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GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 422 AIRFOIL (goe422-il)
Reynolds number: 200,000
Max Cl/Cd: 66.55 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe422-il-200000-n5.txt
Download as CSV file: xf-goe422-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0063   0.08436   0.07994  -0.1137   0.8532   0.0391
  -9.500   0.0117   0.08140   0.07693  -0.1147   0.8452   0.0389
  -9.250   0.0152   0.07811   0.07360  -0.1161   0.8369   0.0388
  -8.750   0.0156   0.07020   0.06561  -0.1205   0.8223   0.0384
  -8.500   0.0103   0.06515   0.06052  -0.1240   0.8150   0.0382
  -8.250  -0.1042   0.03470   0.02895  -0.1489   0.8039   0.0381
  -8.000  -0.1020   0.03022   0.02383  -0.1490   0.7976   0.0384
  -7.750  -0.0873   0.02759   0.02067  -0.1488   0.7926   0.0387
  -7.500  -0.0688   0.02574   0.01841  -0.1484   0.7877   0.0391
  -7.250  -0.0486   0.02443   0.01685  -0.1478   0.7820   0.0394
  -7.000  -0.0251   0.02359   0.01591  -0.1475   0.7768   0.0397
  -6.750   0.0000   0.02282   0.01502  -0.1473   0.7723   0.0402
  -6.500   0.0247   0.02212   0.01420  -0.1470   0.7676   0.0406
  -6.250   0.0482   0.02145   0.01344  -0.1465   0.7620   0.0411
  -6.000   0.0729   0.02080   0.01266  -0.1461   0.7569   0.0417
  -5.750   0.0992   0.02018   0.01187  -0.1459   0.7523   0.0426
  -5.500   0.1253   0.01960   0.01112  -0.1457   0.7476   0.0436
  -5.250   0.1495   0.01910   0.01058  -0.1451   0.7419   0.0444
  -5.000   0.1750   0.01868   0.01015  -0.1448   0.7366   0.0452
  -4.750   0.2020   0.01825   0.00965  -0.1446   0.7319   0.0460
  -4.500   0.2281   0.01786   0.00919  -0.1443   0.7269   0.0470
  -4.250   0.2529   0.01748   0.00878  -0.1437   0.7208   0.0481
  -4.000   0.2791   0.01711   0.00834  -0.1434   0.7154   0.0493
  -3.750   0.3066   0.01678   0.00798  -0.1433   0.7107   0.0506
  -3.500   0.3312   0.01654   0.00774  -0.1427   0.7041   0.0524
  -3.250   0.3570   0.01627   0.00743  -0.1422   0.6972   0.0548
  -3.000   0.3839   0.01602   0.00714  -0.1420   0.6902   0.0576
  -2.750   0.4081   0.01579   0.00691  -0.1412   0.6807   0.0610
  -2.500   0.4349   0.01558   0.00665  -0.1409   0.6731   0.0652
  -2.250   0.4597   0.01543   0.00653  -0.1403   0.6649   0.0705
  -2.000   0.4859   0.01530   0.00639  -0.1399   0.6579   0.0780
  -1.750   0.5124   0.01521   0.00628  -0.1396   0.6512   0.0872
  -1.500   0.5377   0.01513   0.00620  -0.1391   0.6434   0.0964
  -1.250   0.5642   0.01504   0.00605  -0.1388   0.6365   0.1054
  -1.000   0.5894   0.01497   0.00599  -0.1382   0.6289   0.1145
  -0.750   0.6150   0.01489   0.00589  -0.1378   0.6215   0.1254
  -0.500   0.6404   0.01478   0.00582  -0.1374   0.6141   0.1400
  -0.250   0.6651   0.01466   0.00580  -0.1369   0.6057   0.1636
   0.000   0.6901   0.01449   0.00578  -0.1365   0.5981   0.2202
   0.250   0.7140   0.01434   0.00585  -0.1359   0.5895   0.2941
   0.500   0.7385   0.01420   0.00587  -0.1353   0.5818   0.3685
   0.750   0.7613   0.01395   0.00598  -0.1345   0.5740   0.4862
   1.000   0.7804   0.01356   0.00618  -0.1327   0.5663   0.6746
   1.250   0.8005   0.01347   0.00630  -0.1307   0.5589   0.8094
   1.500   0.8374   0.01341   0.00640  -0.1321   0.5498   0.9431
   1.750   0.8662   0.01357   0.00643  -0.1324   0.5415   1.0000
   2.000   0.8885   0.01376   0.00654  -0.1314   0.5326   1.0000
   2.250   0.9105   0.01398   0.00662  -0.1304   0.5241   1.0000
   2.500   0.9320   0.01419   0.00676  -0.1293   0.5148   1.0000
   3.000   0.9739   0.01468   0.00706  -0.1268   0.4966   1.0000
   3.250   0.9932   0.01496   0.00721  -0.1253   0.4877   1.0000
   3.500   1.0122   0.01521   0.00742  -0.1238   0.4782   1.0000
   3.750   1.0303   0.01553   0.00763  -0.1221   0.4692   1.0000
   4.000   1.0494   0.01583   0.00789  -0.1207   0.4597   1.0000
   4.500   1.0859   0.01654   0.00846  -0.1176   0.4412   1.0000
   5.000   1.1219   0.01733   0.00913  -0.1147   0.4237   1.0000
   5.250   1.1390   0.01778   0.00950  -0.1131   0.4158   1.0000
   5.500   1.1576   0.01820   0.00989  -0.1118   0.4081   1.0000
   5.750   1.1751   0.01867   0.01032  -0.1104   0.4008   1.0000
   6.000   1.1926   0.01916   0.01076  -0.1090   0.3945   1.0000
   6.250   1.2111   0.01963   0.01122  -0.1078   0.3881   1.0000
   6.500   1.2280   0.02016   0.01171  -0.1064   0.3822   1.0000
   6.750   1.2454   0.02070   0.01222  -0.1051   0.3770   1.0000
   7.000   1.2634   0.02123   0.01275  -0.1040   0.3713   1.0000
   7.250   1.2791   0.02185   0.01334  -0.1026   0.3653   1.0000
   7.500   1.2948   0.02250   0.01396  -0.1012   0.3598   1.0000
   7.750   1.3120   0.02309   0.01457  -0.1000   0.3545   1.0000
   8.000   1.3283   0.02374   0.01522  -0.0988   0.3497   1.0000
   8.250   1.3435   0.02446   0.01592  -0.0975   0.3453   1.0000
   8.500   1.3599   0.02514   0.01660  -0.0964   0.3413   1.0000
   8.750   1.3764   0.02582   0.01733  -0.0953   0.3369   1.0000
   9.000   1.3917   0.02658   0.01810  -0.0941   0.3325   1.0000
   9.250   1.4061   0.02739   0.01891  -0.0929   0.3284   1.0000
   9.500   1.4208   0.02821   0.01973  -0.0917   0.3248   1.0000
   9.750   1.4368   0.02897   0.02057  -0.0908   0.3211   1.0000
  10.000   1.4513   0.02983   0.02147  -0.0897   0.3171   1.0000
  10.250   1.4649   0.03075   0.02242  -0.0885   0.3131   1.0000
  10.500   1.4766   0.03178   0.02344  -0.0872   0.3089   1.0000
  10.750   1.4901   0.03274   0.02448  -0.0862   0.3049   1.0000
  11.000   1.5036   0.03372   0.02553  -0.0852   0.3010   1.0000
  11.250   1.5159   0.03480   0.02666  -0.0841   0.2972   1.0000
  11.500   1.5269   0.03597   0.02786  -0.0829   0.2932   1.0000
  11.750   1.5372   0.03722   0.02916  -0.0818   0.2888   1.0000
  12.000   1.5474   0.03852   0.03056  -0.0808   0.2832   1.0000
  12.250   1.5542   0.04010   0.03217  -0.0796   0.2770   1.0000
  12.500   1.5613   0.04171   0.03383  -0.0784   0.2704   1.0000
  12.750   1.5685   0.04337   0.03557  -0.0774   0.2637   1.0000
  13.000   1.5728   0.04528   0.03750  -0.0762   0.2570   1.0000
  13.250   1.5778   0.04721   0.03951  -0.0753   0.2477   1.0000
  13.500   1.5805   0.04940   0.04174  -0.0742   0.2388   1.0000
  13.750   1.5803   0.05193   0.04430  -0.0732   0.2277   1.0000
  14.000   1.5771   0.05483   0.04721  -0.0722   0.2124   1.0000
  14.250   1.5652   0.05872   0.05104  -0.0710   0.1916   1.0000
  14.500   1.5455   0.06362   0.05586  -0.0698   0.1713   1.0000
  14.750   1.5264   0.06864   0.06082  -0.0690   0.1544   1.0000
  15.000   1.5088   0.07362   0.06580  -0.0684   0.1406   1.0000
  15.250   1.4935   0.07849   0.07068  -0.0680   0.1294   1.0000
  15.500   1.4795   0.08332   0.07554  -0.0678   0.1212   1.0000
  15.750   1.4681   0.08791   0.08017  -0.0679   0.1152   1.0000
  16.000   1.4571   0.09250   0.08482  -0.0680   0.1112   1.0000
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