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GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 422 AIRFOIL (goe422-il)
Reynolds number: 100,000
Max Cl/Cd: 47.56 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe422-il-100000-n5.txt
Download as CSV file: xf-goe422-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 422 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0102   0.11137   0.10579  -0.1045   0.9267   0.0813
 -10.250   0.0085   0.10869   0.10312  -0.1062   0.9162   0.0818
  -9.250   0.0258   0.09186   0.08621  -0.1137   0.8872   0.0602
  -9.000   0.0361   0.08862   0.08295  -0.1154   0.8820   0.0598
  -8.750   0.0398   0.08574   0.08007  -0.1163   0.8736   0.0595
  -8.500   0.0462   0.08241   0.07672  -0.1180   0.8674   0.0591
  -8.250   0.0493   0.07916   0.07347  -0.1193   0.8602   0.0583
  -7.750   0.0128   0.06650   0.06073  -0.1283   0.8420   0.0544
  -7.500   0.0138   0.06218   0.05635  -0.1316   0.8347   0.0540
  -7.250   0.0158   0.05611   0.05008  -0.1367   0.8297   0.0535
  -7.000   0.0057   0.05140   0.04518  -0.1376   0.8198   0.0531
  -6.750   0.0071   0.04577   0.03914  -0.1399   0.8139   0.0530
  -6.500   0.0146   0.04081   0.03363  -0.1414   0.8090   0.0534
  -6.250   0.0155   0.03743   0.02969  -0.1397   0.8002   0.0542
  -6.000   0.0376   0.03549   0.02748  -0.1400   0.7954   0.0551
  -5.750   0.0663   0.03405   0.02586  -0.1409   0.7919   0.0560
  -5.500   0.0824   0.03277   0.02436  -0.1397   0.7851   0.0566
  -5.250   0.1017   0.03140   0.02273  -0.1388   0.7786   0.0573
  -5.000   0.1290   0.02984   0.02083  -0.1391   0.7742   0.0583
  -4.750   0.1605   0.02825   0.01887  -0.1399   0.7708   0.0596
  -4.500   0.1761   0.02754   0.01796  -0.1379   0.7630   0.0607
  -4.250   0.2006   0.02708   0.01750  -0.1375   0.7569   0.0623
  -4.000   0.2315   0.02634   0.01662  -0.1380   0.7527   0.0647
  -3.750   0.2627   0.02543   0.01548  -0.1385   0.7486   0.0672
  -3.500   0.2777   0.02527   0.01538  -0.1363   0.7401   0.0687
  -3.250   0.3058   0.02471   0.01476  -0.1363   0.7347   0.0711
  -3.000   0.3388   0.02398   0.01388  -0.1370   0.7308   0.0748
  -2.750   0.3567   0.02390   0.01386  -0.1353   0.7228   0.0781
  -2.500   0.3822   0.02352   0.01342  -0.1347   0.7163   0.0834
  -2.250   0.4148   0.02297   0.01280  -0.1353   0.7116   0.0902
  -2.000   0.4334   0.02279   0.01267  -0.1337   0.7030   0.0963
  -1.750   0.4603   0.02236   0.01222  -0.1333   0.6957   0.1059
  -1.500   0.4900   0.02187   0.01169  -0.1335   0.6895   0.1182
  -1.250   0.5086   0.02172   0.01160  -0.1318   0.6801   0.1301
  -1.000   0.5391   0.02125   0.01115  -0.1322   0.6742   0.1476
  -0.750   0.5594   0.02115   0.01115  -0.1308   0.6659   0.1662
  -0.500   0.5851   0.02088   0.01100  -0.1304   0.6588   0.1959
  -0.250   0.6153   0.02044   0.01074  -0.1308   0.6532   0.2606
   0.000   0.6332   0.02033   0.01093  -0.1292   0.6442   0.3427
   0.250   0.6604   0.01972   0.01081  -0.1290   0.6380   0.4985
   0.500   0.6752   0.01923   0.01107  -0.1258   0.6305   0.7434
   0.750   0.7117   0.01897   0.01102  -0.1266   0.6226   0.9269
   1.000   0.7466   0.01893   0.01076  -0.1278   0.6162   1.0000
   1.250   0.7642   0.01922   0.01095  -0.1261   0.6071   1.0000
   1.500   0.7927   0.01924   0.01078  -0.1261   0.6003   1.0000
   1.750   0.8118   0.01952   0.01097  -0.1246   0.5914   1.0000
   2.000   0.8370   0.01964   0.01093  -0.1241   0.5836   1.0000
   2.250   0.8597   0.01985   0.01103  -0.1232   0.5756   1.0000
   2.500   0.8816   0.02008   0.01116  -0.1222   0.5673   1.0000
   2.750   0.9087   0.02022   0.01113  -0.1220   0.5604   1.0000
   3.000   0.9264   0.02058   0.01145  -0.1204   0.5514   1.0000
   3.250   0.9539   0.02070   0.01141  -0.1202   0.5443   1.0000
   3.500   0.9703   0.02110   0.01177  -0.1184   0.5352   1.0000
   3.750   0.9938   0.02132   0.01187  -0.1177   0.5274   1.0000
   4.000   1.0129   0.02167   0.01216  -0.1163   0.5192   1.0000
   4.250   1.0327   0.02201   0.01244  -0.1150   0.5110   1.0000
   4.500   1.0569   0.02229   0.01259  -0.1145   0.5040   1.0000
   4.750   1.0726   0.02279   0.01309  -0.1127   0.4957   1.0000
   5.000   1.0968   0.02306   0.01325  -0.1121   0.4888   1.0000
   5.250   1.1126   0.02360   0.01377  -0.1104   0.4805   1.0000
   5.500   1.1316   0.02402   0.01413  -0.1092   0.4725   1.0000
   5.750   1.1498   0.02448   0.01453  -0.1078   0.4646   1.0000
   6.000   1.1650   0.02504   0.01507  -0.1061   0.4561   1.0000
   6.250   1.1851   0.02545   0.01538  -0.1051   0.4488   1.0000
   6.500   1.1977   0.02616   0.01612  -0.1031   0.4406   1.0000
   6.750   1.2177   0.02660   0.01647  -0.1022   0.4341   1.0000
   7.000   1.2330   0.02728   0.01716  -0.1007   0.4275   1.0000
   7.250   1.2484   0.02797   0.01787  -0.0992   0.4214   1.0000
   7.500   1.2691   0.02844   0.01827  -0.0985   0.4163   1.0000
   7.750   1.2849   0.02916   0.01901  -0.0972   0.4110   1.0000
   8.000   1.2982   0.02999   0.01988  -0.0956   0.4051   1.0000
   8.250   1.3156   0.03060   0.02046  -0.0945   0.3998   1.0000
   8.500   1.3319   0.03130   0.02114  -0.0933   0.3945   1.0000
   8.750   1.3417   0.03233   0.02225  -0.0916   0.3885   1.0000
   9.000   1.3564   0.03312   0.02305  -0.0903   0.3834   1.0000
   9.250   1.3775   0.03359   0.02346  -0.0897   0.3793   1.0000
   9.500   1.3865   0.03479   0.02477  -0.0880   0.3748   1.0000
   9.750   1.3977   0.03589   0.02595  -0.0866   0.3705   1.0000
  10.000   1.4116   0.03683   0.02694  -0.0855   0.3666   1.0000
  10.250   1.4303   0.03746   0.02755  -0.0847   0.3630   1.0000
  10.500   1.4435   0.03847   0.02861  -0.0836   0.3592   1.0000
  10.750   1.4482   0.04005   0.03033  -0.0819   0.3549   1.0000
  11.000   1.4570   0.04138   0.03175  -0.0805   0.3508   1.0000
  11.250   1.4704   0.04235   0.03275  -0.0795   0.3469   1.0000
  11.500   1.4892   0.04294   0.03331  -0.0788   0.3429   1.0000
  11.750   1.4842   0.04532   0.03589  -0.0767   0.3382   1.0000
  12.000   1.4863   0.04723   0.03792  -0.0751   0.3336   1.0000
  12.250   1.4959   0.04852   0.03926  -0.0740   0.3293   1.0000
  12.500   1.5134   0.04913   0.03984  -0.0733   0.3252   1.0000
  12.750   1.4985   0.05265   0.04359  -0.0713   0.3197   1.0000
  13.000   1.4954   0.05518   0.04624  -0.0699   0.3140   1.0000
  13.250   1.5100   0.05595   0.04699  -0.0691   0.3088   1.0000
  13.500   1.4944   0.05998   0.05122  -0.0677   0.3032   1.0000
  13.750   1.4830   0.06373   0.05513  -0.0666   0.2973   1.0000
  14.000   1.4933   0.06502   0.05642  -0.0659   0.2918   1.0000
  14.250   1.4704   0.07042   0.06204  -0.0651   0.2858   1.0000
  14.500   1.4507   0.07568   0.06748  -0.0647   0.2797   1.0000
  14.750   1.4627   0.07689   0.06869  -0.0643   0.2747   1.0000
  15.000   1.4046   0.08780   0.07993  -0.0648   0.2665   1.0000
  15.250   1.4006   0.09136   0.08356  -0.0649   0.2599   1.0000
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