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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 200,000
Max Cl/Cd: 79.75 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe121-il-200000.txt
Download as CSV file: xf-goe121-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 121 (MVA H.1) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3521   0.09737   0.09380  -0.0228   1.0000   0.0467
  -7.750  -0.3601   0.09655   0.09308  -0.0262   1.0000   0.0473
  -7.500  -0.3559   0.09421   0.09078  -0.0317   1.0000   0.0476
  -7.250  -0.3535   0.08941   0.08603  -0.0320   1.0000   0.0481
  -7.000  -0.3474   0.08572   0.08237  -0.0270   1.0000   0.0490
  -6.750  -0.3415   0.08313   0.07981  -0.0252   1.0000   0.0500
  -6.500  -0.3377   0.08088   0.07761  -0.0246   1.0000   0.0512
  -6.250  -0.3363   0.07885   0.07562  -0.0242   1.0000   0.0529
  -6.000  -0.3363   0.07685   0.07365  -0.0242   1.0000   0.0550
  -5.750  -0.3173   0.07481   0.07153  -0.0374   1.0000   0.0586
  -5.500  -0.3138   0.07055   0.06728  -0.0383   1.0000   0.0592
  -5.250  -0.3043   0.06712   0.06389  -0.0361   0.9982   0.0601
  -5.000  -0.2767   0.06383   0.06058  -0.0385   0.9948   0.0620
  -4.750  -0.2381   0.06004   0.05672  -0.0454   0.9900   0.0662
  -4.500  -0.1797   0.05394   0.05038  -0.0597   0.9854   0.0720
  -4.250  -0.1498   0.05106   0.04748  -0.0623   0.9810   0.0741
  -4.000  -0.0792   0.04623   0.04211  -0.0770   0.9756   0.0831
  -3.750  -0.0487   0.04234   0.03831  -0.0797   0.9722   0.0845
  -3.500  -0.0168   0.04002   0.03598  -0.0819   0.9651   0.0876
  -3.250   0.0456   0.03577   0.03116  -0.0916   0.9608   0.0968
  -3.000   0.0828   0.03264   0.02805  -0.0950   0.9567   0.0983
  -2.750   0.1366   0.02390   0.01832  -0.1015   0.9517   0.0688
  -2.500   0.1811   0.02070   0.01471  -0.1053   0.9477   0.0673
  -2.250   0.2253   0.01788   0.01139  -0.1086   0.9445   0.0661
  -2.000   0.2606   0.01602   0.00915  -0.1098   0.9365   0.0660
  -1.750   0.3002   0.01464   0.00750  -0.1117   0.9312   0.0676
  -1.500   0.3337   0.01376   0.00642  -0.1124   0.9218   0.0699
  -1.250   0.3683   0.01305   0.00572  -0.1134   0.9133   0.0740
  -1.000   0.3998   0.01278   0.00538  -0.1135   0.9021   0.0817
  -0.750   0.4284   0.01240   0.00503  -0.1132   0.8892   0.0915
  -0.500   0.4562   0.01191   0.00458  -0.1127   0.8764   0.1179
  -0.250   0.4833   0.01166   0.00431  -0.1122   0.8635   0.1393
   0.000   0.5100   0.01151   0.00417  -0.1117   0.8506   0.1535
   0.250   0.5364   0.01139   0.00408  -0.1110   0.8363   0.1684
   0.500   0.5624   0.01126   0.00397  -0.1102   0.8194   0.1821
   0.750   0.5884   0.01109   0.00383  -0.1094   0.8006   0.1944
   1.000   0.6146   0.01094   0.00367  -0.1085   0.7807   0.2056
   1.250   0.6406   0.01083   0.00355  -0.1077   0.7579   0.2197
   1.500   0.6668   0.01073   0.00348  -0.1069   0.7354   0.2535
   1.750   0.6869   0.00918   0.00344  -0.1049   0.7136   1.0000
   2.000   0.7131   0.00935   0.00340  -0.1041   0.6902   1.0000
   2.250   0.7390   0.00951   0.00342  -0.1034   0.6624   1.0000
   2.500   0.7645   0.00968   0.00343  -0.1026   0.6289   1.0000
   2.750   0.7895   0.00990   0.00346  -0.1017   0.5909   1.0000
   3.000   0.8139   0.01024   0.00354  -0.1008   0.5572   1.0000
   3.250   0.8385   0.01063   0.00371  -0.1000   0.5287   1.0000
   3.500   0.8635   0.01101   0.00394  -0.0994   0.5044   1.0000
   3.750   0.8888   0.01138   0.00420  -0.0988   0.4836   1.0000
   4.000   0.9143   0.01172   0.00445  -0.0983   0.4660   1.0000
   4.250   0.9400   0.01203   0.00472  -0.0978   0.4496   1.0000
   4.500   0.9658   0.01233   0.00499  -0.0973   0.4342   1.0000
   4.750   0.9913   0.01262   0.00528  -0.0968   0.4178   1.0000
   5.000   1.0162   0.01292   0.00554  -0.0962   0.3970   1.0000
   5.250   1.0404   0.01328   0.00581  -0.0956   0.3754   1.0000
   5.500   1.0649   0.01362   0.00612  -0.0949   0.3531   1.0000
   5.750   1.0885   0.01404   0.00647  -0.0942   0.3304   1.0000
   6.000   1.1127   0.01442   0.00683  -0.0936   0.3063   1.0000
   6.250   1.1366   0.01481   0.00720  -0.0929   0.2803   1.0000
   6.500   1.1594   0.01533   0.00757  -0.0921   0.2345   1.0000
   6.750   1.1769   0.01652   0.00831  -0.0907   0.1681   1.0000
   7.000   1.1901   0.01844   0.00962  -0.0887   0.0731   1.0000
   7.250   1.2089   0.01964   0.01073  -0.0872   0.0489   1.0000
   7.500   1.2286   0.02066   0.01175  -0.0859   0.0417   1.0000
   7.750   1.2453   0.02195   0.01310  -0.0841   0.0376   1.0000
   8.000   1.2620   0.02314   0.01445  -0.0823   0.0359   1.0000
   8.250   1.2773   0.02442   0.01585  -0.0804   0.0345   1.0000
   8.500   1.2913   0.02581   0.01732  -0.0783   0.0332   1.0000
   8.750   1.3046   0.02728   0.01885  -0.0762   0.0316   1.0000
   9.000   1.3157   0.02916   0.02074  -0.0740   0.0300   1.0000
   9.250   1.3289   0.03174   0.02335  -0.0720   0.0291   1.0000
   9.500   1.3476   0.03396   0.02568  -0.0707   0.0286   1.0000
   9.750   1.3667   0.03588   0.02776  -0.0694   0.0283   1.0000
  10.000   1.3857   0.03817   0.03024  -0.0681   0.0281   1.0000
  10.250   1.4028   0.04066   0.03297  -0.0666   0.0279   1.0000
  10.500   1.4155   0.04288   0.03546  -0.0647   0.0274   1.0000
  10.750   1.4250   0.04525   0.03812  -0.0625   0.0269   1.0000
  11.000   1.4316   0.04816   0.04135  -0.0601   0.0268   1.0000
  11.250   1.4341   0.05171   0.04522  -0.0576   0.0272   1.0000
  11.500   1.4309   0.05552   0.04933  -0.0546   0.0276   1.0000
  11.750   1.4458   0.06113   0.05512  -0.0542   0.0292   1.0000
  12.000   1.4231   0.06195   0.05644  -0.0481   0.0310   1.0000
  12.250   1.3838   0.06867   0.06375  -0.0443   0.0344   1.0000
  12.500   1.3657   0.07422   0.06950  -0.0432   0.0358   1.0000
  12.750   1.2692   0.06653   0.06156  -0.0305   0.0297   1.0000
  13.000   1.2383   0.07130   0.06665  -0.0295   0.0305   1.0000
  13.250   1.2013   0.07746   0.07310  -0.0299   0.0309   1.0000
  13.500   1.1645   0.08418   0.08008  -0.0314   0.0312   1.0000
  13.750   1.1300   0.09091   0.08702  -0.0337   0.0315   1.0000
  14.000   1.0950   0.09787   0.09416  -0.0368   0.0317   1.0000
  14.250   1.0581   0.10421   0.10066  -0.0399   0.0317   1.0000
  14.500   1.0196   0.11189   0.10851  -0.0446   0.0319   1.0000
  14.750   0.9633   0.12429   0.12114  -0.0531   0.0333   1.0000
  15.000   0.9187   0.13596   0.13290  -0.0601   0.0357   1.0000
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