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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 200,000
Max Cl/Cd: 73.5 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe630-il-200000-n5.txt
Download as CSV file: xf-goe630-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 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   0.0937   0.09260   0.08848  -0.1122   0.8682   0.0382
  -9.500   0.0988   0.09012   0.08594  -0.1154   0.8550   0.0387
  -9.250   0.1018   0.08780   0.08355  -0.1180   0.8429   0.0389
  -9.000   0.1145   0.08467   0.08038  -0.1182   0.8330   0.0393
  -8.750   0.1303   0.08230   0.07795  -0.1179   0.8241   0.0401
  -8.500   0.1397   0.08020   0.07580  -0.1183   0.8142   0.0408
  -8.250   0.1469   0.07815   0.07371  -0.1187   0.8045   0.0417
  -8.000   0.1535   0.07604   0.07155  -0.1192   0.7957   0.0425
  -7.750   0.1550   0.07401   0.06951  -0.1199   0.7862   0.0442
  -7.500   0.1492   0.07213   0.06760  -0.1211   0.7777   0.0449
  -7.250   0.1461   0.07014   0.06562  -0.1226   0.7691   0.0451
  -7.000   0.1502   0.06723   0.06265  -0.1268   0.7621   0.0453
  -6.750   0.1614   0.06479   0.06022  -0.1248   0.7557   0.0458
  -6.500   0.1743   0.06295   0.05835  -0.1236   0.7492   0.0464
  -6.250   0.1862   0.06089   0.05624  -0.1242   0.7433   0.0471
  -6.000   0.1973   0.05866   0.05400  -0.1255   0.7365   0.0477
  -5.750   0.2104   0.05627   0.05155  -0.1274   0.7301   0.0483
  -5.500   0.2250   0.05377   0.04899  -0.1296   0.7241   0.0490
  -5.250   0.2498   0.04937   0.04439  -0.1385   0.7173   0.0526
  -5.000   0.2630   0.04528   0.04019  -0.1391   0.7119   0.0447
  -4.750   0.2799   0.04339   0.03826  -0.1392   0.7057   0.0436
  -4.250   0.3251   0.03115   0.02521  -0.1470   0.6946   0.0393
  -4.000   0.3470   0.03060   0.02465  -0.1467   0.6878   0.0399
  -3.750   0.3697   0.02921   0.02311  -0.1468   0.6810   0.0407
  -3.500   0.3932   0.02671   0.02029  -0.1471   0.6751   0.0413
  -3.250   0.4155   0.02387   0.01703  -0.1470   0.6681   0.0412
  -3.000   0.4392   0.02197   0.01474  -0.1466   0.6617   0.0415
  -2.750   0.4630   0.02056   0.01301  -0.1461   0.6547   0.0420
  -2.500   0.4873   0.01943   0.01157  -0.1455   0.6472   0.0426
  -2.250   0.5123   0.01859   0.01042  -0.1448   0.6402   0.0440
  -2.000   0.5371   0.01788   0.00942  -0.1441   0.6319   0.0450
  -1.750   0.5621   0.01722   0.00856  -0.1435   0.6242   0.0456
  -1.500   0.5866   0.01671   0.00797  -0.1428   0.6155   0.0464
  -1.250   0.6115   0.01633   0.00749  -0.1422   0.6074   0.0472
  -1.000   0.6361   0.01599   0.00706  -0.1415   0.5980   0.0483
  -0.750   0.6607   0.01570   0.00668  -0.1407   0.5888   0.0496
  -0.500   0.6851   0.01550   0.00636  -0.1400   0.5793   0.0517
  -0.250   0.7092   0.01527   0.00606  -0.1392   0.5694   0.0535
   0.000   0.7330   0.01506   0.00582  -0.1383   0.5604   0.0552
   0.250   0.7567   0.01492   0.00565  -0.1375   0.5504   0.0572
   0.500   0.7801   0.01484   0.00550  -0.1366   0.5408   0.0597
   0.750   0.8032   0.01478   0.00537  -0.1356   0.5309   0.0628
   1.000   0.8263   0.01475   0.00533  -0.1347   0.5213   0.0674
   1.250   0.8492   0.01479   0.00527  -0.1337   0.5123   0.0722
   1.500   0.8722   0.01478   0.00529  -0.1328   0.5034   0.0796
   1.750   0.8947   0.01483   0.00531  -0.1318   0.4954   0.0926
   2.000   0.9173   0.01483   0.00539  -0.1308   0.4870   0.1242
   2.250   0.9385   0.01479   0.00554  -0.1297   0.4794   0.2199
   2.500   0.9593   0.01448   0.00577  -0.1287   0.4714   0.4524
   3.000   1.0340   0.01419   0.00615  -0.1331   0.4551   1.0000
   3.250   1.0556   0.01447   0.00630  -0.1320   0.4488   1.0000
   3.500   1.0779   0.01471   0.00649  -0.1310   0.4428   1.0000
   3.750   1.0996   0.01498   0.00668  -0.1299   0.4367   1.0000
   4.000   1.1206   0.01528   0.00688  -0.1288   0.4314   1.0000
   4.250   1.1422   0.01554   0.00710  -0.1277   0.4256   1.0000
   4.500   1.1631   0.01583   0.00734  -0.1266   0.4201   1.0000
   4.750   1.1832   0.01615   0.00758  -0.1253   0.4151   1.0000
   5.000   1.2038   0.01643   0.00785  -0.1241   0.4102   1.0000
   5.250   1.2235   0.01672   0.00813  -0.1228   0.4055   1.0000
   5.500   1.2427   0.01705   0.00841  -0.1213   0.4013   1.0000
   5.750   1.2620   0.01740   0.00871  -0.1200   0.3976   1.0000
   6.000   1.2817   0.01771   0.00905  -0.1187   0.3936   1.0000
   6.250   1.3008   0.01804   0.00939  -0.1173   0.3894   1.0000
   6.500   1.3194   0.01841   0.00974  -0.1159   0.3855   1.0000
   6.750   1.3384   0.01881   0.01010  -0.1146   0.3820   1.0000
   7.000   1.3571   0.01916   0.01050  -0.1133   0.3782   1.0000
   7.250   1.3759   0.01954   0.01092  -0.1121   0.3746   1.0000
   7.500   1.3945   0.01995   0.01134  -0.1108   0.3714   1.0000
   7.750   1.4131   0.02037   0.01177  -0.1096   0.3683   1.0000
   8.000   1.4328   0.02082   0.01219  -0.1086   0.3656   1.0000
   8.250   1.4508   0.02125   0.01270  -0.1073   0.3626   1.0000
   8.500   1.4683   0.02171   0.01324  -0.1060   0.3594   1.0000
   8.750   1.4853   0.02219   0.01377  -0.1047   0.3560   1.0000
   9.000   1.5027   0.02269   0.01429  -0.1035   0.3531   1.0000
   9.250   1.5215   0.02319   0.01479  -0.1025   0.3506   1.0000
   9.500   1.5399   0.02371   0.01537  -0.1014   0.3481   1.0000
   9.750   1.5554   0.02428   0.01606  -0.1000   0.3452   1.0000
  10.000   1.5706   0.02488   0.01675  -0.0987   0.3421   1.0000
  10.250   1.5862   0.02548   0.01743  -0.0974   0.3392   1.0000
  10.500   1.6025   0.02608   0.01808  -0.0962   0.3366   1.0000
  10.750   1.6199   0.02667   0.01866  -0.0952   0.3334   1.0000
  11.000   1.6288   0.02751   0.01965  -0.0932   0.3293   1.0000
  11.250   1.6372   0.02839   0.02065  -0.0913   0.3245   1.0000
  11.500   1.6468   0.02925   0.02152  -0.0896   0.3196   1.0000
  11.750   1.6554   0.03022   0.02258  -0.0878   0.3148   1.0000
  12.000   1.6614   0.03137   0.02387  -0.0860   0.3095   1.0000
  12.250   1.6680   0.03250   0.02504  -0.0843   0.3041   1.0000
  12.500   1.6744   0.03374   0.02636  -0.0826   0.2989   1.0000
  12.750   1.6795   0.03513   0.02789  -0.0811   0.2934   1.0000
  13.000   1.6834   0.03659   0.02939  -0.0794   0.2874   1.0000
  13.250   1.6867   0.03823   0.03117  -0.0780   0.2812   1.0000
  13.500   1.6885   0.04003   0.03305  -0.0765   0.2745   1.0000
  13.750   1.6897   0.04198   0.03508  -0.0752   0.2675   1.0000
  14.000   1.6891   0.04417   0.03737  -0.0739   0.2596   1.0000
  14.250   1.6871   0.04660   0.03989  -0.0727   0.2506   1.0000
  14.500   1.6818   0.04943   0.04278  -0.0716   0.2403   1.0000
  14.750   1.6765   0.05242   0.04584  -0.0707   0.2294   1.0000
  15.000   1.6694   0.05574   0.04921  -0.0698   0.2171   1.0000
  15.250   1.6560   0.05984   0.05333  -0.0691   0.2021   1.0000
  15.500   1.6380   0.06470   0.05816  -0.0686   0.1860   1.0000
  15.750   1.6145   0.07043   0.06387  -0.0684   0.1686   1.0000
  16.000   1.5926   0.07621   0.06964  -0.0685   0.1547   1.0000
  16.250   1.5707   0.08220   0.07565  -0.0689   0.1416   1.0000
  16.500   1.5470   0.08863   0.08209  -0.0696   0.1275   1.0000
  16.750   1.5230   0.09528   0.08875  -0.0706   0.1137   1.0000
  17.000   1.4989   0.10213   0.09560  -0.0719   0.1004   1.0000
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