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

GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 645 AIRFOIL (goe645-il)
Reynolds number: 500,000
Max Cl/Cd: 93.48 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe645-il-500000.txt
Download as CSV file: xf-goe645-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 645 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.6378   0.08891   0.08592  -0.0589   1.0000   0.0288
 -15.000  -0.7021   0.07466   0.07141  -0.0688   1.0000   0.0286
 -14.750  -0.7371   0.06622   0.06281  -0.0748   1.0000   0.0286
 -14.500  -0.7649   0.05920   0.05563  -0.0798   1.0000   0.0287
 -14.250  -0.7851   0.05341   0.04971  -0.0839   1.0000   0.0287
 -14.000  -0.8035   0.04790   0.04405  -0.0880   1.0000   0.0289
 -13.750  -0.8193   0.04279   0.03879  -0.0922   1.0000   0.0290
 -13.500  -0.8354   0.03830   0.03412  -0.0962   1.0000   0.0292
 -13.250  -0.8543   0.03577   0.03146  -0.0955   1.0000   0.0292
 -13.000  -0.8743   0.03441   0.02999  -0.0910   1.0000   0.0293
 -12.750  -0.8848   0.03234   0.02785  -0.0876   1.0000   0.0296
 -12.500  -0.8877   0.03099   0.02649  -0.0844   1.0000   0.0300
 -12.250  -0.8813   0.02993   0.02540  -0.0824   0.9995   0.0304
 -12.000  -0.8469   0.02858   0.02400  -0.0855   0.9959   0.0310
 -11.750  -0.8123   0.02729   0.02261  -0.0886   0.9921   0.0319
 -11.500  -0.7799   0.02607   0.02125  -0.0909   0.9869   0.0328
 -11.250  -0.7445   0.02500   0.01998  -0.0936   0.9829   0.0336
 -11.000  -0.7168   0.02329   0.01818  -0.0950   0.9765   0.0345
 -10.750  -0.6840   0.02214   0.01703  -0.0968   0.9713   0.0352
 -10.500  -0.6520   0.02123   0.01608  -0.0982   0.9648   0.0361
 -10.250  -0.6197   0.02038   0.01515  -0.0996   0.9574   0.0371
 -10.000  -0.5853   0.01963   0.01429  -0.1013   0.9492   0.0382
  -9.750  -0.5486   0.01878   0.01331  -0.1034   0.9409   0.0390
  -9.500  -0.5158   0.01753   0.01205  -0.1051   0.9284   0.0402
  -9.250  -0.4803   0.01678   0.01126  -0.1070   0.9142   0.0413
  -9.000  -0.4475   0.01621   0.01058  -0.1081   0.8969   0.0426
  -8.750  -0.4190   0.01575   0.00997  -0.1082   0.8782   0.0437
  -8.500  -0.3928   0.01538   0.00946  -0.1078   0.8601   0.0445
  -8.250  -0.3721   0.01459   0.00858  -0.1067   0.8428   0.0458
  -8.000  -0.3488   0.01414   0.00805  -0.1058   0.8279   0.0471
  -7.750  -0.3247   0.01379   0.00760  -0.1050   0.8146   0.0486
  -7.500  -0.3004   0.01348   0.00718  -0.1041   0.8019   0.0500
  -7.250  -0.2767   0.01306   0.00667  -0.1032   0.7899   0.0515
  -7.000  -0.2533   0.01261   0.00615  -0.1023   0.7788   0.0536
  -6.750  -0.2286   0.01229   0.00576  -0.1016   0.7677   0.0559
  -6.500  -0.2036   0.01197   0.00536  -0.1008   0.7578   0.0590
  -6.250  -0.1790   0.01160   0.00495  -0.1001   0.7476   0.0637
  -6.000  -0.1541   0.01123   0.00461  -0.0994   0.7376   0.0738
  -5.750  -0.1286   0.01097   0.00443  -0.0987   0.7276   0.1001
  -5.500  -0.1022   0.01081   0.00427  -0.0982   0.7174   0.1146
  -5.250  -0.0759   0.01069   0.00409  -0.0977   0.7078   0.1241
  -5.000  -0.0492   0.01057   0.00393  -0.0972   0.6975   0.1314
  -4.750  -0.0230   0.01043   0.00375  -0.0967   0.6874   0.1382
  -4.500   0.0033   0.01032   0.00361  -0.0961   0.6762   0.1450
  -4.250   0.0297   0.01019   0.00346  -0.0956   0.6652   0.1530
  -4.000   0.0560   0.01012   0.00333  -0.0950   0.6543   0.1615
  -3.750   0.0824   0.00998   0.00322  -0.0945   0.6424   0.1731
  -3.500   0.1087   0.00990   0.00314  -0.0940   0.6307   0.1878
  -3.250   0.1348   0.00985   0.00307  -0.0934   0.6183   0.2043
  -3.000   0.1613   0.00982   0.00303  -0.0929   0.6051   0.2198
  -2.750   0.1879   0.00982   0.00301  -0.0923   0.5920   0.2338
  -2.500   0.2143   0.00987   0.00299  -0.0918   0.5788   0.2461
  -2.250   0.2406   0.00995   0.00300  -0.0912   0.5658   0.2578
  -2.000   0.2670   0.00997   0.00299  -0.0907   0.5531   0.2665
  -1.750   0.2936   0.01003   0.00298  -0.0902   0.5407   0.2738
  -1.500   0.3198   0.01009   0.00296  -0.0896   0.5291   0.2800
  -1.250   0.3461   0.01012   0.00296  -0.0891   0.5184   0.2865
  -1.000   0.3730   0.01018   0.00296  -0.0887   0.5094   0.2927
  -0.750   0.3995   0.01022   0.00295  -0.0882   0.5009   0.2984
  -0.500   0.4260   0.01024   0.00297  -0.0878   0.4930   0.3047
  -0.250   0.4527   0.01030   0.00298  -0.0873   0.4848   0.3109
   0.000   0.4789   0.01035   0.00299  -0.0868   0.4770   0.3172
   0.250   0.5055   0.01036   0.00302  -0.0864   0.4693   0.3242
   0.750   0.5583   0.01045   0.00308  -0.0855   0.4557   0.3393
   1.000   0.5845   0.01051   0.00312  -0.0850   0.4489   0.3469
   1.250   0.6106   0.01055   0.00316  -0.0845   0.4428   0.3549
   1.500   0.6371   0.01058   0.00321  -0.0841   0.4364   0.3647
   1.750   0.6626   0.01063   0.00327  -0.0835   0.4301   0.3764
   2.000   0.6886   0.01066   0.00334  -0.0830   0.4242   0.3911
   2.250   0.7144   0.01067   0.00341  -0.0825   0.4179   0.4086
   2.500   0.7389   0.01072   0.00349  -0.0818   0.4116   0.4329
   2.750   0.7639   0.01064   0.00359  -0.0811   0.4057   0.4799
   3.000   0.7863   0.01046   0.00372  -0.0800   0.3994   0.5881
   3.250   0.8629   0.00988   0.00402  -0.0903   0.3898   1.0000
   3.500   0.8867   0.01001   0.00411  -0.0894   0.3830   1.0000
   3.750   0.9094   0.01020   0.00422  -0.0883   0.3762   1.0000
   4.000   0.9335   0.01032   0.00432  -0.0874   0.3684   1.0000
   4.250   0.9557   0.01052   0.00445  -0.0863   0.3605   1.0000
   4.500   0.9797   0.01066   0.00457  -0.0854   0.3529   1.0000
   4.750   1.0017   0.01087   0.00471  -0.0842   0.3447   1.0000
   5.000   1.0252   0.01103   0.00485  -0.0833   0.3367   1.0000
   5.250   1.0468   0.01127   0.00502  -0.0821   0.3281   1.0000
   5.500   1.0699   0.01145   0.00519  -0.0812   0.3202   1.0000
   6.000   1.1134   0.01191   0.00558  -0.0788   0.3041   1.0000
   6.500   1.1556   0.01242   0.00602  -0.0763   0.2894   1.0000
   6.750   1.1755   0.01271   0.00627  -0.0749   0.2822   1.0000
   7.000   1.1960   0.01298   0.00652  -0.0736   0.2761   1.0000
   7.250   1.2161   0.01325   0.00678  -0.0722   0.2702   1.0000
   7.500   1.2333   0.01358   0.00707  -0.0703   0.2650   1.0000
   7.750   1.2520   0.01383   0.00733  -0.0687   0.2597   1.0000
   8.000   1.2696   0.01412   0.00762  -0.0669   0.2551   1.0000
   8.250   1.2856   0.01447   0.00795  -0.0649   0.2508   1.0000
   8.500   1.3033   0.01478   0.00828  -0.0632   0.2469   1.0000
   8.750   1.3217   0.01508   0.00860  -0.0616   0.2429   1.0000
   9.000   1.3386   0.01543   0.00897  -0.0599   0.2388   1.0000
   9.250   1.3536   0.01588   0.00940  -0.0580   0.2347   1.0000
   9.500   1.3714   0.01623   0.00979  -0.0565   0.2313   1.0000
   9.750   1.3888   0.01660   0.01020  -0.0550   0.2270   1.0000
  10.000   1.4038   0.01709   0.01069  -0.0533   0.2222   1.0000
  10.250   1.4174   0.01766   0.01126  -0.0514   0.2177   1.0000
  10.500   1.4347   0.01809   0.01174  -0.0501   0.2131   1.0000
  10.750   1.4483   0.01870   0.01237  -0.0485   0.2074   1.0000
  11.000   1.4609   0.01940   0.01307  -0.0468   0.2015   1.0000
  11.250   1.4748   0.02007   0.01376  -0.0453   0.1940   1.0000
  11.500   1.4855   0.02094   0.01463  -0.0437   0.1860   1.0000
  11.750   1.4953   0.02193   0.01561  -0.0421   0.1758   1.0000
  12.000   1.5034   0.02309   0.01674  -0.0405   0.1632   1.0000
  12.250   1.5069   0.02463   0.01822  -0.0388   0.1501   1.0000
  12.500   1.5118   0.02617   0.01974  -0.0373   0.1436   1.0000
  12.750   1.5164   0.02781   0.02139  -0.0361   0.1392   1.0000
  13.000   1.5207   0.02954   0.02316  -0.0349   0.1358   1.0000
  13.250   1.5257   0.03129   0.02496  -0.0340   0.1335   1.0000
  13.500   1.5299   0.03315   0.02687  -0.0331   0.1316   1.0000
  13.750   1.5325   0.03521   0.02898  -0.0323   0.1297   1.0000
  14.000   1.5341   0.03741   0.03124  -0.0316   0.1282   1.0000
  14.250   1.5342   0.03982   0.03370  -0.0310   0.1267   1.0000
  14.500   1.5319   0.04252   0.03645  -0.0304   0.1247   1.0000
  14.750   1.5350   0.04476   0.03878  -0.0301   0.1235   1.0000
  15.000   1.5383   0.04703   0.04114  -0.0299   0.1222   1.0000
  15.250   1.5391   0.04959   0.04379  -0.0297   0.1206   1.0000
  15.500   1.5386   0.05236   0.04663  -0.0296   0.1193   1.0000
  15.750   1.5373   0.05526   0.04961  -0.0295   0.1181   1.0000
  16.000   1.5332   0.05849   0.05290  -0.0296   0.1165   1.0000
  16.250   1.5301   0.06166   0.05612  -0.0297   0.1152   1.0000
  16.500   1.5262   0.06491   0.05942  -0.0299   0.1136   1.0000
  16.750   1.5243   0.06794   0.06251  -0.0300   0.1118   1.0000
  17.000   1.5255   0.07080   0.06549  -0.0304   0.1106   1.0000
  17.250   1.5252   0.07384   0.06863  -0.0309   0.1089   1.0000
  17.500   1.5223   0.07725   0.07213  -0.0314   0.1067   1.0000
  17.750   1.5182   0.08079   0.07574  -0.0321   0.1050   1.0000
  18.000   1.5124   0.08453   0.07952  -0.0327   0.1031   1.0000
  18.250   1.5072   0.08815   0.08317  -0.0333   0.1009   1.0000
  18.500   1.5052   0.09163   0.08677  -0.0342   0.0991   1.0000
  18.750   1.5043   0.09503   0.09029  -0.0351   0.0970   1.0000
  19.000   1.4997   0.09896   0.09431  -0.0363   0.0938   1.0000
  19.250   1.4907   0.10345   0.09885  -0.0376   0.0909   1.0000
<< Back to GOE 645 AIRFOIL (goe645-il)

Polar data table (+)

Polar graphs


<< Back to GOE 645 AIRFOIL (goe645-il)