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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 500,000
Max Cl/Cd: 89.01 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg15-il-500000.txt
Download as CSV file: xf-rg15-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-15 8.9%                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3834   0.09514   0.09293  -0.0279   1.0000   0.0168
 -10.000  -0.3853   0.09049   0.08830  -0.0291   1.0000   0.0168
  -7.250  -0.5664   0.04339   0.04060  -0.0420   1.0000   0.0175
  -7.000  -0.5660   0.03977   0.03681  -0.0406   1.0000   0.0180
  -6.750  -0.5591   0.03691   0.03377  -0.0391   1.0000   0.0183
  -6.000  -0.5105   0.02131   0.01656  -0.0377   0.9973   0.0131
  -5.750  -0.4787   0.01778   0.01249  -0.0387   0.9954   0.0128
  -5.500  -0.4447   0.01627   0.01076  -0.0402   0.9935   0.0137
  -5.250  -0.4119   0.01504   0.00936  -0.0413   0.9908   0.0148
  -5.000  -0.3775   0.01411   0.00828  -0.0427   0.9880   0.0162
  -4.750  -0.3438   0.01263   0.00664  -0.0442   0.9857   0.0191
  -4.500  -0.3065   0.01215   0.00615  -0.0464   0.9836   0.0228
  -4.250  -0.2729   0.01163   0.00555  -0.0476   0.9800   0.0250
  -4.000  -0.2399   0.01074   0.00461  -0.0489   0.9758   0.0299
  -3.750  -0.2031   0.01035   0.00417  -0.0508   0.9729   0.0340
  -3.500  -0.1652   0.00979   0.00359  -0.0530   0.9707   0.0450
  -3.250  -0.1338   0.00909   0.00315  -0.0539   0.9654   0.1038
  -3.000  -0.0992   0.00855   0.00288  -0.0556   0.9612   0.1733
  -2.750  -0.0621   0.00798   0.00263  -0.0579   0.9584   0.2635
  -2.500  -0.0277   0.00730   0.00239  -0.0597   0.9544   0.3931
  -2.250   0.0018   0.00652   0.00223  -0.0603   0.9477   0.5644
  -2.000   0.0365   0.00617   0.00217  -0.0616   0.9432   0.6666
  -1.750   0.0663   0.00603   0.00207  -0.0617   0.9337   0.6997
  -1.500   0.0987   0.00590   0.00197  -0.0624   0.9251   0.7271
  -1.250   0.1307   0.00580   0.00188  -0.0629   0.9154   0.7526
  -1.000   0.1599   0.00574   0.00182  -0.0629   0.9023   0.7712
  -0.750   0.1887   0.00570   0.00175  -0.0628   0.8881   0.7873
  -0.500   0.2163   0.00569   0.00171  -0.0624   0.8724   0.8027
  -0.250   0.2430   0.00568   0.00168  -0.0619   0.8551   0.8173
   0.000   0.2694   0.00569   0.00166  -0.0613   0.8369   0.8315
   0.250   0.2955   0.00572   0.00164  -0.0606   0.8183   0.8454
   0.500   0.3209   0.00575   0.00164  -0.0598   0.7982   0.8595
   0.750   0.3457   0.00579   0.00164  -0.0589   0.7778   0.8742
   1.000   0.3699   0.00584   0.00166  -0.0578   0.7567   0.8897
   1.250   0.3933   0.00589   0.00168  -0.0565   0.7349   0.9067
   1.500   0.4161   0.00594   0.00169  -0.0552   0.7123   0.9263
   1.750   0.4403   0.00601   0.00171  -0.0541   0.6890   0.9475
   2.250   0.5072   0.00625   0.00177  -0.0564   0.6353   0.9836
   2.500   0.5452   0.00640   0.00182  -0.0587   0.6055   0.9994
   2.750   0.5686   0.00658   0.00188  -0.0580   0.5781   1.0000
   3.000   0.5930   0.00679   0.00199  -0.0574   0.5496   1.0000
   3.250   0.6178   0.00701   0.00210  -0.0568   0.5195   1.0000
   3.500   0.6426   0.00725   0.00223  -0.0563   0.4877   1.0000
   3.750   0.6676   0.00750   0.00237  -0.0558   0.4579   1.0000
   4.000   0.6925   0.00779   0.00253  -0.0553   0.4263   1.0000
   4.250   0.7175   0.00808   0.00273  -0.0549   0.3947   1.0000
   4.500   0.7420   0.00842   0.00294  -0.0543   0.3581   1.0000
   4.750   0.7664   0.00878   0.00316  -0.0538   0.3210   1.0000
   5.000   0.7908   0.00917   0.00342  -0.0533   0.2864   1.0000
   5.250   0.8150   0.00959   0.00369  -0.0528   0.2490   1.0000
   5.500   0.8390   0.01004   0.00402  -0.0522   0.2146   1.0000
   5.750   0.8622   0.01057   0.00438  -0.0516   0.1756   1.0000
   6.000   0.8852   0.01115   0.00476  -0.0510   0.1365   1.0000
   6.250   0.9083   0.01170   0.00518  -0.0504   0.1067   1.0000
   6.500   0.9314   0.01227   0.00562  -0.0497   0.0820   1.0000
   6.750   0.9548   0.01278   0.00609  -0.0491   0.0635   1.0000
   7.000   0.9780   0.01333   0.00659  -0.0484   0.0494   1.0000
   7.250   1.0004   0.01395   0.00714  -0.0477   0.0352   1.0000
   7.500   1.0204   0.01490   0.00799  -0.0465   0.0177   1.0000
   7.750   1.0416   0.01568   0.00882  -0.0454   0.0134   1.0000
   8.000   1.0608   0.01670   0.00995  -0.0440   0.0116   1.0000
   8.250   1.0812   0.01752   0.01087  -0.0428   0.0108   1.0000
   8.500   1.1006   0.01842   0.01190  -0.0415   0.0100   1.0000
   8.750   1.1188   0.01941   0.01299  -0.0401   0.0093   1.0000
   9.000   1.1355   0.02055   0.01422  -0.0385   0.0089   1.0000
   9.250   1.1498   0.02195   0.01574  -0.0365   0.0085   1.0000
   9.500   1.1586   0.02414   0.01811  -0.0340   0.0080   1.0000
   9.750   1.1703   0.02607   0.02023  -0.0319   0.0078   1.0000
  10.000   1.1861   0.02717   0.02148  -0.0303   0.0075   1.0000
  10.250   1.1982   0.02879   0.02329  -0.0284   0.0074   1.0000
  10.500   1.2072   0.03067   0.02537  -0.0261   0.0073   1.0000
  10.750   1.2120   0.03259   0.02751  -0.0232   0.0072   1.0000
  11.000   1.2130   0.03475   0.02991  -0.0201   0.0071   1.0000
  11.250   1.2106   0.03711   0.03251  -0.0170   0.0070   1.0000
  11.500   1.2053   0.03968   0.03532  -0.0142   0.0069   1.0000
  11.750   1.1967   0.04263   0.03851  -0.0118   0.0069   1.0000
  12.000   1.1839   0.04618   0.04230  -0.0100   0.0070   1.0000
  12.250   1.1706   0.04996   0.04631  -0.0092   0.0068   1.0000
  12.500   1.1545   0.05452   0.05110  -0.0095   0.0068   1.0000
  12.750   1.1374   0.05974   0.05652  -0.0110   0.0069   1.0000
  13.000   1.1195   0.06570   0.06267  -0.0138   0.0069   1.0000
  13.250   1.1001   0.07263   0.06980  -0.0177   0.0069   1.0000
  13.500   1.0819   0.08006   0.07738  -0.0224   0.0071   1.0000
  13.750   1.0624   0.08853   0.08601  -0.0281   0.0071   1.0000
  14.000   1.0406   0.09825   0.09588  -0.0345   0.0072   1.0000
  14.250   1.0196   0.10869   0.10642  -0.0414   0.0072   1.0000
  14.500   0.9970   0.11985   0.11767  -0.0482   0.0075   1.0000
  14.750   0.9690   0.13379   0.13171  -0.0564   0.0076   1.0000
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