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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.24 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe122-il-1000000.txt
Download as CSV file: xf-goe122-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 122 (MVA H.2) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3406   0.08872   0.08728  -0.0076   1.0000   0.0116
  -8.500  -0.3368   0.08532   0.08389  -0.0086   1.0000   0.0118
  -8.250  -0.4448   0.09374   0.09223  -0.0005   1.0000   0.0113
  -8.000  -0.4378   0.09088   0.08938  -0.0019   1.0000   0.0114
  -7.750  -0.4312   0.08790   0.08643  -0.0037   1.0000   0.0116
  -7.500  -0.4237   0.08465   0.08319  -0.0064   1.0000   0.0118
  -7.250  -0.4119   0.08097   0.07952  -0.0105   1.0000   0.0120
  -7.000  -0.3982   0.07709   0.07565  -0.0150   1.0000   0.0124
  -6.750  -0.3822   0.07293   0.07148  -0.0200   1.0000   0.0131
  -6.500  -0.3434   0.06459   0.06305  -0.0346   0.9713   0.0142
  -6.250  -0.3182   0.05908   0.05742  -0.0407   0.9428   0.0143
  -6.000  -0.2735   0.03786   0.03610  -0.0427   0.8902   0.0146
  -5.750  -0.2567   0.03506   0.03323  -0.0440   0.8798   0.0149
  -5.500  -0.2375   0.03189   0.02998  -0.0460   0.8700   0.0152
  -5.250  -0.2370   0.04411   0.04198  -0.0509   0.8870   0.0156
  -4.250  -0.1190   0.00937   0.00616  -0.0564   0.8240   0.0190
  -4.000  -0.0951   0.00947   0.00627  -0.0564   0.8091   0.0199
  -3.750  -0.0656   0.00895   0.00544  -0.0558   0.7945   0.0232
  -3.500  -0.0404   0.00712   0.00323  -0.0557   0.7793   0.0233
  -3.250  -0.0181   0.01584   0.01122  -0.0579   0.7939   0.0241
  -3.000   0.0082   0.01529   0.01066  -0.0580   0.7748   0.0251
  -2.750   0.0352   0.01504   0.01030  -0.0580   0.7538   0.0270
  -2.500   0.0641   0.01610   0.01120  -0.0575   0.7324   0.0299
  -2.250   0.0918   0.01514   0.00996  -0.0573   0.7094   0.0300
  -2.000   0.1186   0.01203   0.00647  -0.0574   0.6878   0.0319
  -1.750   0.1461   0.01159   0.00597  -0.0574   0.6664   0.0336
  -1.500   0.1741   0.01124   0.00548  -0.0573   0.6487   0.0359
  -1.250   0.2027   0.01002   0.00398  -0.0569   0.6332   0.0317
  -1.000   0.2309   0.00980   0.00364  -0.0568   0.6158   0.0308
  -0.750   0.2587   0.00927   0.00303  -0.0567   0.5979   0.0311
  -0.500   0.2866   0.00886   0.00255  -0.0566   0.5804   0.0314
  -0.250   0.3145   0.00857   0.00219  -0.0565   0.5614   0.0318
   0.000   0.3424   0.00839   0.00193  -0.0565   0.5394   0.0323
   0.250   0.3703   0.00830   0.00173  -0.0565   0.5139   0.0327
   0.500   0.3982   0.00825   0.00158  -0.0565   0.4878   0.0331
   0.750   0.4262   0.00823   0.00146  -0.0565   0.4660   0.0336
   1.000   0.4542   0.00824   0.00139  -0.0565   0.4477   0.0347
   1.250   0.4822   0.00824   0.00132  -0.0565   0.4330   0.0354
   1.500   0.5103   0.00825   0.00129  -0.0565   0.4217   0.0367
   1.750   0.5383   0.00830   0.00127  -0.0565   0.4085   0.0381
   2.000   0.5663   0.00837   0.00127  -0.0565   0.3946   0.0396
   2.250   0.5944   0.00841   0.00129  -0.0565   0.3850   0.0446
   2.500   0.6179   0.00672   0.00154  -0.0565   0.3777   0.8365
   2.750   0.6466   0.00651   0.00157  -0.0564   0.3683   1.0000
   3.000   0.6746   0.00661   0.00163  -0.0564   0.3600   1.0000
   3.250   0.7024   0.00675   0.00171  -0.0564   0.3488   1.0000
   3.500   0.7301   0.00690   0.00180  -0.0564   0.3373   1.0000
   3.750   0.7578   0.00705   0.00189  -0.0564   0.3236   1.0000
   4.000   0.7854   0.00720   0.00199  -0.0564   0.3107   1.0000
   4.250   0.8128   0.00739   0.00212  -0.0564   0.2946   1.0000
   4.500   0.8400   0.00762   0.00226  -0.0563   0.2713   1.0000
   4.750   0.8659   0.00809   0.00249  -0.0562   0.2228   1.0000
   5.000   0.8906   0.00878   0.00288  -0.0560   0.1684   1.0000
   5.250   0.9169   0.00917   0.00317  -0.0559   0.1464   1.0000
   5.500   0.9394   0.01027   0.00379  -0.0555   0.0569   1.0000
   5.750   0.9649   0.01077   0.00421  -0.0552   0.0399   1.0000
   6.000   0.9911   0.01114   0.00458  -0.0550   0.0351   1.0000
   6.250   1.0174   0.01146   0.00495  -0.0548   0.0331   1.0000
   6.500   1.0436   0.01176   0.00528  -0.0547   0.0320   1.0000
   6.750   1.0696   0.01210   0.00566  -0.0545   0.0304   1.0000
   7.000   1.0951   0.01249   0.00609  -0.0543   0.0285   1.0000
   7.250   1.1196   0.01308   0.00673  -0.0539   0.0260   1.0000
   7.500   1.1440   0.01362   0.00734  -0.0535   0.0244   1.0000
   7.750   1.1700   0.01386   0.00760  -0.0533   0.0233   1.0000
   8.000   1.1952   0.01420   0.00797  -0.0531   0.0217   1.0000
   8.250   1.2200   0.01460   0.00837  -0.0528   0.0202   1.0000
   8.500   1.2411   0.01555   0.00940  -0.0521   0.0181   1.0000
   8.750   1.2669   0.01574   0.00961  -0.0519   0.0173   1.0000
   9.000   1.2918   0.01604   0.00992  -0.0517   0.0160   1.0000
   9.250   1.3162   0.01640   0.01028  -0.0514   0.0149   1.0000
   9.500   1.3354   0.01744   0.01140  -0.0504   0.0134   1.0000
   9.750   1.3588   0.01786   0.01187  -0.0500   0.0128   1.0000
  10.000   1.3812   0.01839   0.01245  -0.0494   0.0121   1.0000
  10.250   1.4032   0.01893   0.01303  -0.0488   0.0114   1.0000
  10.500   1.4241   0.01955   0.01367  -0.0482   0.0107   1.0000
  10.750   1.4361   0.02108   0.01532  -0.0464   0.0098   1.0000
  11.000   1.4563   0.02168   0.01598  -0.0456   0.0095   1.0000
  11.250   1.4738   0.02248   0.01687  -0.0445   0.0091   1.0000
  11.500   1.4897   0.02336   0.01784  -0.0433   0.0087   1.0000
  11.750   1.5044   0.02427   0.01882  -0.0420   0.0084   1.0000
  12.000   1.5169   0.02520   0.01983  -0.0404   0.0081   1.0000
  12.250   1.5244   0.02629   0.02098  -0.0381   0.0078   1.0000
  12.500   1.5268   0.02784   0.02262  -0.0358   0.0075   1.0000
  12.750   1.5219   0.03022   0.02514  -0.0336   0.0073   1.0000
  13.000   1.5083   0.03380   0.02891  -0.0317   0.0071   1.0000
  13.250   1.5092   0.03625   0.03149  -0.0311   0.0070   1.0000
  13.500   1.5114   0.03874   0.03410  -0.0309   0.0069   1.0000
  13.750   1.5124   0.04152   0.03700  -0.0310   0.0068   1.0000
  14.000   1.5110   0.04475   0.04036  -0.0313   0.0067   1.0000
  14.250   1.5087   0.04821   0.04395  -0.0320   0.0066   1.0000
  14.500   1.5054   0.05193   0.04778  -0.0329   0.0065   1.0000
  14.750   1.5004   0.05594   0.05192  -0.0339   0.0064   1.0000
  15.000   1.4944   0.06017   0.05626  -0.0351   0.0063   1.0000
  15.250   1.4865   0.06476   0.06098  -0.0366   0.0062   1.0000
  15.500   1.4775   0.06957   0.06591  -0.0382   0.0061   1.0000
  15.750   1.4683   0.07458   0.07103  -0.0400   0.0060   1.0000
  16.000   1.4579   0.07991   0.07648  -0.0419   0.0059   1.0000
  16.250   1.4475   0.08530   0.08198  -0.0440   0.0059   1.0000
  16.500   1.4359   0.09101   0.08780  -0.0463   0.0058   1.0000
  16.750   1.4237   0.09692   0.09383  -0.0486   0.0058   1.0000
  17.000   1.4114   0.10290   0.09992  -0.0511   0.0057   1.0000
  17.250   1.3988   0.10910   0.10622  -0.0538   0.0057   1.0000
  17.500   1.3863   0.11540   0.11263  -0.0566   0.0056   1.0000
  17.750   1.3723   0.12204   0.11938  -0.0596   0.0056   1.0000
  18.000   1.3591   0.12872   0.12617  -0.0628   0.0056   1.0000
  18.250   1.3458   0.13559   0.13316  -0.0662   0.0055   1.0000
  18.500   1.3332   0.14252   0.14019  -0.0698   0.0055   1.0000
  18.750   1.3194   0.14985   0.14763  -0.0738   0.0055   1.0000
  19.000   1.3049   0.15764   0.15554  -0.0781   0.0055   1.0000
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