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NASA RC(4)-10 AIRFOIL (rc410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA RC(4)-10 AIRFOIL (rc410-il)
Reynolds number: 100,000
Max Cl/Cd: 39.12 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rc410-il-100000.txt
Download as CSV file: xf-rc410-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5157   0.10604   0.10135   0.0066   1.0000   0.1057
  -8.750  -0.5386   0.10234   0.09776  -0.0042   1.0000   0.1078
  -8.500  -0.5628   0.09845   0.09380  -0.0140   1.0000   0.1083
  -8.250  -0.5160   0.09313   0.08862  -0.0025   1.0000   0.1111
  -8.000  -0.5046   0.08980   0.08531  -0.0022   1.0000   0.1141
  -7.750  -0.5034   0.08578   0.08135  -0.0058   1.0000   0.1173
  -7.500  -0.5199   0.08121   0.07665  -0.0174   1.0000   0.1225
  -7.250  -0.5200   0.07602   0.07136  -0.0211   1.0000   0.1241
  -7.000  -0.5011   0.07156   0.06703  -0.0199   1.0000   0.1258
  -6.750  -0.4866   0.06808   0.06359  -0.0201   1.0000   0.1285
  -6.500  -0.4754   0.06458   0.06005  -0.0218   1.0000   0.1327
  -6.250  -0.4867   0.06287   0.05782  -0.0241   1.0000   0.1394
  -6.000  -0.4881   0.05943   0.05453  -0.0212   1.0000   0.1404
  -5.750  -0.4901   0.05706   0.05223  -0.0181   1.0000   0.1417
  -5.500  -0.4904   0.05495   0.05012  -0.0154   1.0000   0.1436
  -5.250  -0.4629   0.04351   0.03740  -0.0200   0.9922   0.0960
  -5.000  -0.4308   0.03909   0.03259  -0.0222   0.9856   0.0914
  -4.750  -0.3991   0.03482   0.02781  -0.0241   0.9793   0.0900
  -4.500  -0.3657   0.03124   0.02350  -0.0254   0.9730   0.0930
  -4.250  -0.3301   0.02948   0.02166  -0.0278   0.9680   0.0997
  -4.000  -0.2969   0.02761   0.01912  -0.0285   0.9614   0.1081
  -3.750  -0.2578   0.02622   0.01770  -0.0312   0.9569   0.1206
  -3.500  -0.2250   0.02512   0.01649  -0.0326   0.9507   0.1340
  -3.250  -0.1912   0.02412   0.01534  -0.0340   0.9448   0.1486
  -3.000  -0.1532   0.02310   0.01417  -0.0361   0.9407   0.1630
  -2.750  -0.1253   0.02238   0.01331  -0.0363   0.9340   0.1742
  -2.500  -0.0913   0.02187   0.01264  -0.0375   0.9284   0.1861
  -2.250  -0.0535   0.02094   0.01181  -0.0395   0.9244   0.1976
  -2.000  -0.0291   0.02050   0.01138  -0.0391   0.9174   0.2068
  -1.750   0.0028   0.02012   0.01099  -0.0399   0.9123   0.2178
  -1.500   0.0355   0.01956   0.01061  -0.0408   0.9074   0.2307
  -1.250   0.0604   0.01921   0.01038  -0.0401   0.8981   0.2425
  -1.000   0.0889   0.01882   0.01009  -0.0396   0.8883   0.2607
  -0.750   0.1169   0.01833   0.00974  -0.0387   0.8772   0.2879
  -0.500   0.2441   0.01564   0.00929  -0.0532   0.8664   1.0000
  -0.250   0.2640   0.01579   0.00927  -0.0512   0.8547   1.0000
   0.000   0.2833   0.01590   0.00922  -0.0489   0.8439   1.0000
   0.250   0.3034   0.01602   0.00924  -0.0471   0.8311   1.0000
   0.500   0.3231   0.01613   0.00925  -0.0450   0.8184   1.0000
   0.750   0.3425   0.01619   0.00922  -0.0427   0.8054   1.0000
   1.000   0.3616   0.01618   0.00911  -0.0401   0.7919   1.0000
   1.250   0.3810   0.01612   0.00896  -0.0374   0.7791   1.0000
   1.500   0.4018   0.01610   0.00888  -0.0353   0.7654   1.0000
   1.750   0.4227   0.01602   0.00876  -0.0332   0.7506   1.0000
   2.000   0.4435   0.01586   0.00855  -0.0309   0.7348   1.0000
   2.250   0.4645   0.01562   0.00825  -0.0284   0.7176   1.0000
   2.500   0.4856   0.01527   0.00785  -0.0258   0.6978   1.0000
   2.750   0.5069   0.01485   0.00741  -0.0234   0.6697   1.0000
   3.000   0.5280   0.01434   0.00683  -0.0207   0.6264   1.0000
   3.250   0.5473   0.01399   0.00611  -0.0176   0.5203   1.0000
   3.500   0.5628   0.01498   0.00598  -0.0150   0.3817   1.0000
   3.750   0.5831   0.01593   0.00649  -0.0138   0.3425   1.0000
   4.000   0.6050   0.01672   0.00699  -0.0128   0.3204   1.0000
   4.250   0.6280   0.01745   0.00752  -0.0118   0.3046   1.0000
   4.500   0.6517   0.01815   0.00808  -0.0110   0.2917   1.0000
   4.750   0.6756   0.01890   0.00868  -0.0103   0.2807   1.0000
   5.000   0.6997   0.01963   0.00930  -0.0096   0.2705   1.0000
   5.250   0.7242   0.02038   0.01004  -0.0090   0.2621   1.0000
   5.500   0.7488   0.02118   0.01073  -0.0084   0.2543   1.0000
   5.750   0.7732   0.02199   0.01158  -0.0079   0.2469   1.0000
   6.000   0.7976   0.02277   0.01235  -0.0073   0.2395   1.0000
   6.250   0.8223   0.02379   0.01333  -0.0068   0.2337   1.0000
   6.500   0.8463   0.02463   0.01432  -0.0062   0.2275   1.0000
   6.750   0.8706   0.02557   0.01523  -0.0057   0.2217   1.0000
   7.000   0.8939   0.02667   0.01646  -0.0051   0.2162   1.0000
   7.250   0.9172   0.02767   0.01761  -0.0045   0.2107   1.0000
   7.500   0.9410   0.02875   0.01870  -0.0040   0.2060   1.0000
   7.750   0.9632   0.03016   0.02027  -0.0035   0.2013   1.0000
   8.000   0.9843   0.03133   0.02170  -0.0027   0.1959   1.0000
   8.250   1.0071   0.03250   0.02294  -0.0021   0.1915   1.0000
   8.500   1.0299   0.03430   0.02470  -0.0018   0.1876   1.0000
   8.750   1.0459   0.03586   0.02676  -0.0006   0.1832   1.0000
   9.000   1.0645   0.03735   0.02848   0.0002   0.1784   1.0000
   9.250   1.0868   0.03868   0.02981   0.0007   0.1746   1.0000
   9.500   1.1042   0.04097   0.03225   0.0014   0.1712   1.0000
   9.750   1.1115   0.04348   0.03532   0.0029   0.1673   1.0000
  10.000   1.1231   0.04565   0.03777   0.0040   0.1632   1.0000
  10.250   1.1440   0.04701   0.03913   0.0046   0.1597   1.0000
  10.500   1.1608   0.04947   0.04160   0.0050   0.1565   1.0000
  10.750   1.1488   0.05355   0.04633   0.0072   0.1539   1.0000
  11.000   1.1334   0.05804   0.05125   0.0089   0.1516   1.0000
  11.250   1.1098   0.06307   0.05659   0.0103   0.1502   1.0000
  11.500   1.0535   0.07059   0.06438   0.0109   0.1513   1.0000
  11.750   0.9760   0.08369   0.07762   0.0051   0.1545   1.0000
  12.000   0.9246   0.09797   0.09194  -0.0028   0.1578   1.0000
  12.250   0.9262   0.10301   0.09700  -0.0034   0.1569   1.0000
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