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RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG-15 8.9% (rg15-il)
Reynolds number: 100,000
Max Cl/Cd: 50.54 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg15-il-100000-n5.txt
Download as CSV file: xf-rg15-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4836   0.09107   0.08599  -0.0275   1.0000   0.0221
  -9.000  -0.4865   0.08666   0.08164  -0.0294   1.0000   0.0219
  -8.750  -0.4913   0.08202   0.07707  -0.0316   1.0000   0.0216
  -8.500  -0.4982   0.07721   0.07235  -0.0340   1.0000   0.0213
  -8.250  -0.5101   0.07189   0.06712  -0.0373   1.0000   0.0208
  -8.000  -0.5230   0.06614   0.06138  -0.0409   1.0000   0.0206
  -7.750  -0.5326   0.06065   0.05581  -0.0428   1.0000   0.0202
  -7.500  -0.5389   0.05561   0.05063  -0.0437   1.0000   0.0204
  -7.250  -0.5415   0.05082   0.04562  -0.0438   1.0000   0.0203
  -7.000  -0.5396   0.04656   0.04106  -0.0435   1.0000   0.0214
  -6.750  -0.5344   0.04236   0.03648  -0.0428   1.0000   0.0221
  -6.500  -0.5256   0.03832   0.03195  -0.0418   1.0000   0.0230
  -6.250  -0.5132   0.03468   0.02779  -0.0407   1.0000   0.0234
  -6.000  -0.4976   0.03143   0.02400  -0.0395   1.0000   0.0238
  -5.750  -0.4792   0.02874   0.02077  -0.0382   1.0000   0.0245
  -5.500  -0.4600   0.02608   0.01773  -0.0371   1.0000   0.0254
  -5.250  -0.4400   0.02433   0.01584  -0.0362   1.0000   0.0272
  -5.000  -0.4190   0.02331   0.01464  -0.0353   1.0000   0.0310
  -4.750  -0.3969   0.02193   0.01294  -0.0342   1.0000   0.0337
  -4.500  -0.3752   0.02046   0.01133  -0.0331   1.0000   0.0359
  -4.250  -0.3539   0.01959   0.01047  -0.0322   1.0000   0.0410
  -4.000  -0.3319   0.01877   0.00949  -0.0312   1.0000   0.0457
  -3.750  -0.3100   0.01782   0.00852  -0.0304   1.0000   0.0507
  -3.500  -0.2874   0.01718   0.00777  -0.0296   1.0000   0.0593
  -3.250  -0.2595   0.01643   0.00715  -0.0301   0.9979   0.0832
  -3.000  -0.2238   0.01562   0.00658  -0.0322   0.9925   0.1422
  -2.750  -0.1901   0.01461   0.00628  -0.0344   0.9865   0.2852
  -2.250  -0.1287   0.01325   0.00630  -0.0357   0.9728   0.6462
  -2.000  -0.0983   0.01316   0.00631  -0.0356   0.9644   0.7246
  -1.750  -0.0653   0.01312   0.00624  -0.0360   0.9569   0.7773
  -1.500  -0.0367   0.01305   0.00615  -0.0356   0.9471   0.8173
  -1.250  -0.0060   0.01297   0.00604  -0.0355   0.9383   0.8528
  -1.000   0.0286   0.01288   0.00589  -0.0362   0.9306   0.8869
  -0.750   0.0651   0.01278   0.00575  -0.0374   0.9218   0.9182
  -0.500   0.1143   0.01268   0.00557  -0.0413   0.9162   0.9462
  -0.250   0.1627   0.01257   0.00538  -0.0454   0.9072   0.9714
   0.000   0.2142   0.01242   0.00516  -0.0502   0.8989   0.9916
   0.250   0.2550   0.01229   0.00496  -0.0529   0.8875   1.0000
   0.500   0.2858   0.01219   0.00479  -0.0536   0.8723   1.0000
   0.750   0.3162   0.01212   0.00466  -0.0541   0.8559   1.0000
   1.000   0.3469   0.01207   0.00456  -0.0546   0.8389   1.0000
   1.250   0.3780   0.01203   0.00448  -0.0551   0.8212   1.0000
   1.500   0.4085   0.01202   0.00441  -0.0554   0.8025   1.0000
   1.750   0.4367   0.01205   0.00439  -0.0553   0.7814   1.0000
   2.000   0.4656   0.01210   0.00438  -0.0553   0.7602   1.0000
   2.250   0.4929   0.01218   0.00444  -0.0550   0.7370   1.0000
   2.500   0.5198   0.01230   0.00450  -0.0546   0.7130   1.0000
   2.750   0.5463   0.01244   0.00458  -0.0541   0.6879   1.0000
   3.000   0.5723   0.01261   0.00469  -0.0535   0.6618   1.0000
   3.250   0.5977   0.01281   0.00486  -0.0528   0.6344   1.0000
   3.500   0.6226   0.01304   0.00503  -0.0520   0.6055   1.0000
   3.750   0.6472   0.01330   0.00523  -0.0512   0.5755   1.0000
   4.000   0.6713   0.01359   0.00545  -0.0503   0.5443   1.0000
   4.250   0.6951   0.01392   0.00575  -0.0494   0.5121   1.0000
   4.500   0.7185   0.01428   0.00603  -0.0485   0.4788   1.0000
   4.750   0.7416   0.01468   0.00636  -0.0476   0.4439   1.0000
   5.000   0.7642   0.01512   0.00672  -0.0466   0.4081   1.0000
   5.250   0.7864   0.01561   0.00712  -0.0456   0.3711   1.0000
   5.500   0.8084   0.01613   0.00761  -0.0446   0.3332   1.0000
   5.750   0.8299   0.01673   0.00811  -0.0436   0.2951   1.0000
   6.000   0.8509   0.01739   0.00867  -0.0426   0.2556   1.0000
   6.250   0.8714   0.01814   0.00929  -0.0416   0.2165   1.0000
   6.500   0.8919   0.01894   0.00999  -0.0406   0.1796   1.0000
   6.750   0.9117   0.01983   0.01078  -0.0396   0.1476   1.0000
   7.000   0.9312   0.02079   0.01166  -0.0385   0.1213   1.0000
   7.250   0.9505   0.02179   0.01270  -0.0374   0.0986   1.0000
   7.500   0.9685   0.02292   0.01380  -0.0361   0.0814   1.0000
   7.750   0.9865   0.02407   0.01500  -0.0348   0.0659   1.0000
   8.000   1.0039   0.02526   0.01623  -0.0335   0.0518   1.0000
   8.250   1.0203   0.02654   0.01755  -0.0321   0.0404   1.0000
   8.500   1.0341   0.02810   0.01918  -0.0304   0.0333   1.0000
   8.750   1.0491   0.02951   0.02072  -0.0289   0.0271   1.0000
   9.000   1.0602   0.03138   0.02275  -0.0269   0.0237   1.0000
   9.250   1.0730   0.03324   0.02486  -0.0250   0.0215   1.0000
   9.500   1.0850   0.03520   0.02702  -0.0232   0.0200   1.0000
   9.750   1.0957   0.03721   0.02919  -0.0214   0.0188   1.0000
  10.000   1.1040   0.03947   0.03161  -0.0196   0.0179   1.0000
  10.250   1.1088   0.04231   0.03465  -0.0175   0.0173   1.0000
  10.500   1.1120   0.04501   0.03765  -0.0153   0.0167   1.0000
  10.750   1.1119   0.04769   0.04068  -0.0130   0.0162   1.0000
  11.000   1.1079   0.05051   0.04382  -0.0109   0.0155   1.0000
  11.250   1.1009   0.05362   0.04723  -0.0093   0.0150   1.0000
  11.500   1.0914   0.05712   0.05100  -0.0084   0.0147   1.0000
  11.750   1.0794   0.06109   0.05524  -0.0083   0.0145   1.0000
  12.000   1.0658   0.06553   0.05991  -0.0093   0.0142   1.0000
  12.250   1.0483   0.07114   0.06578  -0.0115   0.0143   1.0000
  12.500   1.0287   0.07772   0.07259  -0.0151   0.0144   1.0000
  12.750   1.0074   0.08547   0.08054  -0.0200   0.0146   1.0000
  13.000   0.9829   0.09487   0.09013  -0.0263   0.0152   1.0000
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