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GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il)
Reynolds number: 200,000
Max Cl/Cd: 72.43 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe142-il-200000-n5.txt
Download as CSV file: xf-goe142-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 142 (MVA H.19) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4018   0.10496   0.10140  -0.0072   1.0000   0.0208
  -8.250  -0.3982   0.10283   0.09932  -0.0114   1.0000   0.0216
  -8.000  -0.3948   0.10020   0.09673  -0.0146   1.0000   0.0217
  -7.500  -0.3012   0.07931   0.07616  -0.0247   1.0000   0.0220
  -7.250  -0.3019   0.07491   0.07181  -0.0242   1.0000   0.0223
  -7.000  -0.3007   0.07148   0.06842  -0.0234   1.0000   0.0225
  -6.750  -0.2997   0.06829   0.06527  -0.0232   1.0000   0.0228
  -6.500  -0.3002   0.06525   0.06228  -0.0232   1.0000   0.0229
  -6.250  -0.3015   0.06237   0.05945  -0.0231   1.0000   0.0231
  -6.000  -0.2937   0.05850   0.05557  -0.0257   0.9977   0.0232
  -5.750  -0.2710   0.05282   0.04984  -0.0328   0.9922   0.0231
  -5.500  -0.2951   0.06468   0.06133  -0.0376   1.0000   0.0219
  -5.250  -0.2874   0.06083   0.05751  -0.0368   0.9973   0.0201
  -5.000  -0.2511   0.05517   0.05173  -0.0445   0.9921   0.0182
  -4.750  -0.2089   0.04870   0.04506  -0.0531   0.9866   0.0172
  -4.500  -0.1699   0.04466   0.04086  -0.0589   0.9820   0.0190
  -4.250  -0.1293   0.03952   0.03547  -0.0645   0.9760   0.0199
  -4.000  -0.0879   0.03432   0.02994  -0.0697   0.9714   0.0194
  -3.750  -0.0502   0.02925   0.02446  -0.0730   0.9643   0.0195
  -3.500  -0.0109   0.02355   0.01814  -0.0760   0.9585   0.0201
  -3.250   0.0248   0.01897   0.01272  -0.0776   0.9516   0.0224
  -3.000   0.0581   0.01747   0.01097  -0.0789   0.9438   0.0239
  -2.750   0.0896   0.01602   0.00920  -0.0795   0.9340   0.0254
  -2.500   0.1216   0.01474   0.00761  -0.0800   0.9245   0.0275
  -2.250   0.1527   0.01405   0.00668  -0.0802   0.9136   0.0307
  -2.000   0.1813   0.01316   0.00571  -0.0802   0.9006   0.0342
  -1.750   0.2096   0.01258   0.00504  -0.0799   0.8866   0.0378
  -1.500   0.2374   0.01214   0.00448  -0.0796   0.8718   0.0430
  -1.250   0.2646   0.01172   0.00403  -0.0791   0.8557   0.0481
  -1.000   0.2916   0.01145   0.00364  -0.0786   0.8381   0.0542
  -0.750   0.3184   0.01115   0.00333  -0.0781   0.8195   0.0625
  -0.500   0.3451   0.01093   0.00301  -0.0775   0.8000   0.0705
  -0.250   0.3718   0.01080   0.00281  -0.0770   0.7784   0.0830
   0.250   0.4248   0.01055   0.00248  -0.0760   0.7323   0.1181
   0.500   0.4513   0.01044   0.00238  -0.0756   0.7079   0.1590
   0.750   0.4689   0.00878   0.00242  -0.0736   0.6853   0.7890
   1.250   0.5272   0.00883   0.00225  -0.0734   0.6335   1.0000
   1.500   0.5537   0.00902   0.00225  -0.0730   0.6084   1.0000
   1.750   0.5800   0.00923   0.00228  -0.0725   0.5833   1.0000
   2.000   0.6063   0.00945   0.00233  -0.0721   0.5590   1.0000
   2.250   0.6327   0.00967   0.00240  -0.0717   0.5344   1.0000
   2.500   0.6590   0.00991   0.00249  -0.0714   0.5110   1.0000
   2.750   0.6851   0.01016   0.00262  -0.0710   0.4880   1.0000
   3.000   0.7114   0.01041   0.00276  -0.0707   0.4657   1.0000
   3.250   0.7375   0.01068   0.00291  -0.0704   0.4444   1.0000
   3.500   0.7638   0.01094   0.00309  -0.0701   0.4237   1.0000
   3.750   0.7898   0.01122   0.00330  -0.0697   0.4045   1.0000
   4.000   0.8159   0.01150   0.00352  -0.0694   0.3862   1.0000
   4.250   0.8419   0.01179   0.00375  -0.0691   0.3681   1.0000
   4.500   0.8678   0.01209   0.00400  -0.0688   0.3513   1.0000
   4.750   0.8937   0.01240   0.00430  -0.0685   0.3353   1.0000
   5.000   0.9193   0.01273   0.00459  -0.0682   0.3197   1.0000
   5.250   0.9450   0.01306   0.00490  -0.0679   0.3053   1.0000
   5.500   0.9705   0.01340   0.00524  -0.0675   0.2911   1.0000
   5.750   0.9959   0.01375   0.00562  -0.0672   0.2773   1.0000
   6.000   1.0212   0.01411   0.00600  -0.0668   0.2641   1.0000
   6.250   1.0463   0.01449   0.00640  -0.0664   0.2508   1.0000
   6.500   1.0712   0.01489   0.00682  -0.0660   0.2366   1.0000
   6.750   1.0955   0.01534   0.00725  -0.0656   0.2167   1.0000
   7.000   1.1191   0.01585   0.00773  -0.0651   0.1935   1.0000
   7.250   1.1431   0.01634   0.00822  -0.0647   0.1735   1.0000
   7.500   1.1663   0.01691   0.00876  -0.0641   0.1528   1.0000
   7.750   1.1889   0.01757   0.00936  -0.0636   0.1272   1.0000
   8.000   1.2099   0.01845   0.01010  -0.0628   0.0932   1.0000
   8.250   1.2283   0.01968   0.01115  -0.0619   0.0577   1.0000
   8.500   1.2466   0.02092   0.01231  -0.0608   0.0387   1.0000
   8.750   1.2650   0.02208   0.01350  -0.0596   0.0295   1.0000
   9.000   1.2837   0.02314   0.01467  -0.0585   0.0249   1.0000
   9.250   1.2995   0.02450   0.01615  -0.0570   0.0217   1.0000
   9.500   1.3169   0.02555   0.01738  -0.0558   0.0194   1.0000
   9.750   1.3327   0.02671   0.01870  -0.0544   0.0173   1.0000
  10.000   1.3441   0.02825   0.02037  -0.0526   0.0159   1.0000
  10.250   1.3509   0.03013   0.02239  -0.0502   0.0149   1.0000
  10.500   1.3605   0.03162   0.02406  -0.0482   0.0143   1.0000
  10.750   1.3661   0.03324   0.02585  -0.0456   0.0138   1.0000
  11.000   1.3693   0.03501   0.02779  -0.0430   0.0132   1.0000
  11.250   1.3718   0.03691   0.02986  -0.0407   0.0127   1.0000
  11.500   1.3740   0.03891   0.03201  -0.0388   0.0121   1.0000
  11.750   1.3756   0.04103   0.03428  -0.0373   0.0115   1.0000
  12.000   1.3758   0.04341   0.03678  -0.0361   0.0110   1.0000
  12.250   1.3733   0.04627   0.03981  -0.0353   0.0106   1.0000
  12.500   1.3673   0.04976   0.04344  -0.0347   0.0103   1.0000
  12.750   1.3602   0.05366   0.04750  -0.0344   0.0100   1.0000
  13.000   1.3562   0.05731   0.05137  -0.0347   0.0099   1.0000
  13.250   1.3507   0.06136   0.05563  -0.0354   0.0097   1.0000
  13.500   1.3433   0.06583   0.06031  -0.0364   0.0096   1.0000
  13.750   1.3345   0.07073   0.06542  -0.0380   0.0095   1.0000
  14.000   1.3242   0.07602   0.07091  -0.0399   0.0094   1.0000
  14.250   1.3123   0.08175   0.07685  -0.0422   0.0093   1.0000
  14.500   1.2996   0.08784   0.08313  -0.0450   0.0093   1.0000
  14.750   1.2855   0.09439   0.08987  -0.0481   0.0092   1.0000
  15.000   1.2709   0.10133   0.09699  -0.0516   0.0092   1.0000
  15.250   1.2556   0.10870   0.10453  -0.0556   0.0092   1.0000
  15.500   1.2399   0.11643   0.11243  -0.0598   0.0092   1.0000
  15.750   1.2240   0.12456   0.12072  -0.0644   0.0093   1.0000
  16.000   1.2078   0.13314   0.12945  -0.0694   0.0093   1.0000
  16.250   1.1913   0.14218   0.13863  -0.0748   0.0094   1.0000
  16.500   1.1746   0.15176   0.14833  -0.0805   0.0095   1.0000
  16.750   1.1573   0.16209   0.15877  -0.0867   0.0096   1.0000
  17.000   1.1388   0.17363   0.17038  -0.0936   0.0097   1.0000
  17.250   1.1187   0.18675   0.18354  -0.1011   0.0099   1.0000
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