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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.91 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe264-il-1000000.txt
Download as CSV file: xf-goe264-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3253   0.09617   0.09464  -0.0220   1.0000   0.0136
  -8.000  -0.3211   0.09300   0.09150  -0.0234   1.0000   0.0136
  -7.750  -0.3156   0.08972   0.08823  -0.0255   0.9975   0.0137
  -7.500  -0.3002   0.08529   0.08380  -0.0295   0.9928   0.0142
  -7.250  -0.2794   0.08229   0.08080  -0.0337   0.9863   0.0145
  -7.000  -0.2590   0.07907   0.07757  -0.0383   0.9782   0.0151
  -6.750  -0.2400   0.07574   0.07422  -0.0427   0.9685   0.0163
  -6.500  -0.2150   0.07043   0.06886  -0.0518   0.9561   0.0176
  -6.250  -0.1952   0.06585   0.06423  -0.0568   0.9451   0.0177
  -6.000  -0.1815   0.06252   0.06086  -0.0583   0.9352   0.0168
  -5.750  -0.1569   0.05765   0.05591  -0.0642   0.9247   0.0161
  -5.500  -0.1231   0.05023   0.04835  -0.0737   0.9136   0.0168
  -5.250  -0.0879   0.04396   0.04193  -0.0815   0.9023   0.0185
  -5.000  -0.0647   0.04358   0.04149  -0.0817   0.8893   0.0192
  -4.750  -0.0335   0.04021   0.03799  -0.0855   0.8762   0.0203
  -4.500   0.0124   0.03141   0.02882  -0.0945   0.8650   0.0236
  -4.250   0.0359   0.03198   0.02935  -0.0940   0.8498   0.0243
  -4.000   0.0935   0.01505   0.01120  -0.1057   0.8423   0.0303
  -3.750   0.1209   0.01521   0.01130  -0.1056   0.8266   0.0310
  -3.500   0.1483   0.01534   0.01137  -0.1055   0.8104   0.0318
  -3.250   0.1773   0.01459   0.01043  -0.1059   0.7936   0.0330
  -3.000   0.2085   0.01262   0.00804  -0.1069   0.7746   0.0343
  -2.750   0.2377   0.01190   0.00705  -0.1072   0.7499   0.0353
  -2.500   0.2661   0.01178   0.00674  -0.1073   0.7163   0.0362
  -2.000   0.3239   0.01077   0.00515  -0.1078   0.6512   0.0372
  -1.750   0.3535   0.00972   0.00383  -0.1084   0.6320   0.0382
  -1.500   0.3824   0.00937   0.00338  -0.1086   0.6164   0.0393
  -1.250   0.4111   0.00923   0.00316  -0.1088   0.6026   0.0404
  -0.750   0.4686   0.00902   0.00282  -0.1091   0.5774   0.0432
  -0.500   0.4974   0.00890   0.00264  -0.1093   0.5651   0.0444
  -0.250   0.5261   0.00879   0.00247  -0.1094   0.5523   0.0453
   0.000   0.5548   0.00873   0.00234  -0.1096   0.5395   0.0462
   0.250   0.5834   0.00871   0.00228  -0.1097   0.5265   0.0469
   0.500   0.6125   0.00848   0.00196  -0.1100   0.5128   0.0496
   0.750   0.6412   0.00845   0.00188  -0.1102   0.4974   0.0530
   1.000   0.6696   0.00848   0.00185  -0.1103   0.4801   0.0558
   1.250   0.6980   0.00853   0.00183  -0.1104   0.4640   0.0581
   1.500   0.7264   0.00859   0.00183  -0.1106   0.4501   0.0603
   1.750   0.7549   0.00861   0.00182  -0.1107   0.4382   0.0685
   2.000   0.7833   0.00866   0.00188  -0.1109   0.4262   0.0861
   2.250   0.8116   0.00870   0.00198  -0.1110   0.4142   0.1289
   2.500   0.8398   0.00877   0.00207  -0.1112   0.4040   0.1479
   2.750   0.8679   0.00886   0.00216  -0.1113   0.3948   0.1643
   3.000   0.8961   0.00893   0.00227  -0.1114   0.3854   0.1893
   3.250   0.9246   0.00891   0.00242  -0.1117   0.3770   0.2839
   3.500   0.9470   0.00774   0.00261  -0.1109   0.3688   1.0000
   3.750   0.9751   0.00786   0.00271  -0.1110   0.3613   1.0000
   4.000   1.0029   0.00803   0.00283  -0.1110   0.3537   1.0000
   4.250   1.0307   0.00818   0.00295  -0.1111   0.3434   1.0000
   4.500   1.0583   0.00836   0.00309  -0.1111   0.3313   1.0000
   4.750   1.0857   0.00856   0.00323  -0.1112   0.3180   1.0000
   5.000   1.1130   0.00877   0.00339  -0.1112   0.3058   1.0000
   5.250   1.1402   0.00899   0.00357  -0.1112   0.2941   1.0000
   5.500   1.1672   0.00923   0.00375  -0.1111   0.2793   1.0000
   5.750   1.1939   0.00951   0.00396  -0.1111   0.2606   1.0000
   6.000   1.2198   0.00990   0.00422  -0.1109   0.2341   1.0000
   6.250   1.2384   0.01153   0.00518  -0.1100   0.1168   1.0000
   6.500   1.2578   0.01299   0.00618  -0.1091   0.0357   1.0000
   6.750   1.2817   0.01365   0.00675  -0.1086   0.0200   1.0000
   7.000   1.3066   0.01409   0.00721  -0.1082   0.0172   1.0000
   7.250   1.3311   0.01457   0.00772  -0.1077   0.0153   1.0000
   7.500   1.3538   0.01531   0.00854  -0.1070   0.0134   1.0000
   7.750   1.3781   0.01574   0.00901  -0.1065   0.0128   1.0000
   8.000   1.4017   0.01623   0.00953  -0.1060   0.0119   1.0000
   8.250   1.4246   0.01678   0.01013  -0.1053   0.0111   1.0000
   8.500   1.4454   0.01755   0.01096  -0.1044   0.0103   1.0000
   8.750   1.4603   0.01894   0.01250  -0.1025   0.0096   1.0000
   9.000   1.4814   0.01953   0.01315  -0.1016   0.0093   1.0000
   9.250   1.5008   0.02026   0.01394  -0.1004   0.0090   1.0000
   9.500   1.5184   0.02109   0.01484  -0.0990   0.0087   1.0000
   9.750   1.5347   0.02197   0.01580  -0.0974   0.0083   1.0000
  10.000   1.5509   0.02278   0.01668  -0.0959   0.0079   1.0000
  10.250   1.5663   0.02358   0.01751  -0.0942   0.0076   1.0000
  10.500   1.5773   0.02458   0.01856  -0.0919   0.0073   1.0000
  10.750   1.5756   0.02616   0.02024  -0.0876   0.0070   1.0000
  11.000   1.5625   0.02864   0.02287  -0.0823   0.0068   1.0000
  11.250   1.5620   0.03055   0.02490  -0.0792   0.0067   1.0000
  11.500   1.5689   0.03197   0.02641  -0.0773   0.0066   1.0000
  11.750   1.5734   0.03372   0.02826  -0.0754   0.0064   1.0000
  12.000   1.5769   0.03567   0.03033  -0.0736   0.0063   1.0000
  12.250   1.5787   0.03792   0.03268  -0.0721   0.0062   1.0000
  12.500   1.5799   0.04033   0.03521  -0.0707   0.0061   1.0000
  12.750   1.5800   0.04299   0.03798  -0.0696   0.0060   1.0000
  13.000   1.5797   0.04580   0.04090  -0.0687   0.0059   1.0000
  13.250   1.5785   0.04879   0.04402  -0.0679   0.0058   1.0000
  13.500   1.5769   0.05196   0.04730  -0.0675   0.0057   1.0000
  13.750   1.5746   0.05530   0.05076  -0.0672   0.0056   1.0000
  14.000   1.5712   0.05885   0.05443  -0.0671   0.0055   1.0000
  14.250   1.5680   0.06250   0.05820  -0.0673   0.0054   1.0000
  14.500   1.5627   0.06647   0.06230  -0.0675   0.0054   1.0000
  14.750   1.5578   0.07049   0.06643  -0.0681   0.0053   1.0000
  15.000   1.5513   0.07485   0.07092  -0.0688   0.0052   1.0000
  15.250   1.5454   0.07928   0.07546  -0.0699   0.0051   1.0000
  15.500   1.5374   0.08404   0.08035  -0.0710   0.0051   1.0000
  15.750   1.5301   0.08887   0.08529  -0.0724   0.0050   1.0000
  16.000   1.5204   0.09413   0.09068  -0.0739   0.0050   1.0000
  16.250   1.5118   0.09940   0.09607  -0.0757   0.0050   1.0000
  16.500   1.5011   0.10504   0.10184  -0.0777   0.0049   1.0000
  16.750   1.4909   0.11077   0.10768  -0.0799   0.0049   1.0000
  17.000   1.4792   0.11690   0.11394  -0.0824   0.0048   1.0000
  17.250   1.4670   0.12330   0.12047  -0.0853   0.0048   1.0000
  17.500   1.4542   0.12992   0.12722  -0.0884   0.0048   1.0000
  17.750   1.4401   0.13702   0.13446  -0.0920   0.0048   1.0000
  18.000   1.4259   0.14440   0.14198  -0.0959   0.0047   1.0000
  18.250   1.4115   0.15216   0.14988  -0.1004   0.0047   1.0000
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