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GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 693 AIRFOIL (goe693-il)
Reynolds number: 200,000
Max Cl/Cd: 72.51 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe693-il-200000-n5.txt
Download as CSV file: xf-goe693-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 693 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6725   0.05235   0.04856  -0.0727   1.0000   0.0332
 -10.500  -0.7258   0.04566   0.04158  -0.0708   1.0000   0.0331
 -10.250  -0.7421   0.03851   0.03369  -0.0729   0.9953   0.0337
 -10.000  -0.7238   0.03528   0.03013  -0.0750   0.9905   0.0345
  -9.750  -0.6957   0.03413   0.02894  -0.0766   0.9867   0.0354
  -9.500  -0.6669   0.03271   0.02736  -0.0786   0.9836   0.0365
  -9.250  -0.6431   0.03079   0.02516  -0.0797   0.9781   0.0376
  -9.000  -0.6159   0.02866   0.02265  -0.0814   0.9742   0.0388
  -8.750  -0.5883   0.02689   0.02051  -0.0827   0.9701   0.0401
  -8.500  -0.5613   0.02542   0.01869  -0.0835   0.9646   0.0410
  -8.250  -0.5316   0.02395   0.01711  -0.0848   0.9608   0.0421
  -8.000  -0.5038   0.02299   0.01605  -0.0854   0.9550   0.0430
  -7.750  -0.4750   0.02211   0.01505  -0.0861   0.9492   0.0441
  -7.500  -0.4435   0.02127   0.01405  -0.0872   0.9452   0.0456
  -7.250  -0.4181   0.02047   0.01310  -0.0870   0.9369   0.0470
  -7.000  -0.3883   0.01961   0.01206  -0.0876   0.9312   0.0483
  -6.750  -0.3615   0.01888   0.01116  -0.0875   0.9231   0.0493
  -6.500  -0.3338   0.01805   0.01030  -0.0877   0.9161   0.0508
  -6.250  -0.3068   0.01748   0.00968  -0.0876   0.9079   0.0524
  -6.000  -0.2785   0.01697   0.00909  -0.0878   0.9002   0.0546
  -5.750  -0.2514   0.01649   0.00851  -0.0876   0.8911   0.0572
  -5.500  -0.2232   0.01594   0.00789  -0.0876   0.8836   0.0598
  -5.250  -0.1965   0.01552   0.00745  -0.0874   0.8741   0.0628
  -5.000  -0.1684   0.01513   0.00698  -0.0874   0.8662   0.0668
  -4.750  -0.1412   0.01476   0.00658  -0.0872   0.8568   0.0712
  -4.500  -0.1135   0.01449   0.00628  -0.0871   0.8482   0.0771
  -4.250  -0.0858   0.01423   0.00598  -0.0870   0.8397   0.0841
  -4.000  -0.0580   0.01406   0.00573  -0.0869   0.8314   0.0920
  -3.750  -0.0303   0.01383   0.00547  -0.0868   0.8234   0.0991
  -3.500  -0.0027   0.01367   0.00524  -0.0867   0.8150   0.1065
  -3.250   0.0250   0.01347   0.00500  -0.0866   0.8076   0.1137
  -3.000   0.0526   0.01333   0.00482  -0.0865   0.8001   0.1217
  -2.750   0.0802   0.01316   0.00462  -0.0865   0.7930   0.1294
  -2.500   0.1079   0.01302   0.00446  -0.0864   0.7860   0.1378
  -2.250   0.1354   0.01286   0.00430  -0.0863   0.7787   0.1458
  -2.000   0.1631   0.01274   0.00414  -0.0862   0.7716   0.1552
  -1.750   0.1903   0.01259   0.00401  -0.0861   0.7631   0.1661
  -1.500   0.2177   0.01246   0.00388  -0.0859   0.7552   0.1789
  -1.250   0.2450   0.01231   0.00378  -0.0858   0.7469   0.1972
  -1.000   0.2723   0.01216   0.00368  -0.0857   0.7395   0.2243
  -0.750   0.2993   0.01198   0.00362  -0.0855   0.7314   0.2635
  -0.500   0.3260   0.01177   0.00356  -0.0854   0.7237   0.3204
  -0.250   0.3515   0.01141   0.00353  -0.0850   0.7144   0.4191
   0.000   0.3746   0.01088   0.00354  -0.0841   0.7058   0.5838
   0.250   0.3953   0.01035   0.00362  -0.0820   0.6978   0.7688
   0.500   0.4380   0.01018   0.00370  -0.0843   0.6892   0.9294
   0.750   0.4800   0.01023   0.00367  -0.0872   0.6799   0.9794
   1.000   0.5211   0.01029   0.00367  -0.0901   0.6709   1.0000
   1.250   0.5465   0.01037   0.00367  -0.0895   0.6635   1.0000
   1.500   0.5719   0.01045   0.00370  -0.0890   0.6555   1.0000
   1.750   0.5974   0.01055   0.00373  -0.0885   0.6480   1.0000
   2.000   0.6229   0.01064   0.00379  -0.0880   0.6400   1.0000
   2.250   0.6485   0.01074   0.00383  -0.0875   0.6316   1.0000
   2.500   0.6740   0.01084   0.00391  -0.0870   0.6221   1.0000
   2.750   0.6994   0.01095   0.00397  -0.0864   0.6114   1.0000
   3.000   0.7246   0.01106   0.00403  -0.0858   0.5987   1.0000
   3.250   0.7497   0.01118   0.00412  -0.0853   0.5851   1.0000
   3.500   0.7750   0.01132   0.00423  -0.0847   0.5719   1.0000
   3.750   0.8002   0.01146   0.00434  -0.0842   0.5582   1.0000
   4.000   0.8251   0.01162   0.00447  -0.0836   0.5429   1.0000
   4.250   0.8496   0.01181   0.00460  -0.0829   0.5250   1.0000
   4.500   0.8730   0.01204   0.00474  -0.0820   0.5010   1.0000
   4.750   0.8949   0.01236   0.00491  -0.0809   0.4700   1.0000
   5.000   0.9163   0.01273   0.00514  -0.0797   0.4411   1.0000
   5.250   0.9380   0.01311   0.00540  -0.0787   0.4175   1.0000
   5.500   0.9595   0.01352   0.00570  -0.0776   0.3969   1.0000
   5.750   0.9812   0.01391   0.00602  -0.0766   0.3787   1.0000
   6.000   1.0033   0.01429   0.00636  -0.0756   0.3647   1.0000
   6.250   1.0253   0.01468   0.00671  -0.0747   0.3510   1.0000
   6.500   1.0473   0.01506   0.00708  -0.0737   0.3378   1.0000
   6.750   1.0692   0.01544   0.00747  -0.0728   0.3257   1.0000
   7.000   1.0905   0.01584   0.00787  -0.0717   0.3139   1.0000
   7.250   1.1111   0.01628   0.00829  -0.0706   0.3001   1.0000
   7.500   1.1314   0.01671   0.00872  -0.0694   0.2853   1.0000
   7.750   1.1516   0.01714   0.00917  -0.0682   0.2697   1.0000
   8.000   1.1706   0.01761   0.00964  -0.0669   0.2503   1.0000
   8.250   1.1869   0.01821   0.01017  -0.0651   0.2271   1.0000
   8.500   1.2009   0.01891   0.01076  -0.0631   0.2048   1.0000
   8.750   1.2114   0.01971   0.01146  -0.0605   0.1882   1.0000
   9.000   1.2218   0.02053   0.01222  -0.0579   0.1751   1.0000
   9.250   1.2337   0.02133   0.01300  -0.0557   0.1642   1.0000
   9.500   1.2442   0.02224   0.01388  -0.0534   0.1552   1.0000
   9.750   1.2603   0.02287   0.01460  -0.0519   0.1462   1.0000
  10.000   1.2739   0.02366   0.01542  -0.0502   0.1366   1.0000
  10.250   1.2882   0.02442   0.01623  -0.0486   0.1230   1.0000
  10.500   1.3004   0.02534   0.01712  -0.0469   0.1047   1.0000
  10.750   1.3081   0.02660   0.01825  -0.0449   0.0901   1.0000
  11.000   1.3152   0.02796   0.01957  -0.0429   0.0802   1.0000
  11.250   1.3242   0.02923   0.02089  -0.0412   0.0704   1.0000
  11.500   1.3316   0.03068   0.02236  -0.0394   0.0567   1.0000
  11.750   1.3342   0.03257   0.02414  -0.0375   0.0412   1.0000
  12.000   1.3367   0.03454   0.02608  -0.0357   0.0342   1.0000
  12.250   1.3403   0.03648   0.02808  -0.0342   0.0303   1.0000
  12.500   1.3431   0.03856   0.03023  -0.0328   0.0278   1.0000
  12.750   1.3453   0.04075   0.03251  -0.0315   0.0261   1.0000
  13.000   1.3487   0.04290   0.03478  -0.0305   0.0246   1.0000
  13.250   1.3504   0.04526   0.03726  -0.0295   0.0234   1.0000
  13.500   1.3497   0.04793   0.04004  -0.0287   0.0224   1.0000
  13.750   1.3464   0.05095   0.04316  -0.0280   0.0215   1.0000
  14.000   1.3470   0.05365   0.04600  -0.0275   0.0207   1.0000
  14.250   1.3460   0.05661   0.04910  -0.0272   0.0200   1.0000
  14.500   1.3438   0.05981   0.05243  -0.0270   0.0194   1.0000
  14.750   1.3406   0.06324   0.05598  -0.0270   0.0189   1.0000
  15.000   1.3364   0.06690   0.05976  -0.0272   0.0185   1.0000
  15.250   1.3309   0.07082   0.06380  -0.0276   0.0181   1.0000
  15.500   1.3242   0.07503   0.06813  -0.0283   0.0177   1.0000
  15.750   1.3163   0.07953   0.07273  -0.0291   0.0174   1.0000
  16.000   1.3079   0.08418   0.07748  -0.0301   0.0171   1.0000
  16.250   1.3034   0.08838   0.08183  -0.0311   0.0169   1.0000
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