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GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il)
Reynolds number: 500,000
Max Cl/Cd: 93.32 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe318-il-500000.txt
Download as CSV file: xf-goe318-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4485   0.09606   0.09347   0.0138   0.7676   0.0222
  -7.750  -0.4434   0.09256   0.08991   0.0115   0.7584   0.0229
  -7.500  -0.4395   0.08832   0.08567   0.0060   0.7493   0.0242
  -7.250  -0.4246   0.08191   0.07918  -0.0064   0.7423   0.0246
  -7.000  -0.4077   0.07639   0.07359  -0.0133   0.7348   0.0247
  -6.750  -0.3988   0.07008   0.06719  -0.0172   0.7290   0.0250
  -6.500  -0.3861   0.06730   0.06439  -0.0176   0.7217   0.0253
  -6.250  -0.3702   0.06487   0.06189  -0.0185   0.7153   0.0258
  -6.000  -0.3513   0.06186   0.05882  -0.0208   0.7091   0.0267
  -5.750  -0.3292   0.05804   0.05489  -0.0244   0.7031   0.0280
  -5.500  -0.2879   0.05134   0.04779  -0.0325   0.6986   0.0306
  -5.250  -0.2703   0.04403   0.04027  -0.0357   0.6939   0.0312
  -5.000  -0.2501   0.04216   0.03836  -0.0362   0.6881   0.0318
  -4.750  -0.2276   0.04042   0.03652  -0.0368   0.6830   0.0327
  -4.500  -0.2022   0.03802   0.03399  -0.0378   0.6776   0.0341
  -4.250  -0.1657   0.03540   0.03089  -0.0387   0.6721   0.0382
  -4.000  -0.1437   0.02918   0.02428  -0.0403   0.6675   0.0395
  -3.750  -0.1185   0.02785   0.02294  -0.0407   0.6610   0.0405
  -3.500  -0.0923   0.02657   0.02155  -0.0410   0.6550   0.0420
  -3.250  -0.0644   0.02497   0.01974  -0.0412   0.6496   0.0446
  -3.000  -0.0321   0.02547   0.01986  -0.0406   0.6434   0.0482
  -2.750  -0.0071   0.02084   0.01496  -0.0416   0.6387   0.0509
  -2.500   0.0204   0.01993   0.01399  -0.0419   0.6336   0.0529
  -2.250   0.0493   0.01917   0.01308  -0.0419   0.6275   0.0573
  -2.000   0.0779   0.01773   0.01133  -0.0420   0.6222   0.0633
  -1.750   0.1061   0.01692   0.01050  -0.0422   0.6162   0.0662
  -1.500   0.1386   0.01400   0.00699  -0.0413   0.6103   0.0445
  -1.250   0.1674   0.01323   0.00607  -0.0412   0.6037   0.0444
  -1.000   0.1964   0.01244   0.00518  -0.0411   0.5964   0.0437
  -0.750   0.2251   0.01189   0.00453  -0.0410   0.5905   0.0438
  -0.500   0.2539   0.01142   0.00405  -0.0411   0.5844   0.0442
  -0.250   0.2826   0.01105   0.00364  -0.0410   0.5782   0.0447
   0.000   0.3113   0.01074   0.00330  -0.0411   0.5722   0.0454
   0.250   0.3401   0.01050   0.00305  -0.0411   0.5652   0.0467
   0.500   0.3688   0.01034   0.00284  -0.0412   0.5587   0.0479
   0.750   0.3978   0.01005   0.00256  -0.0413   0.5511   0.0491
   1.000   0.4267   0.00983   0.00229  -0.0414   0.5439   0.0520
   1.250   0.4557   0.00969   0.00217  -0.0415   0.5353   0.0557
   1.500   0.4846   0.00962   0.00206  -0.0416   0.5271   0.0611
   1.750   0.5093   0.00719   0.00209  -0.0414   0.5182   1.0000
   2.000   0.5381   0.00726   0.00206  -0.0414   0.5085   1.0000
   2.250   0.5667   0.00735   0.00206  -0.0415   0.4980   1.0000
   2.500   0.5953   0.00745   0.00207  -0.0416   0.4862   1.0000
   2.750   0.6239   0.00755   0.00211  -0.0417   0.4736   1.0000
   3.000   0.6524   0.00767   0.00216  -0.0419   0.4601   1.0000
   3.250   0.6809   0.00782   0.00223  -0.0420   0.4452   1.0000
   3.500   0.7092   0.00800   0.00232  -0.0421   0.4288   1.0000
   3.750   0.7374   0.00821   0.00244  -0.0423   0.4110   1.0000
   4.000   0.7656   0.00842   0.00257  -0.0424   0.3918   1.0000
   4.250   0.7936   0.00867   0.00273  -0.0426   0.3702   1.0000
   4.500   0.8214   0.00897   0.00293  -0.0428   0.3481   1.0000
   4.750   0.8491   0.00928   0.00314  -0.0429   0.3272   1.0000
   5.000   0.8768   0.00960   0.00337  -0.0431   0.3114   1.0000
   5.250   0.9044   0.00989   0.00362  -0.0433   0.3001   1.0000
   5.500   0.9319   0.01021   0.00388  -0.0434   0.2917   1.0000
   5.750   0.9596   0.01044   0.00412  -0.0435   0.2852   1.0000
   6.000   0.9868   0.01076   0.00441  -0.0436   0.2792   1.0000
   6.250   1.0144   0.01100   0.00467  -0.0437   0.2737   1.0000
   6.500   1.0416   0.01128   0.00494  -0.0438   0.2670   1.0000
   6.750   1.0687   0.01156   0.00522  -0.0439   0.2600   1.0000
   7.000   1.0958   0.01181   0.00550  -0.0440   0.2535   1.0000
   7.250   1.1224   0.01214   0.00582  -0.0441   0.2471   1.0000
   7.500   1.1496   0.01234   0.00607  -0.0441   0.2408   1.0000
   7.750   1.1758   0.01271   0.00643  -0.0442   0.2332   1.0000
   8.000   1.2029   0.01289   0.00669  -0.0443   0.2261   1.0000
   8.250   1.2290   0.01324   0.00704  -0.0443   0.2179   1.0000
   8.500   1.2551   0.01356   0.00736  -0.0443   0.2051   1.0000
   8.750   1.2813   0.01387   0.00767  -0.0444   0.1816   1.0000
   9.000   1.2911   0.01666   0.00960  -0.0436   0.0574   1.0000
   9.250   1.3081   0.01819   0.01097  -0.0429   0.0308   1.0000
   9.500   1.3282   0.01918   0.01199  -0.0424   0.0253   1.0000
   9.750   1.3465   0.02030   0.01314  -0.0418   0.0222   1.0000
  10.000   1.3653   0.02125   0.01419  -0.0411   0.0206   1.0000
  10.250   1.3827   0.02227   0.01529  -0.0405   0.0193   1.0000
  10.500   1.3970   0.02350   0.01661  -0.0396   0.0182   1.0000
  10.750   1.4034   0.02533   0.01854  -0.0382   0.0173   1.0000
  11.000   1.4020   0.02750   0.02085  -0.0367   0.0168   1.0000
  11.250   1.4077   0.02952   0.02299  -0.0365   0.0165   1.0000
  11.500   1.4122   0.03183   0.02542  -0.0365   0.0160   1.0000
  11.750   1.4153   0.03437   0.02806  -0.0366   0.0156   1.0000
  12.000   1.4172   0.03708   0.03087  -0.0368   0.0151   1.0000
  12.250   1.4178   0.03997   0.03385  -0.0370   0.0147   1.0000
  12.500   1.4169   0.04303   0.03699  -0.0372   0.0143   1.0000
  12.750   1.4136   0.04637   0.04041  -0.0374   0.0140   1.0000
  13.000   1.4081   0.04997   0.04410  -0.0377   0.0138   1.0000
  13.250   1.4006   0.05377   0.04798  -0.0378   0.0135   1.0000
  13.500   1.3914   0.05770   0.05199  -0.0378   0.0133   1.0000
  13.750   1.3830   0.06138   0.05576  -0.0373   0.0131   1.0000
  14.000   1.3826   0.06451   0.05900  -0.0377   0.0129   1.0000
  14.250   1.3823   0.06773   0.06232  -0.0380   0.0128   1.0000
  14.500   1.3817   0.07100   0.06570  -0.0384   0.0126   1.0000
  14.750   1.3812   0.07430   0.06910  -0.0388   0.0124   1.0000
  15.000   1.3806   0.07765   0.07254  -0.0391   0.0122   1.0000
  15.250   1.3798   0.08102   0.07602  -0.0395   0.0120   1.0000
  15.500   1.3790   0.08445   0.07955  -0.0400   0.0119   1.0000
  15.750   1.3777   0.08802   0.08322  -0.0406   0.0117   1.0000
  16.000   1.3763   0.09167   0.08697  -0.0414   0.0115   1.0000
  16.250   1.3744   0.09546   0.09086  -0.0424   0.0113   1.0000
  16.500   1.3719   0.09943   0.09493  -0.0435   0.0111   1.0000
  16.750   1.3690   0.10353   0.09912  -0.0448   0.0109   1.0000
  17.000   1.3662   0.10763   0.10331  -0.0462   0.0107   1.0000
  17.250   1.3632   0.11173   0.10748  -0.0476   0.0105   1.0000
  17.500   1.3605   0.11566   0.11148  -0.0488   0.0104   1.0000
  17.750   1.3560   0.11989   0.11581  -0.0500   0.0102   1.0000
  18.000   1.3487   0.12471   0.12077  -0.0514   0.0101   1.0000
  18.250   1.3386   0.13035   0.12656  -0.0538   0.0101   1.0000
  18.500   1.3265   0.13666   0.13304  -0.0568   0.0100   1.0000
  18.750   1.3145   0.14331   0.13986  -0.0605   0.0100   1.0000
  19.000   1.3031   0.15014   0.14684  -0.0646   0.0100   1.0000
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