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RG 15A-1.8/11.0 AIRFOIL (rg15a111-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 15A-1.8/11.0 AIRFOIL (rg15a111-il)
Reynolds number: 100,000
Max Cl/Cd: 50.02 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15a111-il-100000.txt
Download as CSV file: xf-rg15a111-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 15A-1.8/11.0 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3649   0.09118   0.08645  -0.0308   1.0000   0.1421
  -9.250  -0.3644   0.08765   0.08295  -0.0308   1.0000   0.1467
  -9.000  -0.4109   0.08335   0.07884  -0.0362   1.0000   0.1519
  -8.750  -0.3892   0.07891   0.07437  -0.0333   1.0000   0.1546
  -8.500  -0.3830   0.07539   0.07087  -0.0322   1.0000   0.1576
  -8.250  -0.3905   0.07146   0.06701  -0.0324   1.0000   0.1611
  -8.000  -0.6127   0.06044   0.05501  -0.0458   1.0000   0.0816
  -7.750  -0.6162   0.05150   0.04583  -0.0447   1.0000   0.0673
  -7.500  -0.6135   0.04738   0.04157  -0.0430   1.0000   0.0655
  -7.250  -0.6114   0.04337   0.03724  -0.0411   1.0000   0.0644
  -7.000  -0.6060   0.03983   0.03328  -0.0391   1.0000   0.0647
  -6.750  -0.5969   0.03660   0.02959  -0.0372   1.0000   0.0654
  -6.500  -0.5843   0.03350   0.02601  -0.0354   1.0000   0.0656
  -6.250  -0.5686   0.03075   0.02279  -0.0337   1.0000   0.0662
  -6.000  -0.5507   0.02871   0.02024  -0.0320   1.0000   0.0680
  -5.750  -0.5323   0.02653   0.01797  -0.0309   1.0000   0.0721
  -5.500  -0.5122   0.02511   0.01641  -0.0296   1.0000   0.0765
  -5.250  -0.4907   0.02369   0.01468  -0.0282   1.0000   0.0809
  -5.000  -0.4705   0.02226   0.01333  -0.0271   1.0000   0.0890
  -4.750  -0.4496   0.02108   0.01214  -0.0259   1.0000   0.1006
  -4.500  -0.4290   0.01995   0.01107  -0.0247   1.0000   0.1195
  -4.250  -0.4091   0.01898   0.01022  -0.0236   1.0000   0.1511
  -4.000  -0.3896   0.01813   0.00964  -0.0227   1.0000   0.1889
  -3.750  -0.3701   0.01742   0.00919  -0.0219   1.0000   0.2420
  -3.500  -0.3510   0.01656   0.00879  -0.0209   1.0000   0.3152
  -3.250  -0.3333   0.01564   0.00858  -0.0196   1.0000   0.4290
  -3.000  -0.3192   0.01515   0.00885  -0.0169   1.0000   0.5741
  -2.750  -0.3054   0.01527   0.00919  -0.0139   1.0000   0.6718
  -2.500  -0.2927   0.01550   0.00949  -0.0107   1.0000   0.7321
  -2.250  -0.2758   0.01581   0.00984  -0.0081   0.9976   0.7811
  -2.000  -0.2436   0.01631   0.01034  -0.0080   0.9874   0.8293
  -1.750  -0.2123   0.01669   0.01065  -0.0078   0.9769   0.8714
  -1.500  -0.1754   0.01702   0.01091  -0.0086   0.9676   0.9114
  -1.250  -0.1185   0.01738   0.01114  -0.0134   0.9602   0.9459
  -1.000  -0.0379   0.01784   0.01138  -0.0233   0.9571   0.9706
  -0.750   0.0440   0.01799   0.01136  -0.0339   0.9523   0.9866
  -0.500   0.1209   0.01798   0.01121  -0.0439   0.9471   1.0000
  -0.250   0.1637   0.01784   0.01099  -0.0477   0.9348   1.0000
   0.000   0.2094   0.01765   0.01074  -0.0518   0.9236   1.0000
   0.250   0.2632   0.01737   0.01041  -0.0570   0.9147   1.0000
   0.500   0.3066   0.01708   0.01010  -0.0603   0.9022   1.0000
   0.750   0.3502   0.01675   0.00975  -0.0634   0.8899   1.0000
   1.000   0.3921   0.01636   0.00937  -0.0659   0.8771   1.0000
   1.250   0.4304   0.01598   0.00899  -0.0677   0.8633   1.0000
   1.500   0.4637   0.01564   0.00865  -0.0684   0.8479   1.0000
   1.750   0.4927   0.01537   0.00837  -0.0682   0.8313   1.0000
   2.000   0.5196   0.01514   0.00812  -0.0676   0.8142   1.0000
   2.250   0.5454   0.01494   0.00790  -0.0667   0.7967   1.0000
   2.500   0.5659   0.01488   0.00783  -0.0650   0.7774   1.0000
   2.750   0.5861   0.01486   0.00778  -0.0631   0.7570   1.0000
   3.000   0.6099   0.01482   0.00767  -0.0618   0.7375   1.0000
   3.250   0.6311   0.01489   0.00769  -0.0601   0.7158   1.0000
   3.500   0.6545   0.01494   0.00771  -0.0588   0.6940   1.0000
   3.750   0.6773   0.01506   0.00777  -0.0574   0.6711   1.0000
   4.000   0.7015   0.01518   0.00781  -0.0562   0.6480   1.0000
   4.250   0.7237   0.01537   0.00797  -0.0548   0.6229   1.0000
   4.500   0.7471   0.01557   0.00810  -0.0535   0.5980   1.0000
   4.750   0.7706   0.01579   0.00823  -0.0523   0.5726   1.0000
   5.000   0.7924   0.01607   0.00846  -0.0509   0.5450   1.0000
   5.250   0.8142   0.01638   0.00873  -0.0495   0.5170   1.0000
   5.500   0.8357   0.01674   0.00901  -0.0481   0.4885   1.0000
   5.750   0.8568   0.01713   0.00933  -0.0467   0.4596   1.0000
   6.000   0.8774   0.01758   0.00969  -0.0452   0.4301   1.0000
   6.250   0.8977   0.01807   0.01012  -0.0437   0.4007   1.0000
   6.500   0.9173   0.01862   0.01059  -0.0422   0.3709   1.0000
   6.750   0.9364   0.01924   0.01112  -0.0407   0.3410   1.0000
   7.000   0.9548   0.01992   0.01170  -0.0391   0.3112   1.0000
   7.250   0.9726   0.02068   0.01238  -0.0374   0.2819   1.0000
   7.500   0.9896   0.02150   0.01310  -0.0357   0.2533   1.0000
   7.750   1.0062   0.02241   0.01392  -0.0340   0.2264   1.0000
   8.000   1.0225   0.02342   0.01479  -0.0324   0.2022   1.0000
   8.250   1.0387   0.02447   0.01579  -0.0307   0.1797   1.0000
   8.500   1.0554   0.02573   0.01696  -0.0293   0.1606   1.0000
   8.750   1.0715   0.02697   0.01824  -0.0276   0.1427   1.0000
   9.000   1.0886   0.02840   0.01966  -0.0262   0.1278   1.0000
   9.250   1.1061   0.02995   0.02123  -0.0249   0.1151   1.0000
   9.500   1.1247   0.03165   0.02290  -0.0239   0.1045   1.0000
   9.750   1.1440   0.03334   0.02458  -0.0229   0.0955   1.0000
  10.000   1.1594   0.03524   0.02679  -0.0213   0.0879   1.0000
  10.250   1.1818   0.03774   0.02916  -0.0212   0.0809   1.0000
  10.500   1.1905   0.03949   0.03136  -0.0187   0.0757   1.0000
  10.750   1.2064   0.04147   0.03333  -0.0177   0.0702   1.0000
  11.000   1.2119   0.04434   0.03659  -0.0153   0.0664   1.0000
  11.250   1.2146   0.04653   0.03912  -0.0127   0.0627   1.0000
  11.500   1.2216   0.04872   0.04142  -0.0108   0.0594   1.0000
  11.750   1.2239   0.05257   0.04540  -0.0092   0.0566   1.0000
  12.000   1.2076   0.05492   0.04814  -0.0050   0.0555   1.0000
  12.250   1.1908   0.05797   0.05154  -0.0019   0.0547   1.0000
  12.500   1.1721   0.06142   0.05530   0.0003   0.0539   1.0000
  12.750   1.1510   0.06555   0.05972   0.0014   0.0536   1.0000
  13.000   1.1277   0.07031   0.06474   0.0013   0.0534   1.0000
  13.250   1.1022   0.07590   0.07058   0.0000   0.0537   1.0000
  13.500   1.0751   0.08245   0.07735  -0.0027   0.0544   1.0000
  13.750   1.0482   0.08983   0.08489  -0.0066   0.0552   1.0000
  14.000   1.0207   0.09821   0.09341  -0.0114   0.0561   1.0000
  14.250   0.9970   0.10702   0.10228  -0.0164   0.0569   1.0000
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