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NASA RC(4)-10 AIRFOIL (rc410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA RC(4)-10 AIRFOIL (rc410-il)
Reynolds number: 50,000
Max Cl/Cd: 27.68 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rc410-il-50000-n5.txt
Download as CSV file: xf-rc410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA RC(4)-10 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5361   0.10647   0.09949  -0.0014   1.0000   0.0641
  -9.250  -0.5323   0.10222   0.09529  -0.0033   1.0000   0.0638
  -9.000  -0.5311   0.09765   0.09076  -0.0062   1.0000   0.0637
  -8.750  -0.5315   0.09276   0.08592  -0.0099   1.0000   0.0636
  -8.500  -0.5337   0.08774   0.08094  -0.0139   1.0000   0.0635
  -8.250  -0.5360   0.08293   0.07614  -0.0170   1.0000   0.0634
  -8.000  -0.5364   0.07804   0.07122  -0.0199   1.0000   0.0633
  -7.750  -0.5355   0.07321   0.06631  -0.0223   1.0000   0.0633
  -7.500  -0.5326   0.06848   0.06147  -0.0242   1.0000   0.0632
  -7.250  -0.5278   0.06385   0.05669  -0.0256   1.0000   0.0631
  -7.000  -0.5216   0.05925   0.05188  -0.0266   1.0000   0.0631
  -6.750  -0.5143   0.05469   0.04704  -0.0271   1.0000   0.0634
  -6.500  -0.5070   0.05005   0.04200  -0.0270   1.0000   0.0640
  -6.250  -0.4931   0.04804   0.03996  -0.0263   1.0000   0.0658
  -6.000  -0.4813   0.04632   0.03817  -0.0251   1.0000   0.0680
  -5.750  -0.4756   0.04416   0.03577  -0.0230   1.0000   0.0701
  -5.500  -0.4715   0.04174   0.03302  -0.0203   1.0000   0.0720
  -5.000  -0.4219   0.03651   0.02702  -0.0219   0.9836   0.0789
  -4.750  -0.3901   0.03415   0.02410  -0.0234   0.9740   0.0861
  -4.500  -0.3571   0.03283   0.02264  -0.0251   0.9657   0.0932
  -4.250  -0.3227   0.03111   0.02052  -0.0267   0.9582   0.1031
  -4.000  -0.2899   0.02994   0.01898  -0.0279   0.9503   0.1144
  -3.750  -0.2563   0.02891   0.01789  -0.0294   0.9432   0.1255
  -3.500  -0.2242   0.02791   0.01671  -0.0304   0.9360   0.1371
  -3.250  -0.1905   0.02699   0.01557  -0.0316   0.9291   0.1489
  -3.000  -0.1563   0.02622   0.01462  -0.0327   0.9229   0.1604
  -2.750  -0.1242   0.02547   0.01389  -0.0336   0.9160   0.1712
  -2.500  -0.0877   0.02480   0.01312  -0.0351   0.9108   0.1816
  -2.250  -0.0567   0.02437   0.01258  -0.0357   0.9040   0.1934
  -2.000  -0.0260   0.02384   0.01209  -0.0363   0.8977   0.2039
  -1.750   0.0031   0.02344   0.01170  -0.0366   0.8919   0.2164
  -1.500   0.0280   0.02315   0.01143  -0.0363   0.8847   0.2303
  -1.250   0.0562   0.02280   0.01115  -0.0364   0.8791   0.2476
  -1.000   0.0794   0.02245   0.01100  -0.0359   0.8721   0.2766
  -0.750   0.1390   0.02017   0.01124  -0.0400   0.8711   0.8889
  -0.500   0.2228   0.02018   0.01097  -0.0501   0.8684   1.0000
  -0.250   0.2464   0.02036   0.01096  -0.0491   0.8568   1.0000
   0.000   0.2691   0.02050   0.01093  -0.0476   0.8426   1.0000
   0.250   0.2901   0.02059   0.01087  -0.0455   0.8262   1.0000
   0.500   0.3102   0.02067   0.01081  -0.0433   0.8091   1.0000
   0.750   0.3304   0.02074   0.01075  -0.0410   0.7928   1.0000
   1.000   0.3508   0.02079   0.01071  -0.0388   0.7769   1.0000
   1.250   0.3710   0.02082   0.01064  -0.0366   0.7601   1.0000
   1.500   0.3911   0.02079   0.01054  -0.0343   0.7419   1.0000
   1.750   0.4115   0.02073   0.01042  -0.0320   0.7234   1.0000
   2.000   0.4324   0.02068   0.01032  -0.0299   0.7055   1.0000
   2.250   0.4536   0.02060   0.01019  -0.0278   0.6868   1.0000
   2.500   0.4743   0.02054   0.01013  -0.0258   0.6634   1.0000
   2.750   0.4953   0.02037   0.00993  -0.0236   0.6374   1.0000
   3.000   0.5158   0.02029   0.00984  -0.0216   0.6012   1.0000
   3.250   0.5361   0.02019   0.00967  -0.0193   0.5498   1.0000
   3.500   0.5556   0.02015   0.00928  -0.0166   0.4631   1.0000
   3.750   0.5727   0.02069   0.00901  -0.0139   0.3834   1.0000
   4.000   0.5906   0.02163   0.00945  -0.0124   0.3428   1.0000
   4.250   0.6100   0.02252   0.01005  -0.0112   0.3185   1.0000
   4.500   0.6304   0.02333   0.01069  -0.0101   0.3014   1.0000
   4.750   0.6514   0.02412   0.01132  -0.0090   0.2876   1.0000
   5.000   0.6732   0.02489   0.01197  -0.0080   0.2754   1.0000
   5.250   0.6959   0.02561   0.01268  -0.0072   0.2646   1.0000
   5.500   0.7192   0.02638   0.01335  -0.0064   0.2562   1.0000
   5.750   0.7430   0.02712   0.01412  -0.0057   0.2474   1.0000
   6.000   0.7671   0.02792   0.01487  -0.0050   0.2398   1.0000
   6.250   0.7911   0.02870   0.01574  -0.0044   0.2318   1.0000
   6.500   0.8162   0.02958   0.01650  -0.0038   0.2260   1.0000
   6.750   0.8400   0.03050   0.01760  -0.0032   0.2194   1.0000
   7.000   0.8638   0.03142   0.01857  -0.0027   0.2131   1.0000
   7.250   0.8876   0.03244   0.01961  -0.0022   0.2075   1.0000
   7.500   0.9103   0.03357   0.02095  -0.0016   0.2018   1.0000
   7.750   0.9336   0.03467   0.02210  -0.0011   0.1970   1.0000
   8.000   0.9563   0.03588   0.02338  -0.0006   0.1923   1.0000
   8.250   0.9757   0.03726   0.02508   0.0002   0.1867   1.0000
   8.500   0.9968   0.03854   0.02647   0.0008   0.1821   1.0000
   8.750   1.0198   0.03984   0.02777   0.0012   0.1785   1.0000
   9.000   1.0347   0.04174   0.03010   0.0021   0.1739   1.0000
   9.250   1.0508   0.04344   0.03206   0.0030   0.1691   1.0000
   9.500   1.0698   0.04484   0.03355   0.0037   0.1652   1.0000
   9.750   1.0874   0.04663   0.03547   0.0043   0.1621   1.0000
  10.000   1.0920   0.04941   0.03876   0.0056   0.1582   1.0000
  10.250   1.0995   0.05177   0.04142   0.0067   0.1543   1.0000
  10.500   1.1124   0.05352   0.04330   0.0076   0.1508   1.0000
  10.750   1.1315   0.05497   0.04473   0.0082   0.1479   1.0000
  11.000   1.1144   0.05931   0.04961   0.0098   0.1456   1.0000
  11.250   1.0916   0.06392   0.05459   0.0111   0.1435   1.0000
  11.500   1.0567   0.06926   0.06017   0.0119   0.1423   1.0000
  11.750   0.9983   0.07854   0.06965   0.0086   0.1418   1.0000
  12.000   0.9011   0.09848   0.08963  -0.0039   0.1410   1.0000
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