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GOE 508 AIRFOIL (goe508-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 508 AIRFOIL (goe508-il)
Reynolds number: 100,000
Max Cl/Cd: 43.67 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe508-il-100000-n5.txt
Download as CSV file: xf-goe508-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 508 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  -0.0380   0.09416   0.08848  -0.1062   0.8964   0.0590
 -10.250  -0.0228   0.09102   0.08529  -0.1085   0.8886   0.0585
 -10.000  -0.0148   0.08758   0.08181  -0.1107   0.8798   0.0582
  -9.750  -0.0104   0.08366   0.07785  -0.1134   0.8712   0.0582
  -9.500  -0.0119   0.07926   0.07342  -0.1164   0.8623   0.0585
  -9.250  -0.0117   0.07532   0.06946  -0.1187   0.8536   0.0584
  -9.000  -0.0135   0.07120   0.06530  -0.1211   0.8456   0.0582
  -8.750  -0.0216   0.06675   0.06085  -0.1234   0.8363   0.0579
  -8.500  -0.0401   0.06073   0.05479  -0.1276   0.8275   0.0575
  -8.250  -0.0819   0.05397   0.04789  -0.1292   0.8166   0.0568
  -8.000  -0.1189   0.04760   0.04116  -0.1286   0.8083   0.0566
  -7.750  -0.1374   0.04344   0.03665  -0.1264   0.7997   0.0567
  -7.500  -0.1431   0.03968   0.03241  -0.1245   0.7937   0.0571
  -7.250  -0.1452   0.03685   0.02911  -0.1219   0.7864   0.0580
  -7.000  -0.1421   0.03414   0.02583  -0.1194   0.7795   0.0591
  -6.750  -0.1203   0.03316   0.02476  -0.1189   0.7747   0.0600
  -6.500  -0.1046   0.03221   0.02369  -0.1173   0.7681   0.0609
  -6.250  -0.0877   0.03108   0.02236  -0.1158   0.7617   0.0618
  -6.000  -0.0670   0.02976   0.02078  -0.1149   0.7570   0.0629
  -5.750  -0.0472   0.02857   0.01932  -0.1138   0.7519   0.0641
  -5.500  -0.0298   0.02755   0.01801  -0.1121   0.7450   0.0656
  -5.250  -0.0062   0.02684   0.01724  -0.1114   0.7399   0.0673
  -5.000   0.0208   0.02621   0.01651  -0.1112   0.7359   0.0693
  -4.750   0.0380   0.02573   0.01595  -0.1094   0.7285   0.0713
  -4.500   0.0614   0.02497   0.01497  -0.1085   0.7232   0.0736
  -4.250   0.0879   0.02441   0.01441  -0.1082   0.7192   0.0756
  -4.000   0.1100   0.02407   0.01403  -0.1072   0.7137   0.0783
  -3.750   0.1313   0.02370   0.01353  -0.1059   0.7075   0.0822
  -3.500   0.1566   0.02330   0.01317  -0.1054   0.7028   0.0857
  -3.250   0.1854   0.02281   0.01254  -0.1053   0.6993   0.0908
  -3.000   0.2022   0.02269   0.01249  -0.1035   0.6923   0.0950
  -2.750   0.2257   0.02243   0.01217  -0.1026   0.6874   0.1020
  -2.500   0.2521   0.02205   0.01181  -0.1022   0.6836   0.1096
  -2.250   0.2765   0.02176   0.01151  -0.1015   0.6794   0.1195
  -2.000   0.2947   0.02171   0.01146  -0.0998   0.6730   0.1300
  -1.750   0.3187   0.02146   0.01126  -0.0990   0.6684   0.1431
  -1.500   0.3463   0.02117   0.01097  -0.0988   0.6649   0.1584
  -1.250   0.3674   0.02111   0.01097  -0.0976   0.6602   0.1737
  -1.000   0.3863   0.02112   0.01107  -0.0961   0.6548   0.1902
  -0.750   0.4108   0.02098   0.01097  -0.0954   0.6506   0.2145
  -0.500   0.4387   0.02067   0.01080  -0.0954   0.6473   0.2554
  -0.250   0.4594   0.02051   0.01089  -0.0942   0.6427   0.3123
   0.000   0.4769   0.02031   0.01112  -0.0927   0.6375   0.4136
   0.250   0.4959   0.01967   0.01128  -0.0907   0.6337   0.6329
   0.500   0.5981   0.01927   0.01137  -0.1038   0.6310   0.9342
   0.750   0.6615   0.01929   0.01118  -0.1105   0.6278   0.9809
   1.000   0.6961   0.01971   0.01155  -0.1125   0.6215   1.0000
   1.250   0.7137   0.01987   0.01161  -0.1107   0.6164   1.0000
   1.500   0.7394   0.01983   0.01140  -0.1101   0.6122   1.0000
   1.750   0.7525   0.02013   0.01164  -0.1075   0.6063   1.0000
   2.000   0.7674   0.02035   0.01180  -0.1052   0.6000   1.0000
   2.250   0.7935   0.02030   0.01160  -0.1046   0.5952   1.0000
   2.500   0.8090   0.02055   0.01179  -0.1024   0.5895   1.0000
   2.750   0.8222   0.02083   0.01204  -0.0998   0.5830   1.0000
   3.000   0.8486   0.02078   0.01186  -0.0993   0.5778   1.0000
   3.250   0.8625   0.02105   0.01208  -0.0968   0.5714   1.0000
   3.500   0.8766   0.02129   0.01229  -0.0943   0.5646   1.0000
   3.750   0.9039   0.02126   0.01214  -0.0940   0.5597   1.0000
   4.000   0.9154   0.02164   0.01253  -0.0912   0.5538   1.0000
   4.250   0.9279   0.02200   0.01288  -0.0886   0.5479   1.0000
   4.500   0.9530   0.02205   0.01285  -0.0880   0.5429   1.0000
   4.750   0.9682   0.02235   0.01313  -0.0858   0.5374   1.0000
   5.000   0.9760   0.02281   0.01362  -0.0825   0.5307   1.0000
   5.250   0.9997   0.02289   0.01363  -0.0816   0.5255   1.0000
   5.500   1.0120   0.02324   0.01397  -0.0790   0.5197   1.0000
   5.750   1.0148   0.02378   0.01455  -0.0750   0.5128   1.0000
   6.000   1.0389   0.02384   0.01456  -0.0742   0.5073   1.0000
   6.250   1.0424   0.02446   0.01521  -0.0705   0.5002   1.0000
   6.500   1.0516   0.02495   0.01571  -0.0678   0.4929   1.0000
   6.750   1.0735   0.02506   0.01577  -0.0668   0.4865   1.0000
   7.000   1.0686   0.02609   0.01688  -0.0624   0.4770   1.0000
   7.250   1.0917   0.02612   0.01684  -0.0616   0.4699   1.0000
   7.500   1.0844   0.02743   0.01824  -0.0574   0.4591   1.0000
   7.750   1.0969   0.02795   0.01875  -0.0555   0.4501   1.0000
   8.000   1.1014   0.02891   0.01974  -0.0529   0.4394   1.0000
   8.250   1.1036   0.03010   0.02097  -0.0504   0.4281   1.0000
   8.500   1.1165   0.03071   0.02153  -0.0488   0.4177   1.0000
   8.750   1.1222   0.03179   0.02262  -0.0467   0.4055   1.0000
   9.000   1.1269   0.03302   0.02386  -0.0447   0.3928   1.0000
   9.250   1.1360   0.03399   0.02478  -0.0430   0.3803   1.0000
   9.500   1.1480   0.03477   0.02548  -0.0416   0.3685   1.0000
   9.750   1.1577   0.03578   0.02642  -0.0401   0.3567   1.0000
  10.000   1.1660   0.03696   0.02758  -0.0386   0.3457   1.0000
  10.250   1.1794   0.03777   0.02830  -0.0374   0.3367   1.0000
  10.500   1.1888   0.03895   0.02946  -0.0361   0.3277   1.0000
  10.750   1.2011   0.03991   0.03035  -0.0350   0.3198   1.0000
  11.000   1.2102   0.04117   0.03160  -0.0338   0.3119   1.0000
  11.250   1.2243   0.04203   0.03238  -0.0328   0.3052   1.0000
  11.500   1.2321   0.04348   0.03388  -0.0317   0.2982   1.0000
  11.750   1.2462   0.04437   0.03470  -0.0308   0.2923   1.0000
  12.000   1.2582   0.04551   0.03585  -0.0300   0.2870   1.0000
  12.250   1.2677   0.04690   0.03731  -0.0291   0.2816   1.0000
  12.500   1.2819   0.04785   0.03823  -0.0283   0.2768   1.0000
  12.750   1.2983   0.04864   0.03899  -0.0277   0.2724   1.0000
  13.000   1.3041   0.05042   0.04088  -0.0268   0.2676   1.0000
  13.250   1.3134   0.05186   0.04238  -0.0261   0.2629   1.0000
  13.500   1.3301   0.05260   0.04307  -0.0255   0.2584   1.0000
  13.750   1.3393   0.05410   0.04463  -0.0248   0.2543   1.0000
  14.000   1.3429   0.05616   0.04682  -0.0241   0.2500   1.0000
  14.250   1.3499   0.05788   0.04861  -0.0235   0.2455   1.0000
  14.500   1.3654   0.05874   0.04945  -0.0230   0.2416   1.0000
  14.750   1.3756   0.06021   0.05097  -0.0225   0.2380   1.0000
  15.000   1.3734   0.06296   0.05391  -0.0219   0.2341   1.0000
  15.250   1.3763   0.06521   0.05627  -0.0215   0.2301   1.0000
  15.500   1.3861   0.06671   0.05782  -0.0211   0.2264   1.0000
  15.750   1.4083   0.06685   0.05787  -0.0207   0.2228   1.0000
  16.000   1.3938   0.07110   0.06239  -0.0205   0.2191   1.0000
  16.250   1.3868   0.07461   0.06607  -0.0204   0.2151   1.0000
  16.500   1.3888   0.07709   0.06865  -0.0203   0.2113   1.0000
  16.750   1.4026   0.07808   0.06963  -0.0200   0.2077   1.0000
  17.000   1.3947   0.08185   0.07357  -0.0202   0.2040   1.0000
  17.250   1.3718   0.08770   0.07966  -0.0210   0.1995   1.0000
  17.500   1.3660   0.09137   0.08345  -0.0215   0.1954   1.0000
  17.750   1.3790   0.09244   0.08453  -0.0214   0.1921   1.0000
  18.000   1.3540   0.09898   0.09128  -0.0229   0.1880   1.0000
  18.250   1.3007   0.11012   0.10271  -0.0261   0.1820   1.0000
  18.500   1.3070   0.11224   0.10487  -0.0266   0.1787   1.0000
  18.750   1.3350   0.11092   0.10354  -0.0258   0.1764   1.0000
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