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GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.26 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe122-il-1000000-n5.txt
Download as CSV file: xf-goe122-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4308   0.09040   0.08890  -0.0053   0.9807   0.0048
  -8.000  -0.4265   0.08603   0.08443  -0.0084   0.9232   0.0049
  -7.750  -0.4232   0.08109   0.07942  -0.0127   0.9031   0.0051
  -7.500  -0.4150   0.07411   0.07239  -0.0206   0.8894   0.0055
  -7.000  -0.3807   0.06612   0.06427  -0.0305   0.8656   0.0058
  -6.750  -0.3603   0.06155   0.05962  -0.0360   0.8545   0.0060
  -6.500  -0.3376   0.05585   0.05381  -0.0425   0.8436   0.0064
  -6.000  -0.2902   0.01537   0.01111  -0.0646   0.8301   0.0109
  -5.750  -0.2624   0.01601   0.01178  -0.0645   0.8141   0.0113
  -5.500  -0.2351   0.01605   0.01177  -0.0643   0.7967   0.0117
  -5.000  -0.1828   0.01252   0.00752  -0.0642   0.7620   0.0143
  -4.750  -0.1549   0.01280   0.00775  -0.0641   0.7420   0.0147
  -4.500  -0.1272   0.01304   0.00793  -0.0640   0.7194   0.0152
  -4.250  -0.0996   0.01289   0.00764  -0.0639   0.6985   0.0160
  -4.000  -0.0721   0.01189   0.00634  -0.0638   0.6803   0.0177
  -3.750  -0.0442   0.01167   0.00595  -0.0638   0.6640   0.0184
  -3.500  -0.0166   0.01118   0.00532  -0.0638   0.6484   0.0190
  -3.250   0.0114   0.01102   0.00508  -0.0638   0.6336   0.0194
  -3.000   0.0394   0.01095   0.00495  -0.0638   0.6208   0.0199
  -2.750   0.0674   0.01078   0.00470  -0.0638   0.6093   0.0206
  -2.500   0.0954   0.01050   0.00432  -0.0638   0.5961   0.0212
  -2.250   0.1234   0.01023   0.00394  -0.0638   0.5794   0.0219
  -2.000   0.1514   0.01008   0.00368  -0.0638   0.5596   0.0227
  -1.750   0.1794   0.00987   0.00337  -0.0638   0.5397   0.0232
  -1.500   0.2073   0.00970   0.00309  -0.0637   0.5194   0.0235
  -1.000   0.2629   0.00948   0.00261  -0.0637   0.4658   0.0240
  -0.750   0.2907   0.00941   0.00243  -0.0637   0.4427   0.0241
  -0.500   0.3187   0.00935   0.00229  -0.0637   0.4258   0.0243
  -0.250   0.3466   0.00913   0.00200  -0.0638   0.4143   0.0247
   0.000   0.3747   0.00894   0.00176  -0.0638   0.4048   0.0250
   0.250   0.4029   0.00879   0.00157  -0.0639   0.3973   0.0256
   0.500   0.4310   0.00872   0.00146  -0.0639   0.3896   0.0264
   0.750   0.4593   0.00867   0.00140  -0.0639   0.3832   0.0272
   1.000   0.4875   0.00865   0.00136  -0.0640   0.3761   0.0279
   1.250   0.5156   0.00865   0.00133  -0.0640   0.3692   0.0287
   1.500   0.5436   0.00869   0.00133  -0.0641   0.3574   0.0293
   1.750   0.5714   0.00878   0.00134  -0.0641   0.3388   0.0297
   2.000   0.5993   0.00884   0.00135  -0.0641   0.3268   0.0302
   2.250   0.6273   0.00889   0.00138  -0.0642   0.3183   0.0309
   2.500   0.6553   0.00896   0.00143  -0.0642   0.3100   0.0316
   2.750   0.6831   0.00904   0.00148  -0.0642   0.3002   0.0321
   3.000   0.7108   0.00914   0.00154  -0.0642   0.2870   0.0335
   3.250   0.7378   0.00937   0.00167  -0.0642   0.2580   0.0413
   3.750   0.7863   0.00831   0.00229  -0.0638   0.1764   1.0000
   4.000   0.8133   0.00856   0.00247  -0.0637   0.1635   1.0000
   4.250   0.8405   0.00877   0.00264  -0.0637   0.1546   1.0000
   4.500   0.8676   0.00900   0.00282  -0.0636   0.1460   1.0000
   4.750   0.8948   0.00920   0.00299  -0.0636   0.1375   1.0000
   5.000   0.9213   0.00950   0.00321  -0.0635   0.1206   1.0000
   5.250   0.9440   0.01055   0.00385  -0.0630   0.0407   1.0000
   5.500   0.9705   0.01083   0.00411  -0.0629   0.0349   1.0000
   5.750   0.9972   0.01106   0.00437  -0.0628   0.0327   1.0000
   6.000   1.0238   0.01130   0.00463  -0.0627   0.0318   1.0000
   6.250   1.0502   0.01155   0.00490  -0.0626   0.0308   1.0000
   6.500   1.0764   0.01184   0.00520  -0.0624   0.0293   1.0000
   6.750   1.1024   0.01214   0.00552  -0.0623   0.0277   1.0000
   7.000   1.1281   0.01247   0.00587  -0.0621   0.0260   1.0000
   7.250   1.1535   0.01284   0.00628  -0.0618   0.0243   1.0000
   7.500   1.1790   0.01318   0.00666  -0.0616   0.0232   1.0000
   7.750   1.2049   0.01341   0.00691  -0.0615   0.0226   1.0000
   8.000   1.2305   0.01368   0.00721  -0.0613   0.0213   1.0000
   8.250   1.2558   0.01399   0.00753  -0.0611   0.0189   1.0000
   8.500   1.2802   0.01441   0.00792  -0.0608   0.0153   1.0000
   8.750   1.3042   0.01485   0.00833  -0.0605   0.0123   1.0000
   9.000   1.3280   0.01532   0.00882  -0.0601   0.0103   1.0000
   9.250   1.3513   0.01582   0.00935  -0.0596   0.0089   1.0000
   9.500   1.3739   0.01638   0.00994  -0.0591   0.0077   1.0000
   9.750   1.3967   0.01689   0.01051  -0.0586   0.0071   1.0000
  10.000   1.4188   0.01745   0.01111  -0.0580   0.0064   1.0000
  10.250   1.4398   0.01810   0.01181  -0.0573   0.0057   1.0000
  10.500   1.4603   0.01878   0.01255  -0.0566   0.0053   1.0000
  10.750   1.4808   0.01941   0.01325  -0.0558   0.0050   1.0000
  11.000   1.5003   0.02009   0.01400  -0.0549   0.0047   1.0000
  11.250   1.5188   0.02082   0.01480  -0.0540   0.0044   1.0000
  11.500   1.5361   0.02162   0.01567  -0.0528   0.0041   1.0000
  11.750   1.5514   0.02253   0.01665  -0.0515   0.0039   1.0000
  12.000   1.5631   0.02365   0.01787  -0.0498   0.0036   1.0000
  12.250   1.5740   0.02460   0.01891  -0.0478   0.0036   1.0000
  12.500   1.5819   0.02563   0.02003  -0.0456   0.0035   1.0000
  12.750   1.5885   0.02685   0.02136  -0.0435   0.0034   1.0000
  13.000   1.5941   0.02827   0.02288  -0.0418   0.0033   1.0000
  13.250   1.5991   0.02988   0.02458  -0.0404   0.0032   1.0000
  13.500   1.6031   0.03171   0.02653  -0.0392   0.0031   1.0000
  13.750   1.6062   0.03376   0.02868  -0.0383   0.0030   1.0000
  14.000   1.6083   0.03608   0.03111  -0.0378   0.0029   1.0000
  14.250   1.6094   0.03866   0.03379  -0.0376   0.0028   1.0000
  14.500   1.6088   0.04162   0.03686  -0.0377   0.0027   1.0000
  14.750   1.6060   0.04501   0.04036  -0.0381   0.0026   1.0000
  15.000   1.6009   0.04885   0.04432  -0.0389   0.0026   1.0000
  15.250   1.5940   0.05307   0.04866  -0.0399   0.0025   1.0000
  15.500   1.5841   0.05778   0.05350  -0.0411   0.0025   1.0000
  15.750   1.5726   0.06286   0.05871  -0.0426   0.0025   1.0000
  16.000   1.5594   0.06828   0.06425  -0.0443   0.0024   1.0000
  16.250   1.5444   0.07419   0.07030  -0.0463   0.0024   1.0000
  16.500   1.5290   0.08027   0.07650  -0.0485   0.0024   1.0000
  16.750   1.5126   0.08659   0.08295  -0.0508   0.0024   1.0000
  17.000   1.4954   0.09318   0.08966  -0.0532   0.0024   1.0000
  17.250   1.4781   0.09986   0.09646  -0.0558   0.0023   1.0000
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