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GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 422 AIRFOIL (goe422-il)
Reynolds number: 500,000
Max Cl/Cd: 97.36 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe422-il-500000.txt
Download as CSV file: xf-goe422-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000   0.0001   0.10300   0.10028  -0.1019   0.9070   0.0403
 -10.750   0.0057   0.10045   0.09770  -0.1024   0.8938   0.0411
 -10.500  -0.0191   0.09264   0.08982  -0.1089   0.8788   0.0434
 -10.250  -0.0081   0.09067   0.08780  -0.1083   0.8674   0.0436
 -10.000   0.0029   0.08881   0.08586  -0.1080   0.8572   0.0438
  -9.750   0.0140   0.08688   0.08388  -0.1082   0.8476   0.0441
  -9.500   0.0239   0.08478   0.08171  -0.1087   0.8395   0.0445
  -9.250   0.0328   0.08245   0.07934  -0.1096   0.8316   0.0451
  -9.000   0.0012   0.07185   0.06869  -0.1211   0.8231   0.0484
  -8.750   0.0130   0.07011   0.06694  -0.1206   0.8170   0.0487
  -8.500   0.0247   0.06837   0.06517  -0.1208   0.8109   0.0489
  -8.250  -0.1323   0.02472   0.01939  -0.1510   0.8004   0.0385
  -8.000  -0.1130   0.02306   0.01745  -0.1506   0.7951   0.0386
  -7.750  -0.0922   0.02151   0.01562  -0.1502   0.7904   0.0387
  -7.500  -0.0697   0.02001   0.01390  -0.1500   0.7856   0.0390
  -7.250  -0.0460   0.01900   0.01282  -0.1496   0.7810   0.0394
  -7.000  -0.0208   0.01835   0.01212  -0.1494   0.7761   0.0398
  -6.750   0.0052   0.01780   0.01149  -0.1492   0.7716   0.0404
  -6.500   0.0318   0.01723   0.01079  -0.1491   0.7671   0.0409
  -6.250   0.0573   0.01658   0.01006  -0.1488   0.7626   0.0413
  -6.000   0.0834   0.01598   0.00936  -0.1485   0.7576   0.0418
  -5.750   0.1099   0.01545   0.00872  -0.1482   0.7530   0.0422
  -5.500   0.1373   0.01501   0.00815  -0.1481   0.7485   0.0427
  -5.250   0.1640   0.01463   0.00770  -0.1479   0.7438   0.0432
  -5.000   0.1898   0.01400   0.00705  -0.1475   0.7386   0.0438
  -4.750   0.2163   0.01358   0.00662  -0.1473   0.7334   0.0446
  -4.500   0.2438   0.01330   0.00628  -0.1471   0.7277   0.0455
  -4.250   0.2697   0.01298   0.00597  -0.1467   0.7208   0.0465
  -4.000   0.2964   0.01272   0.00564  -0.1463   0.7137   0.0477
  -3.750   0.3231   0.01241   0.00528  -0.1460   0.7075   0.0490
  -3.500   0.3493   0.01212   0.00504  -0.1457   0.7013   0.0505
  -3.250   0.3763   0.01191   0.00480  -0.1454   0.6954   0.0522
  -3.000   0.4036   0.01174   0.00455  -0.1452   0.6896   0.0542
  -2.750   0.4298   0.01149   0.00436  -0.1449   0.6830   0.0569
  -2.500   0.4567   0.01132   0.00415  -0.1446   0.6764   0.0607
  -2.250   0.4838   0.01120   0.00401  -0.1444   0.6703   0.0664
  -2.000   0.5104   0.01104   0.00394  -0.1441   0.6634   0.0759
  -1.750   0.5375   0.01099   0.00390  -0.1438   0.6565   0.0880
  -1.500   0.5644   0.01095   0.00386  -0.1436   0.6496   0.0988
  -1.250   0.5908   0.01087   0.00378  -0.1433   0.6418   0.1077
  -1.000   0.6172   0.01085   0.00370  -0.1430   0.6344   0.1158
  -0.750   0.6435   0.01076   0.00366  -0.1427   0.6263   0.1246
  -0.500   0.6695   0.01071   0.00359  -0.1423   0.6187   0.1347
  -0.250   0.6956   0.01065   0.00357  -0.1420   0.6110   0.1489
   0.000   0.7210   0.01051   0.00357  -0.1416   0.6029   0.1952
   0.250   0.7458   0.01028   0.00364  -0.1412   0.5953   0.3065
   0.750   0.7907   0.00948   0.00387  -0.1395   0.5788   0.6716
   1.000   0.8119   0.00936   0.00402  -0.1379   0.5694   0.7995
   1.250   0.8325   0.00932   0.00410  -0.1362   0.5600   0.8605
   1.500   0.8794   0.00936   0.00422  -0.1400   0.5482   1.0000
   1.750   0.9021   0.00952   0.00429  -0.1390   0.5394   1.0000
   2.000   0.9245   0.00969   0.00437  -0.1380   0.5301   1.0000
   2.250   0.9473   0.00986   0.00447  -0.1370   0.5218   1.0000
   2.500   0.9699   0.01003   0.00457  -0.1361   0.5129   1.0000
   2.750   0.9921   0.01024   0.00470  -0.1350   0.5047   1.0000
   3.000   1.0145   0.01042   0.00483  -0.1340   0.4957   1.0000
   3.250   1.0349   0.01064   0.00497  -0.1327   0.4872   1.0000
   3.500   1.0551   0.01085   0.00513  -0.1313   0.4774   1.0000
   3.750   1.0745   0.01110   0.00531  -0.1298   0.4679   1.0000
   4.000   1.0944   0.01136   0.00551  -0.1284   0.4578   1.0000
   4.250   1.1144   0.01164   0.00573  -0.1271   0.4484   1.0000
   4.500   1.1335   0.01196   0.00598  -0.1256   0.4383   1.0000
   4.750   1.1538   0.01226   0.00623  -0.1244   0.4289   1.0000
   5.000   1.1718   0.01264   0.00654  -0.1228   0.4191   1.0000
   5.250   1.1923   0.01296   0.00682  -0.1218   0.4101   1.0000
   5.500   1.2099   0.01339   0.00718  -0.1202   0.4013   1.0000
   5.750   1.2304   0.01372   0.00750  -0.1192   0.3936   1.0000
   6.000   1.2487   0.01415   0.00787  -0.1178   0.3860   1.0000
   6.250   1.2678   0.01456   0.00825  -0.1166   0.3795   1.0000
   6.500   1.2872   0.01497   0.00864  -0.1155   0.3731   1.0000
   6.750   1.3045   0.01548   0.00910  -0.1141   0.3670   1.0000
   7.000   1.3242   0.01589   0.00951  -0.1131   0.3618   1.0000
   7.250   1.3432   0.01633   0.00995  -0.1120   0.3564   1.0000
   7.500   1.3602   0.01688   0.01046  -0.1106   0.3511   1.0000
   7.750   1.3781   0.01740   0.01097  -0.1094   0.3460   1.0000
   8.000   1.3972   0.01787   0.01146  -0.1085   0.3412   1.0000
   8.250   1.4147   0.01842   0.01200  -0.1073   0.3367   1.0000
   8.500   1.4300   0.01910   0.01265  -0.1059   0.3323   1.0000
   8.750   1.4486   0.01962   0.01320  -0.1049   0.3286   1.0000
   9.000   1.4672   0.02016   0.01377  -0.1040   0.3246   1.0000
   9.250   1.4838   0.02080   0.01443  -0.1029   0.3205   1.0000
   9.500   1.4984   0.02157   0.01518  -0.1016   0.3163   1.0000
   9.750   1.5146   0.02227   0.01590  -0.1005   0.3123   1.0000
  10.000   1.5321   0.02291   0.01659  -0.0997   0.3077   1.0000
  10.250   1.5462   0.02376   0.01744  -0.0985   0.3023   1.0000
  10.500   1.5579   0.02478   0.01844  -0.0970   0.2971   1.0000
  10.750   1.5749   0.02549   0.01921  -0.0962   0.2914   1.0000
  11.000   1.5879   0.02647   0.02020  -0.0951   0.2855   1.0000
  11.250   1.5992   0.02759   0.02132  -0.0938   0.2800   1.0000
  11.500   1.6149   0.02845   0.02223  -0.0930   0.2741   1.0000
  11.750   1.6240   0.02978   0.02355  -0.0916   0.2667   1.0000
  12.000   1.6360   0.03093   0.02472  -0.0906   0.2577   1.0000
  12.250   1.6427   0.03251   0.02628  -0.0891   0.2475   1.0000
  12.500   1.6474   0.03429   0.02803  -0.0876   0.2342   1.0000
  12.750   1.6473   0.03650   0.03018  -0.0858   0.2138   1.0000
  13.000   1.6317   0.04009   0.03358  -0.0831   0.1828   1.0000
  13.250   1.6109   0.04430   0.03764  -0.0804   0.1548   1.0000
  13.500   1.5947   0.04829   0.04153  -0.0782   0.1331   1.0000
  13.750   1.5825   0.05204   0.04523  -0.0765   0.1180   1.0000
  14.000   1.5772   0.05526   0.04844  -0.0753   0.1106   1.0000
  14.250   1.5734   0.05839   0.05159  -0.0743   0.1060   1.0000
  14.500   1.5729   0.06119   0.05445  -0.0736   0.1037   1.0000
  14.750   1.5715   0.06418   0.05750  -0.0729   0.1019   1.0000
  15.000   1.5685   0.06740   0.06078  -0.0723   0.1003   1.0000
  15.250   1.5649   0.07074   0.06418  -0.0718   0.0988   1.0000
  15.500   1.5604   0.07422   0.06772  -0.0714   0.0975   1.0000
  15.750   1.5546   0.07790   0.07147  -0.0710   0.0964   1.0000
  16.000   1.5516   0.08130   0.07496  -0.0708   0.0958   1.0000
  16.250   1.5499   0.08455   0.07830  -0.0707   0.0953   1.0000
  16.500   1.5474   0.08794   0.08177  -0.0706   0.0948   1.0000
  16.750   1.5443   0.09140   0.08531  -0.0706   0.0943   1.0000
  17.000   1.5420   0.09474   0.08874  -0.0706   0.0937   1.0000
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