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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.73 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe596-il-1000000.txt
Download as CSV file: xf-goe596-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2822   0.09731   0.09570  -0.0359   1.0000   0.0201
 -10.250  -0.2832   0.09323   0.09162  -0.0369   1.0000   0.0201
 -10.000  -0.2842   0.08920   0.08761  -0.0377   1.0000   0.0201
  -9.750  -0.2888   0.08445   0.08287  -0.0380   1.0000   0.0204
  -9.500  -0.2848   0.08196   0.08040  -0.0375   1.0000   0.0205
  -9.250  -0.2814   0.07957   0.07803  -0.0370   1.0000   0.0207
  -9.000  -0.2805   0.07708   0.07556  -0.0365   1.0000   0.0209
  -8.750  -0.2701   0.07363   0.07211  -0.0387   0.9986   0.0213
  -8.500  -0.2603   0.06969   0.06817  -0.0417   0.9936   0.0218
  -8.250  -0.2532   0.06535   0.06383  -0.0450   0.9874   0.0229
  -7.250  -0.2806   0.04445   0.04248  -0.0849   0.9608   0.0247
  -7.000  -0.2537   0.04244   0.04040  -0.0879   0.9518   0.0251
  -6.750  -0.2282   0.04025   0.03811  -0.0903   0.9396   0.0254
  -6.500  -0.2068   0.03825   0.03599  -0.0914   0.9248   0.0261
  -6.250  -0.1884   0.03313   0.03042  -0.0918   0.9076   0.0291
  -6.000  -0.1752   0.02959   0.02650  -0.0909   0.8927   0.0292
  -5.750  -0.1708   0.02347   0.01992  -0.0897   0.8786   0.0301
  -5.500  -0.1484   0.02258   0.01897  -0.0892   0.8671   0.0305
  -5.250  -0.1255   0.02183   0.01814  -0.0888   0.8564   0.0310
  -5.000  -0.1025   0.02100   0.01718  -0.0882   0.8458   0.0318
  -4.750  -0.0871   0.01565   0.01099  -0.0856   0.8349   0.0286
  -4.500  -0.0633   0.01443   0.00953  -0.0848   0.8239   0.0288
  -4.250  -0.0379   0.01406   0.00894  -0.0842   0.8120   0.0294
  -4.000  -0.0143   0.01251   0.00716  -0.0834   0.7997   0.0297
  -3.750   0.0106   0.01162   0.00613  -0.0827   0.7849   0.0299
  -3.500   0.0356   0.01093   0.00532  -0.0821   0.7669   0.0301
  -3.250   0.0605   0.01043   0.00470  -0.0813   0.7419   0.0304
  -3.000   0.0850   0.01008   0.00421  -0.0805   0.7111   0.0307
  -2.750   0.1094   0.00982   0.00381  -0.0797   0.6794   0.0311
  -2.500   0.1345   0.00961   0.00348  -0.0791   0.6559   0.0315
  -2.250   0.1602   0.00946   0.00325  -0.0785   0.6382   0.0323
  -2.000   0.1861   0.00928   0.00300  -0.0780   0.6240   0.0330
  -1.750   0.2121   0.00909   0.00274  -0.0775   0.6118   0.0336
  -1.500   0.2385   0.00892   0.00251  -0.0771   0.6016   0.0342
  -1.250   0.2650   0.00877   0.00232  -0.0767   0.5931   0.0346
  -1.000   0.2916   0.00866   0.00217  -0.0764   0.5846   0.0351
  -0.750   0.3180   0.00848   0.00195  -0.0760   0.5773   0.0356
  -0.500   0.3443   0.00826   0.00169  -0.0756   0.5697   0.0372
  -0.250   0.3711   0.00818   0.00159  -0.0752   0.5631   0.0387
   0.000   0.3983   0.00812   0.00153  -0.0750   0.5569   0.0406
   0.250   0.4252   0.00809   0.00147  -0.0747   0.5507   0.0422
   0.500   0.4524   0.00800   0.00137  -0.0745   0.5450   0.0456
   0.750   0.4794   0.00795   0.00133  -0.0742   0.5387   0.0511
   1.000   0.5043   0.00759   0.00132  -0.0737   0.5324   0.1984
   1.250   0.5258   0.00680   0.00139  -0.0728   0.5262   0.5209
   1.500   0.5854   0.00581   0.00156  -0.0797   0.5179   0.9901
   1.750   0.6349   0.00587   0.00158  -0.0845   0.5096   1.0000
   2.000   0.6591   0.00597   0.00161  -0.0836   0.5023   1.0000
   2.250   0.6843   0.00602   0.00165  -0.0830   0.4959   1.0000
   2.500   0.7089   0.00611   0.00169  -0.0822   0.4886   1.0000
   2.750   0.7340   0.00618   0.00174  -0.0816   0.4806   1.0000
   3.000   0.7584   0.00629   0.00179  -0.0808   0.4696   1.0000
   3.250   0.7831   0.00639   0.00185  -0.0801   0.4576   1.0000
   3.500   0.8073   0.00653   0.00192  -0.0793   0.4410   1.0000
   3.750   0.8321   0.00665   0.00200  -0.0786   0.4278   1.0000
   4.000   0.8562   0.00682   0.00210  -0.0778   0.4113   1.0000
   4.250   0.8801   0.00700   0.00221  -0.0770   0.3938   1.0000
   4.500   0.9041   0.00720   0.00234  -0.0762   0.3769   1.0000
   4.750   0.9274   0.00743   0.00249  -0.0753   0.3570   1.0000
   5.000   0.9506   0.00769   0.00266  -0.0744   0.3383   1.0000
   5.250   0.9742   0.00792   0.00283  -0.0736   0.3228   1.0000
   5.500   0.9976   0.00817   0.00301  -0.0728   0.3069   1.0000
   5.750   1.0208   0.00845   0.00321  -0.0719   0.2890   1.0000
   6.000   1.0431   0.00879   0.00344  -0.0710   0.2623   1.0000
   6.250   1.0633   0.00930   0.00375  -0.0697   0.2213   1.0000
   6.500   1.0798   0.01010   0.00424  -0.0678   0.1671   1.0000
   6.750   1.0956   0.01095   0.00479  -0.0659   0.1157   1.0000
   7.000   1.1062   0.01220   0.00564  -0.0631   0.0491   1.0000
   7.250   1.1276   0.01259   0.00602  -0.0620   0.0441   1.0000
   7.500   1.1485   0.01302   0.00644  -0.0608   0.0399   1.0000
   7.750   1.1707   0.01333   0.00677  -0.0599   0.0383   1.0000
   8.000   1.1919   0.01369   0.00716  -0.0588   0.0364   1.0000
   8.250   1.2117   0.01415   0.00762  -0.0575   0.0343   1.0000
   8.500   1.2307   0.01464   0.00815  -0.0561   0.0325   1.0000
   8.750   1.2516   0.01497   0.00851  -0.0550   0.0316   1.0000
   9.000   1.2716   0.01535   0.00892  -0.0537   0.0304   1.0000
   9.250   1.2905   0.01576   0.00935  -0.0524   0.0291   1.0000
   9.500   1.3067   0.01631   0.00992  -0.0506   0.0277   1.0000
   9.750   1.3183   0.01699   0.01065  -0.0479   0.0264   1.0000
  10.000   1.3344   0.01735   0.01106  -0.0460   0.0258   1.0000
  10.250   1.3499   0.01775   0.01149  -0.0441   0.0249   1.0000
  10.500   1.3650   0.01818   0.01194  -0.0422   0.0239   1.0000
  10.750   1.3779   0.01874   0.01252  -0.0400   0.0230   1.0000
  11.000   1.3855   0.01960   0.01343  -0.0372   0.0219   1.0000
  11.250   1.3954   0.02037   0.01426  -0.0349   0.0212   1.0000
  11.500   1.4093   0.02097   0.01491  -0.0333   0.0207   1.0000
  11.750   1.4220   0.02166   0.01564  -0.0315   0.0199   1.0000
  12.000   1.4342   0.02240   0.01643  -0.0299   0.0193   1.0000
  12.250   1.4458   0.02322   0.01728  -0.0283   0.0185   1.0000
  12.500   1.4504   0.02455   0.01865  -0.0262   0.0177   1.0000
  12.750   1.4555   0.02594   0.02011  -0.0243   0.0172   1.0000
  13.000   1.4659   0.02700   0.02125  -0.0231   0.0167   1.0000
  13.250   1.4758   0.02816   0.02246  -0.0220   0.0162   1.0000
  13.500   1.4844   0.02947   0.02383  -0.0209   0.0157   1.0000
  13.750   1.4912   0.03100   0.02543  -0.0198   0.0153   1.0000
  14.000   1.4964   0.03274   0.02722  -0.0189   0.0149   1.0000
  14.250   1.4978   0.03493   0.02947  -0.0181   0.0144   1.0000
  14.500   1.4893   0.03825   0.03289  -0.0173   0.0139   1.0000
  14.750   1.4933   0.04044   0.03517  -0.0170   0.0137   1.0000
  15.000   1.4966   0.04278   0.03760  -0.0168   0.0135   1.0000
  15.250   1.4993   0.04523   0.04014  -0.0167   0.0132   1.0000
  15.500   1.4996   0.04803   0.04302  -0.0168   0.0129   1.0000
  15.750   1.5010   0.05076   0.04584  -0.0170   0.0126   1.0000
  16.000   1.5009   0.05373   0.04888  -0.0173   0.0123   1.0000
  16.250   1.5016   0.05663   0.05185  -0.0177   0.0120   1.0000
  16.500   1.4972   0.06026   0.05555  -0.0183   0.0118   1.0000
  16.750   1.4911   0.06416   0.05955  -0.0191   0.0116   1.0000
  17.000   1.4833   0.06837   0.06384  -0.0200   0.0114   1.0000
  17.250   1.4712   0.07326   0.06883  -0.0212   0.0112   1.0000
  17.500   1.4562   0.07870   0.07437  -0.0226   0.0110   1.0000
  17.750   1.4497   0.08306   0.07883  -0.0239   0.0109   1.0000
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