Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 460 AIRFOIL (goe460-il)
Reynolds number: 500,000
Max Cl/Cd: 54.37 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe460-il-500000.txt
Download as CSV file: xf-goe460-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 460 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
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -1.0918   0.08601   0.08092  -0.0555   1.0000   0.0570
 -19.250  -1.0990   0.08216   0.07704  -0.0566   1.0000   0.0580
 -19.000  -1.1050   0.07848   0.07332  -0.0576   1.0000   0.0591
 -18.750  -1.1090   0.07512   0.06990  -0.0584   1.0000   0.0601
 -18.500  -1.1129   0.07179   0.06650  -0.0592   1.0000   0.0613
 -18.250  -1.1159   0.06858   0.06321  -0.0598   1.0000   0.0627
 -18.000  -1.1238   0.06493   0.05953  -0.0605   1.0000   0.0639
 -17.750  -1.1307   0.06146   0.05602  -0.0610   1.0000   0.0655
 -17.500  -1.1342   0.05843   0.05294  -0.0613   1.0000   0.0670
 -17.250  -1.1358   0.05565   0.05010  -0.0615   1.0000   0.0687
 -17.000  -1.1401   0.05267   0.04708  -0.0616   1.0000   0.0707
 -16.750  -1.1433   0.04988   0.04427  -0.0615   1.0000   0.0730
 -16.500  -1.1434   0.04747   0.04181  -0.0613   1.0000   0.0759
 -16.250  -1.1448   0.04501   0.03933  -0.0609   1.0000   0.0789
 -16.000  -1.1433   0.04289   0.03719  -0.0605   1.0000   0.0828
 -15.750  -1.1413   0.04089   0.03516  -0.0599   1.0000   0.0866
 -15.500  -1.1392   0.03896   0.03322  -0.0591   1.0000   0.0910
 -15.250  -1.1350   0.03729   0.03150  -0.0582   1.0000   0.0954
 -15.000  -1.1344   0.03542   0.02963  -0.0571   1.0000   0.0993
 -14.750  -1.1256   0.03426   0.02839  -0.0561   1.0000   0.1035
 -14.500  -1.1275   0.03241   0.02654  -0.0544   1.0000   0.1070
 -14.250  -1.1251   0.03096   0.02508  -0.0528   1.0000   0.1108
 -14.000  -1.1175   0.02994   0.02398  -0.0513   1.0000   0.1140
 -13.750  -1.1187   0.02847   0.02251  -0.0490   1.0000   0.1174
 -13.500  -1.1181   0.02722   0.02126  -0.0466   1.0000   0.1209
 -13.250  -1.1142   0.02626   0.02027  -0.0442   1.0000   0.1240
 -13.000  -1.1120   0.02531   0.01929  -0.0415   1.0000   0.1270
 -12.750  -1.1144   0.02426   0.01824  -0.0382   1.0000   0.1305
 -12.500  -1.1148   0.02342   0.01740  -0.0349   1.0000   0.1339
 -12.250  -1.1141   0.02272   0.01667  -0.0314   1.0000   0.1371
 -12.000  -1.1182   0.02195   0.01591  -0.0273   1.0000   0.1411
 -11.750  -1.1230   0.02129   0.01527  -0.0229   1.0000   0.1453
 -11.500  -1.1066   0.02059   0.01459  -0.0223   0.9986   0.1525
 -11.250  -1.0756   0.01990   0.01394  -0.0244   0.9957   0.1631
 -11.000  -1.0439   0.01927   0.01335  -0.0265   0.9928   0.1743
 -10.750  -1.0143   0.01868   0.01278  -0.0280   0.9894   0.1834
 -10.500  -0.9825   0.01827   0.01234  -0.0296   0.9859   0.1924
 -10.250  -0.9531   0.01769   0.01180  -0.0310   0.9827   0.2001
 -10.000  -0.9190   0.01733   0.01140  -0.0330   0.9806   0.2074
  -9.750  -0.8861   0.01684   0.01092  -0.0349   0.9788   0.2141
  -9.500  -0.8623   0.01637   0.01046  -0.0349   0.9730   0.2197
  -9.250  -0.8295   0.01606   0.01009  -0.0364   0.9698   0.2250
  -9.000  -0.7982   0.01552   0.00959  -0.0379   0.9672   0.2312
  -8.750  -0.7639   0.01507   0.00915  -0.0399   0.9654   0.2371
  -8.500  -0.7265   0.01474   0.00877  -0.0423   0.9641   0.2422
  -8.250  -0.7053   0.01428   0.00834  -0.0415   0.9567   0.2473
  -8.000  -0.6720   0.01382   0.00791  -0.0432   0.9535   0.2537
  -7.750  -0.6331   0.01347   0.00753  -0.0459   0.9513   0.2598
  -7.500  -0.5961   0.01295   0.00707  -0.0484   0.9488   0.2677
  -7.250  -0.5713   0.01261   0.00674  -0.0481   0.9404   0.2740
  -7.000  -0.5386   0.01221   0.00635  -0.0495   0.9347   0.2820
  -6.750  -0.5096   0.01183   0.00600  -0.0502   0.9276   0.2919
  -6.500  -0.4876   0.01147   0.00569  -0.0493   0.9178   0.3033
  -6.250  -0.4646   0.01114   0.00539  -0.0487   0.9088   0.3181
  -6.000  -0.4450   0.01081   0.00512  -0.0473   0.8986   0.3354
  -5.750  -0.4276   0.01054   0.00489  -0.0454   0.8884   0.3531
  -5.500  -0.4071   0.01029   0.00465  -0.0440   0.8788   0.3704
  -5.250  -0.3909   0.01011   0.00448  -0.0417   0.8679   0.3854
  -5.000  -0.3708   0.00990   0.00427  -0.0402   0.8583   0.3995
  -4.750  -0.3555   0.00976   0.00415  -0.0376   0.8474   0.4116
  -4.500  -0.3333   0.00964   0.00398  -0.0364   0.8382   0.4240
  -4.250  -0.3202   0.00951   0.00390  -0.0334   0.8271   0.4350
  -4.000  -0.2995   0.00943   0.00377  -0.0319   0.8172   0.4466
  -3.750  -0.2859   0.00935   0.00371  -0.0288   0.8047   0.4573
  -3.500  -0.2685   0.00929   0.00363  -0.0265   0.7932   0.4674
  -3.250  -0.2521   0.00924   0.00356  -0.0240   0.7804   0.4781
  -3.000  -0.2349   0.00918   0.00350  -0.0218   0.7673   0.4879
  -2.750  -0.2153   0.00914   0.00343  -0.0199   0.7554   0.4981
  -2.500  -0.1974   0.00907   0.00337  -0.0178   0.7417   0.5084
  -2.250  -0.1787   0.00905   0.00332  -0.0158   0.7275   0.5195
  -2.000  -0.1604   0.00900   0.00326  -0.0137   0.7131   0.5302
  -1.500  -0.1214   0.00896   0.00318  -0.0100   0.6853   0.5504
  -1.250  -0.1011   0.00898   0.00314  -0.0083   0.6713   0.5599
  -1.000  -0.0817   0.00897   0.00311  -0.0065   0.6571   0.5692
  -0.750  -0.0614   0.00900   0.00308  -0.0048   0.6438   0.5789
  -0.500  -0.0410   0.00898   0.00307  -0.0032   0.6317   0.5884
  -0.250  -0.0206   0.00903   0.00306  -0.0016   0.6196   0.5983
   0.000   0.0000   0.00899   0.00306   0.0000   0.6083   0.6083
   0.250   0.0206   0.00903   0.00306   0.0016   0.5983   0.6197
   0.500   0.0409   0.00898   0.00307   0.0032   0.5883   0.6318
   0.750   0.0615   0.00900   0.00308   0.0048   0.5789   0.6437
   1.000   0.0818   0.00897   0.00311   0.0065   0.5692   0.6570
   1.250   0.1012   0.00898   0.00314   0.0083   0.5599   0.6709
   1.500   0.1214   0.00896   0.00318   0.0100   0.5503   0.6852
   2.000   0.1603   0.00900   0.00326   0.0137   0.5302   0.7134
   2.250   0.1787   0.00905   0.00332   0.0158   0.5195   0.7275
   2.500   0.1975   0.00907   0.00337   0.0177   0.5086   0.7417
   2.750   0.2153   0.00914   0.00343   0.0199   0.4983   0.7554
   3.000   0.2349   0.00918   0.00350   0.0218   0.4879   0.7675
   3.250   0.2522   0.00924   0.00356   0.0240   0.4781   0.7804
   3.500   0.2686   0.00929   0.00363   0.0265   0.4674   0.7930
   3.750   0.2859   0.00935   0.00371   0.0288   0.4573   0.8048
   4.000   0.2997   0.00943   0.00377   0.0318   0.4466   0.8170
   4.250   0.3203   0.00951   0.00390   0.0334   0.4351   0.8271
   4.500   0.3334   0.00964   0.00398   0.0364   0.4239   0.8382
   4.750   0.3556   0.00976   0.00415   0.0376   0.4117   0.8475
   5.000   0.3709   0.00989   0.00427   0.0402   0.3996   0.8583
   5.250   0.3910   0.01011   0.00448   0.0417   0.3855   0.8680
   5.500   0.4071   0.01029   0.00465   0.0440   0.3702   0.8788
   5.750   0.4276   0.01055   0.00489   0.0453   0.3528   0.8882
   6.000   0.4448   0.01082   0.00511   0.0473   0.3350   0.8985
   6.250   0.4644   0.01114   0.00539   0.0487   0.3178   0.9090
   6.500   0.4877   0.01147   0.00568   0.0493   0.3032   0.9178
   6.750   0.5097   0.01183   0.00600   0.0502   0.2916   0.9276
   7.000   0.5388   0.01221   0.00635   0.0495   0.2821   0.9347
   7.250   0.5716   0.01261   0.00674   0.0481   0.2740   0.9405
   7.500   0.5965   0.01295   0.00707   0.0483   0.2674   0.9489
   7.750   0.6334   0.01347   0.00753   0.0458   0.2598   0.9513
   8.000   0.6725   0.01382   0.00791   0.0431   0.2539   0.9535
   8.250   0.7057   0.01428   0.00833   0.0415   0.2473   0.9567
   8.500   0.7270   0.01473   0.00877   0.0422   0.2422   0.9641
   8.750   0.7646   0.01507   0.00914   0.0398   0.2372   0.9655
   9.000   0.7988   0.01551   0.00958   0.0378   0.2312   0.9673
   9.250   0.8300   0.01605   0.01008   0.0363   0.2249   0.9699
   9.500   0.8628   0.01637   0.01046   0.0348   0.2194   0.9731
   9.750   0.8867   0.01684   0.01091   0.0348   0.2137   0.9789
  10.000   0.9198   0.01732   0.01139   0.0329   0.2073   0.9806
  10.250   0.9538   0.01768   0.01179   0.0309   0.2001   0.9828
  10.500   0.9833   0.01826   0.01232   0.0294   0.1924   0.9859
  10.750   1.0150   0.01867   0.01276   0.0278   0.1832   0.9895
  11.000   1.0449   0.01925   0.01334   0.0263   0.1743   0.9928
  11.250   1.0768   0.01988   0.01392   0.0242   0.1631   0.9958
  11.500   1.1074   0.02058   0.01457   0.0222   0.1521   0.9987
  11.750   1.1232   0.02126   0.01524   0.0229   0.1453   1.0000
  12.000   1.1182   0.02192   0.01588   0.0273   0.1410   1.0000
  12.250   1.1142   0.02269   0.01664   0.0314   0.1370   1.0000
  12.500   1.1151   0.02338   0.01736   0.0348   0.1339   1.0000
  12.750   1.1143   0.02424   0.01822   0.0382   0.1303   1.0000
  13.000   1.1121   0.02529   0.01926   0.0415   0.1269   1.0000
  13.250   1.1149   0.02621   0.02022   0.0442   0.1239   1.0000
  13.500   1.1184   0.02720   0.02123   0.0466   0.1205   1.0000
  13.750   1.1191   0.02844   0.02248   0.0489   0.1173   1.0000
  14.000   1.1184   0.02989   0.02393   0.0512   0.1141   1.0000
  14.250   1.1261   0.03091   0.02502   0.0527   0.1108   1.0000
  14.500   1.1289   0.03234   0.02647   0.0543   0.1072   1.0000
  14.750   1.1269   0.03419   0.02832   0.0560   0.1035   1.0000
  15.000   1.1357   0.03536   0.02956   0.0570   0.0994   1.0000
  15.250   1.1365   0.03722   0.03142   0.0581   0.0954   1.0000
  15.500   1.1410   0.03887   0.03312   0.0589   0.0909   1.0000
  15.750   1.1432   0.04079   0.03506   0.0597   0.0867   1.0000
  16.000   1.1455   0.04277   0.03707   0.0603   0.0826   1.0000
  16.250   1.1470   0.04490   0.03921   0.0607   0.0788   1.0000
  16.500   1.1459   0.04734   0.04168   0.0611   0.0757   1.0000
  16.750   1.1460   0.04974   0.04412   0.0613   0.0730   1.0000
  17.000   1.1431   0.05251   0.04691   0.0613   0.0707   1.0000
  17.250   1.1380   0.05557   0.05001   0.0612   0.0688   1.0000
  17.500   1.1375   0.05825   0.05275   0.0610   0.0670   1.0000
  17.750   1.1336   0.06133   0.05588   0.0607   0.0654   1.0000
  18.000   1.1259   0.06491   0.05949   0.0601   0.0637   1.0000
  18.250   1.1177   0.06860   0.06322   0.0595   0.0625   1.0000
  18.500   1.1160   0.07166   0.06636   0.0588   0.0614   1.0000
  18.750   1.1128   0.07491   0.06968   0.0581   0.0602   1.0000
  19.000   1.1085   0.07834   0.07317   0.0572   0.0590   1.0000
  19.250   1.1017   0.08212   0.07700   0.0562   0.0578   1.0000
<< Back to GOE 460 AIRFOIL (goe460-il)

Polar data table (+)

Polar graphs


<< Back to GOE 460 AIRFOIL (goe460-il)