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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 500,000
Max Cl/Cd: 120.71 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe450-il-500000.txt
Download as CSV file: xf-goe450-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1748   0.08426   0.08209  -0.0569   0.9869   0.0224
  -8.750  -0.1637   0.08022   0.07804  -0.0599   0.9855   0.0231
  -8.500  -0.1526   0.07592   0.07374  -0.0633   0.9843   0.0241
  -8.250  -0.1478   0.07110   0.06892  -0.0692   0.9806   0.0254
  -8.000  -0.1409   0.06621   0.06403  -0.0749   0.9760   0.0256
  -7.750  -0.1307   0.06116   0.05897  -0.0808   0.9719   0.0257
  -7.500  -0.1277   0.05574   0.05356  -0.0832   0.9654   0.0261
  -7.250  -0.1145   0.05279   0.05061  -0.0837   0.9608   0.0265
  -7.000  -0.0996   0.04980   0.04760  -0.0855   0.9567   0.0270
  -6.750  -0.0901   0.04663   0.04442  -0.0878   0.9481   0.0276
  -6.500  -0.0764   0.04279   0.04054  -0.0917   0.9422   0.0285
  -6.250  -0.0626   0.03867   0.03638  -0.0961   0.9336   0.0299
  -6.000  -0.0311   0.03104   0.02848  -0.1092   0.9277   0.0318
  -5.750  -0.0207   0.02469   0.02201  -0.1125   0.9202   0.0325
  -5.500  -0.0036   0.02301   0.02031  -0.1123   0.9139   0.0332
  -5.250   0.0160   0.02097   0.01820  -0.1131   0.9072   0.0341
  -5.000   0.0381   0.01834   0.01543  -0.1147   0.9006   0.0358
  -4.750   0.0674   0.01286   0.00926  -0.1188   0.8957   0.0401
  -4.500   0.0873   0.01100   0.00739  -0.1191   0.8881   0.0412
  -4.250   0.1106   0.01000   0.00632  -0.1193   0.8820   0.0425
  -4.000   0.1345   0.00897   0.00517  -0.1194   0.8739   0.0451
  -3.750   0.1609   0.00702   0.00271  -0.1201   0.8677   0.0510
  -3.500   0.1849   0.00635   0.00202  -0.1201   0.8590   0.0527
  -3.250   0.2106   0.00576   0.00129  -0.1201   0.8515   0.0559
  -3.000   0.2367   0.00497   0.00018  -0.1202   0.8419   0.0631
  -2.250   0.3310   0.01184   0.00577  -0.1247   0.8351   0.0418
  -2.000   0.3584   0.01126   0.00504  -0.1243   0.8243   0.0409
  -1.750   0.3857   0.01078   0.00447  -0.1240   0.8130   0.0407
  -1.500   0.4128   0.01024   0.00386  -0.1237   0.8020   0.0411
  -1.250   0.4400   0.00983   0.00339  -0.1235   0.7910   0.0419
  -1.000   0.4672   0.00950   0.00300  -0.1232   0.7791   0.0421
  -0.750   0.4944   0.00923   0.00269  -0.1230   0.7675   0.0428
  -0.500   0.5218   0.00904   0.00245  -0.1228   0.7562   0.0437
  -0.250   0.5491   0.00891   0.00226  -0.1226   0.7450   0.0449
   0.000   0.5765   0.00881   0.00211  -0.1224   0.7336   0.0463
   0.250   0.6040   0.00875   0.00200  -0.1223   0.7227   0.0479
   0.500   0.6314   0.00870   0.00191  -0.1221   0.7123   0.0516
   1.000   0.6856   0.00820   0.00193  -0.1221   0.6909   0.2750
   1.250   0.7098   0.00671   0.00211  -0.1215   0.6802   1.0000
   1.500   0.7367   0.00684   0.00213  -0.1212   0.6690   1.0000
   1.750   0.7636   0.00697   0.00217  -0.1210   0.6578   1.0000
   2.000   0.7904   0.00709   0.00222  -0.1207   0.6463   1.0000
   2.250   0.8172   0.00722   0.00229  -0.1205   0.6347   1.0000
   2.500   0.8438   0.00737   0.00236  -0.1202   0.6242   1.0000
   2.750   0.8706   0.00750   0.00245  -0.1200   0.6137   1.0000
   3.000   0.8970   0.00764   0.00255  -0.1197   0.6005   1.0000
   3.250   0.9231   0.00779   0.00264  -0.1194   0.5858   1.0000
   3.500   0.9491   0.00795   0.00275  -0.1190   0.5708   1.0000
   3.750   0.9749   0.00812   0.00286  -0.1186   0.5544   1.0000
   4.000   1.0006   0.00830   0.00300  -0.1182   0.5382   1.0000
   4.250   1.0260   0.00850   0.00315  -0.1178   0.5214   1.0000
   4.500   1.0508   0.00874   0.00331  -0.1173   0.4994   1.0000
   4.750   1.0745   0.00905   0.00351  -0.1165   0.4725   1.0000
   5.000   1.0978   0.00940   0.00373  -0.1158   0.4449   1.0000
   5.250   1.1216   0.00973   0.00398  -0.1151   0.4209   1.0000
   5.500   1.1447   0.01011   0.00425  -0.1144   0.3969   1.0000
   5.750   1.1677   0.01050   0.00456  -0.1136   0.3717   1.0000
   6.000   1.1900   0.01094   0.00488  -0.1128   0.3427   1.0000
   6.250   1.2105   0.01152   0.00527  -0.1116   0.3035   1.0000
   6.500   1.2272   0.01241   0.00581  -0.1100   0.2374   1.0000
   6.750   1.2374   0.01387   0.00675  -0.1074   0.1530   1.0000
   7.000   1.2475   0.01530   0.00770  -0.1047   0.0769   1.0000
   7.250   1.2629   0.01623   0.00846  -0.1028   0.0476   1.0000
   7.500   1.2808   0.01693   0.00911  -0.1012   0.0404   1.0000
   7.750   1.2996   0.01751   0.00977  -0.0998   0.0379   1.0000
   8.000   1.3161   0.01822   0.01052  -0.0980   0.0354   1.0000
   8.250   1.3270   0.01914   0.01150  -0.0952   0.0329   1.0000
   8.500   1.3406   0.01988   0.01232  -0.0930   0.0315   1.0000
   8.750   1.3544   0.02062   0.01312  -0.0909   0.0301   1.0000
   9.000   1.3661   0.02149   0.01408  -0.0885   0.0287   1.0000
   9.250   1.3757   0.02252   0.01516  -0.0860   0.0274   1.0000
   9.500   1.3793   0.02399   0.01669  -0.0828   0.0261   1.0000
   9.750   1.3807   0.02570   0.01850  -0.0794   0.0250   1.0000
  10.000   1.3946   0.02652   0.01941  -0.0779   0.0242   1.0000
  10.250   1.4050   0.02765   0.02061  -0.0759   0.0232   1.0000
  10.500   1.4140   0.02891   0.02195  -0.0739   0.0223   1.0000
  10.750   1.4221   0.03028   0.02338  -0.0720   0.0215   1.0000
  11.000   1.4282   0.03186   0.02500  -0.0700   0.0208   1.0000
  11.250   1.4279   0.03410   0.02729  -0.0674   0.0200   1.0000
  11.500   1.4325   0.03602   0.02931  -0.0653   0.0194   1.0000
  11.750   1.4428   0.03732   0.03072  -0.0640   0.0188   1.0000
  12.000   1.4513   0.03885   0.03236  -0.0626   0.0181   1.0000
  12.250   1.4587   0.04052   0.03411  -0.0613   0.0175   1.0000
  12.500   1.4654   0.04230   0.03597  -0.0599   0.0169   1.0000
  12.750   1.4713   0.04414   0.03788  -0.0587   0.0165   1.0000
  13.000   1.4764   0.04611   0.03991  -0.0575   0.0160   1.0000
  13.250   1.4800   0.04835   0.04219  -0.0560   0.0156   1.0000
  13.500   1.4832   0.05088   0.04483  -0.0539   0.0151   1.0000
  13.750   1.4865   0.05313   0.04725  -0.0530   0.0149   1.0000
  14.000   1.4891   0.05554   0.04982  -0.0521   0.0145   1.0000
  14.250   1.4907   0.05811   0.05253  -0.0513   0.0141   1.0000
  14.500   1.4916   0.06081   0.05537  -0.0506   0.0138   1.0000
  14.750   1.4919   0.06362   0.05831  -0.0501   0.0134   1.0000
  15.000   1.4915   0.06659   0.06140  -0.0499   0.0131   1.0000
  15.250   1.4900   0.06979   0.06472  -0.0498   0.0129   1.0000
  15.500   1.4876   0.07316   0.06821  -0.0499   0.0127   1.0000
  15.750   1.4845   0.07669   0.07186  -0.0501   0.0125   1.0000
  16.000   1.4811   0.08034   0.07561  -0.0505   0.0123   1.0000
  16.250   1.4761   0.08428   0.07967  -0.0509   0.0121   1.0000
  16.500   1.4674   0.08882   0.08435  -0.0513   0.0119   1.0000
  16.750   1.4526   0.09443   0.09015  -0.0520   0.0118   1.0000
  17.000   1.4351   0.10078   0.09672  -0.0536   0.0117   1.0000
  17.250   1.4213   0.10687   0.10302  -0.0561   0.0117   1.0000
  17.500   1.4064   0.11338   0.10972  -0.0590   0.0116   1.0000
  17.750   1.3904   0.12031   0.11685  -0.0623   0.0116   1.0000
  18.000   1.3736   0.12776   0.12449  -0.0663   0.0116   1.0000
  18.250   1.3556   0.13576   0.13267  -0.0708   0.0116   1.0000
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