0.9796   0.01403   0.00562  -0.0683   0.2344   1.0000
   5.750   1.0040   0.01456   0.00601  -0.0679   0.2033   1.0000
   6.000   1.0282   0.01515   0.00648  -0.0675   0.1768   1.0000
   6.500   1.0759   0.01635   0.00754  -0.0666   0.1440   1.0000
   7.000   1.1237   0.01745   0.00860  -0.0656   0.1223   1.0000
   7.250   1.1473   0.01800   0.00917  -0.0652   0.1137   1.0000
   7.500   1.1709   0.01853   0.00972  -0.0647   0.1051   1.0000
   7.750   1.1948   0.01900   0.01025  -0.0642   0.0963   1.0000
   8.000   1.2180   0.01956   0.01080  -0.0636   0.0819   1.0000
   8.250   1.2343   0.02102   0.01187  -0.0624   0.0328   1.0000
   8.500   1.2533   0.02211   0.01308  -0.0613   0.0266   1.0000
   8.750   1.2721   0.02318   0.01428  -0.0601   0.0231   1.0000
   9.000   1.2888   0.02447   0.01573  -0.0587   0.0203   1.0000
   9.250   1.3074   0.02543   0.01685  -0.0576   0.0191   1.0000
   9.500   1.3242   0.02652   0.01812  -0.0562   0.0179   1.0000
   9.750   1.3393   0.02771   0.01946  -0.0548   0.0167   1.0000
  10.000   1.3520   0.02903   0.02092  -0.0532   0.0156   1.0000
  10.250   1.3590   0.03073   0.02278  -0.0510   0.0146   1.0000
  10.500   1.3597   0.03261   0.02480  -0.0481   0.0141   1.0000
  10.750   1.3639   0.03416   0.02649  -0.0457   0.0137   1.0000
  11.000   1.3660   0.03598   0.02845  -0.0435   0.0134   1.0000
  11.250   1.3669   0.03805   0.03067  -0.0416   0.0131   1.0000
  11.500   1.3668   0.04041   0.03315  -0.0402   0.0128   1.0000
  11.750   1.3662   0.04300   0.03588  -0.0392   0.0125   1.0000
  12.000   1.3655   0.04578   0.03880  -0.0386   0.0121   1.0000
  12.250   1.3644   0.04876   0.04190  -0.0383   0.0118   1.0000
  12.500   1.3629   0.05194   0.04521  -0.0384   0.0115   1.0000
  12.750   1.3605   0.05536   0.04875  -0.0388   0.0112   1.0000
  13.000   1.3573   0.05902   0.05256  -0.0395   0.0109   1.0000
  13.250   1.3533   0.06291   0.05655  -0.0404   0.0106   1.0000
  13.500   1.3481   0.06701   0.06076  -0.0413   0.0104   1.0000
  13.750   1.3422   0.07125   0.06509  -0.0423   0.0102   1.0000
  14.000   1.3360   0.07547   0.06940  -0.0429   0.0100   1.0000
  14.250   1.3304   0.07976   0.07382  -0.0437   0.0099   1.0000
  14.500   1.3244   0.08434   0.07856  -0.0452   0.0098   1.0000
  14.750   1.3177   0.08914   0.08352  -0.0468   0.0098   1.0000
  15.000   1.3097   0.09433   0.08888  -0.0488   0.0097   1.0000
  15.250   1.3013   0.09973   0.09444  -0.0511   0.0096   1.0000
  15.500   1.2921   0.10543   0.10032  -0.0536   0.0095   1.0000
  15.750   1.2820   0.11144   0.10650  -0.0565   0.0095   1.0000
  16.000   1.2716   0.11773   0.11295  -0.0596   0.0094   1.0000
  16.250   1.2609   0.12429   0.11967  -0.0631   0.0094   1.0000
  16.500   1.2497   0.13116   0.12671  -0.0670   0.0094   1.0000
  16.750   1.2384   0.13830   0.13400  -0.0711   0.0094   1.0000
  17.000   1.2267   0.14583   0.14169  -0.0756   0.0094   1.0000
  17.250   1.2150   0.15371   0.14972  -0.0805   0.0094   1.0000
  17.500   1.2031   0.16203   0.15818  -0.0857   0.0094   1.0000
  17.750   1.1906   0.17091   0.16720  -0.0914   0.0095   1.0000
  18.000   1.1776   0.18042   0.17683  -0.0975   0.0095   1.0000
  18.250   1.1640   0.19079   0.18732  -0.1041   0.0096   1.0000
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