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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 100,000
Max Cl/Cd: 46.62 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg149-il-100000-n5.txt
Download as CSV file: xf-rg149-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9% 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5307   0.08951   0.08439  -0.0268   1.0000   0.0284
  -9.500  -0.5362   0.08412   0.07907  -0.0296   1.0000   0.0284
  -9.250  -0.5438   0.07833   0.07333  -0.0331   1.0000   0.0282
  -9.000  -0.5555   0.07171   0.06677  -0.0382   1.0000   0.0280
  -8.750  -0.5708   0.06657   0.06163  -0.0404   1.0000   0.0276
  -8.500  -0.5859   0.06133   0.05630  -0.0414   1.0000   0.0274
  -8.250  -0.5969   0.05650   0.05132  -0.0414   1.0000   0.0272
  -8.000  -0.6058   0.05160   0.04618  -0.0407   1.0000   0.0272
  -7.750  -0.6101   0.04704   0.04129  -0.0394   1.0000   0.0273
  -7.500  -0.6104   0.04261   0.03643  -0.0377   1.0000   0.0275
  -7.250  -0.6061   0.03861   0.03194  -0.0358   1.0000   0.0279
  -7.000  -0.5973   0.03517   0.02793  -0.0338   1.0000   0.0286
  -6.750  -0.5855   0.03247   0.02489  -0.0322   1.0000   0.0302
  -6.500  -0.5695   0.03099   0.02324  -0.0309   1.0000   0.0321
  -6.250  -0.5527   0.02896   0.02089  -0.0294   1.0000   0.0335
  -6.000  -0.5345   0.02696   0.01854  -0.0278   1.0000   0.0347
  -5.750  -0.5150   0.02526   0.01652  -0.0264   1.0000   0.0365
  -5.500  -0.4944   0.02414   0.01504  -0.0250   1.0000   0.0391
  -5.250  -0.4748   0.02252   0.01338  -0.0238   1.0000   0.0413
  -5.000  -0.4544   0.02140   0.01218  -0.0225   1.0000   0.0431
  -4.750  -0.4338   0.02041   0.01106  -0.0212   1.0000   0.0455
  -4.500  -0.4132   0.01953   0.01008  -0.0199   1.0000   0.0485
  -4.250  -0.3930   0.01875   0.00924  -0.0186   1.0000   0.0530
  -4.000  -0.3726   0.01810   0.00858  -0.0175   1.0000   0.0591
  -3.750  -0.3521   0.01740   0.00783  -0.0162   1.0000   0.0658
  -3.500  -0.3313   0.01679   0.00723  -0.0151   1.0000   0.0782
  -3.250  -0.3038   0.01618   0.00672  -0.0155   0.9974   0.1065
  -3.000  -0.2687   0.01550   0.00637  -0.0176   0.9912   0.1686
  -2.750  -0.2348   0.01470   0.00615  -0.0195   0.9849   0.2848
  -2.500  -0.2031   0.01395   0.00596  -0.0208   0.9775   0.4189
  -2.250  -0.1718   0.01320   0.00590  -0.0214   0.9709   0.5913
  -2.000  -0.1463   0.01288   0.00617  -0.0196   0.9624   0.7633
  -1.750  -0.1120   0.01292   0.00625  -0.0198   0.9555   0.8506
  -1.500  -0.0750   0.01296   0.00622  -0.0208   0.9475   0.9014
  -1.250  -0.0233   0.01303   0.00617  -0.0249   0.9437   0.9383
  -1.000   0.0324   0.01305   0.00605  -0.0302   0.9390   0.9646
  -0.750   0.0902   0.01300   0.00588  -0.0362   0.9342   0.9828
  -0.500   0.1513   0.01287   0.00564  -0.0430   0.9298   0.9970
  -0.250   0.1908   0.01274   0.00544  -0.0455   0.9174   1.0000
   0.000   0.2259   0.01261   0.00525  -0.0470   0.9031   1.0000
   0.250   0.2604   0.01248   0.00508  -0.0483   0.8879   1.0000
   0.500   0.2941   0.01236   0.00491  -0.0494   0.8718   1.0000
   0.750   0.3242   0.01228   0.00478  -0.0497   0.8533   1.0000
   1.000   0.3530   0.01222   0.00469  -0.0497   0.8339   1.0000
   1.250   0.3817   0.01218   0.00460  -0.0496   0.8144   1.0000
   1.500   0.4070   0.01218   0.00457  -0.0489   0.7926   1.0000
   1.750   0.4330   0.01220   0.00454  -0.0482   0.7707   1.0000
   2.000   0.4566   0.01225   0.00454  -0.0471   0.7454   1.0000
   2.250   0.4799   0.01233   0.00455  -0.0459   0.7181   1.0000
   2.500   0.5025   0.01244   0.00459  -0.0445   0.6884   1.0000
   2.750   0.5245   0.01259   0.00464  -0.0431   0.6581   1.0000
   3.000   0.5463   0.01277   0.00473  -0.0416   0.6282   1.0000
   3.250   0.5681   0.01298   0.00487  -0.0402   0.6003   1.0000
   3.500   0.5900   0.01321   0.00506  -0.0389   0.5725   1.0000
   3.750   0.6117   0.01347   0.00525  -0.0375   0.5432   1.0000
   4.000   0.6330   0.01377   0.00545  -0.0361   0.5104   1.0000
   4.250   0.6539   0.01410   0.00568  -0.0347   0.4735   1.0000
   4.500   0.6746   0.01448   0.00594  -0.0332   0.4347   1.0000
   4.750   0.6951   0.01491   0.00626  -0.0318   0.3948   1.0000
   5.000   0.7153   0.01540   0.00661  -0.0304   0.3518   1.0000
   5.250   0.7354   0.01595   0.00701  -0.0291   0.3080   1.0000
   5.500   0.7553   0.01657   0.00747  -0.0278   0.2646   1.0000
   5.750   0.7750   0.01726   0.00803  -0.0266   0.2253   1.0000
   6.000   0.7949   0.01799   0.00863  -0.0254   0.1914   1.0000
   6.250   0.8146   0.01876   0.00929  -0.0243   0.1662   1.0000
   6.500   0.8343   0.01955   0.01003  -0.0231   0.1456   1.0000
   6.750   0.8539   0.02037   0.01082  -0.0219   0.1285   1.0000
   7.000   0.8736   0.02117   0.01163  -0.0208   0.1138   1.0000
   7.250   0.8935   0.02197   0.01249  -0.0197   0.1008   1.0000
   7.500   0.9131   0.02281   0.01340  -0.0185   0.0904   1.0000
   7.750   0.9320   0.02374   0.01439  -0.0173   0.0811   1.0000
   8.000   0.9493   0.02481   0.01543  -0.0160   0.0738   1.0000
   8.250   0.9683   0.02587   0.01668  -0.0147   0.0676   1.0000
   8.500   0.9847   0.02712   0.01791  -0.0134   0.0620   1.0000
   8.750   1.0035   0.02822   0.01928  -0.0121   0.0560   1.0000
   9.000   1.0197   0.02948   0.02060  -0.0108   0.0514   1.0000
   9.250   1.0362   0.03084   0.02217  -0.0095   0.0461   1.0000
   9.500   1.0510   0.03199   0.02344  -0.0081   0.0413   1.0000
   9.750   1.0637   0.03355   0.02514  -0.0066   0.0373   1.0000
  10.000   1.0769   0.03528   0.02715  -0.0049   0.0339   1.0000
  10.250   1.0872   0.03687   0.02887  -0.0032   0.0313   1.0000
  10.500   1.0931   0.03884   0.03089  -0.0013   0.0290   1.0000
  10.750   1.0983   0.04088   0.03336   0.0010   0.0269   1.0000
  11.000   1.1005   0.04300   0.03574   0.0033   0.0252   1.0000
  11.250   1.1002   0.04529   0.03825   0.0053   0.0240   1.0000
  11.500   1.0984   0.04769   0.04082   0.0071   0.0232   1.0000
  11.750   1.0945   0.05035   0.04364   0.0084   0.0226   1.0000
  12.000   1.0881   0.05346   0.04690   0.0093   0.0221   1.0000
  12.500   1.0628   0.06186   0.05578   0.0088   0.0215   1.0000
  12.750   1.0471   0.06693   0.06110   0.0070   0.0214   1.0000
  13.000   1.0294   0.07282   0.06722   0.0042   0.0214   1.0000
  13.250   1.0104   0.07949   0.07409   0.0003   0.0215   1.0000
  13.500   0.9886   0.08740   0.08219  -0.0049   0.0216   1.0000
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