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NASA RC(4)-10 AIRFOIL (rc410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA RC(4)-10 AIRFOIL (rc410-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.38 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rc410-il-1000000-n5.txt
Download as CSV file: xf-rc410-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -1.2058   0.04760   0.04504  -0.0267   1.0000   0.0109
 -13.750  -1.2248   0.03912   0.03620  -0.0273   1.0000   0.0110
 -13.500  -1.2228   0.03583   0.03269  -0.0264   1.0000   0.0110
 -13.250  -1.2151   0.03336   0.03003  -0.0253   1.0000   0.0111
 -13.000  -1.2040   0.03129   0.02779  -0.0243   1.0000   0.0112
 -12.750  -1.1902   0.02952   0.02587  -0.0233   1.0000   0.0113
 -12.500  -1.1744   0.02796   0.02415  -0.0224   1.0000   0.0114
 -12.250  -1.1570   0.02657   0.02263  -0.0215   1.0000   0.0115
 -12.000  -1.1383   0.02533   0.02125  -0.0207   1.0000   0.0116
 -11.750  -1.1206   0.02442   0.02007  -0.0192   0.8912   0.0116
 -11.500  -1.1019   0.02353   0.01896  -0.0180   0.8587   0.0117
 -11.250  -1.0811   0.02267   0.01791  -0.0171   0.8401   0.0118
 -11.000  -1.0593   0.02186   0.01694  -0.0164   0.8268   0.0119
 -10.750  -1.0367   0.02112   0.01607  -0.0157   0.8161   0.0119
 -10.500  -1.0160   0.01999   0.01478  -0.0148   0.8074   0.0121
 -10.250  -0.9938   0.01910   0.01376  -0.0141   0.7994   0.0124
 -10.000  -0.9702   0.01837   0.01295  -0.0135   0.7930   0.0126
  -9.750  -0.9461   0.01773   0.01220  -0.0130   0.7866   0.0127
  -9.500  -0.9214   0.01714   0.01152  -0.0125   0.7809   0.0129
  -9.250  -0.8963   0.01659   0.01089  -0.0120   0.7754   0.0130
  -9.000  -0.8710   0.01607   0.01029  -0.0116   0.7701   0.0132
  -8.750  -0.8455   0.01557   0.00971  -0.0111   0.7655   0.0134
  -8.500  -0.8197   0.01509   0.00917  -0.0107   0.7613   0.0135
  -8.250  -0.7937   0.01464   0.00864  -0.0104   0.7566   0.0137
  -8.000  -0.7676   0.01421   0.00814  -0.0100   0.7520   0.0139
  -7.750  -0.7412   0.01380   0.00766  -0.0096   0.7478   0.0141
  -7.500  -0.7147   0.01341   0.00721  -0.0093   0.7434   0.0144
  -7.250  -0.6880   0.01304   0.00679  -0.0090   0.7391   0.0146
  -7.000  -0.6612   0.01271   0.00639  -0.0087   0.7351   0.0147
  -6.750  -0.6341   0.01239   0.00602  -0.0084   0.7315   0.0149
  -6.500  -0.6072   0.01202   0.00561  -0.0081   0.7276   0.0152
  -6.250  -0.5804   0.01163   0.00519  -0.0078   0.7233   0.0156
  -6.000  -0.5533   0.01132   0.00483  -0.0075   0.7191   0.0161
  -5.750  -0.5259   0.01104   0.00453  -0.0072   0.7153   0.0165
  -5.500  -0.4985   0.01078   0.00425  -0.0070   0.7112   0.0171
  -5.250  -0.4709   0.01054   0.00398  -0.0068   0.7071   0.0177
  -5.000  -0.4433   0.01033   0.00373  -0.0066   0.7033   0.0182
  -4.750  -0.4157   0.01010   0.00348  -0.0064   0.6997   0.0188
  -4.500  -0.3881   0.00985   0.00324  -0.0062   0.6959   0.0200
  -4.250  -0.3603   0.00964   0.00302  -0.0060   0.6917   0.0214
  -4.000  -0.3326   0.00945   0.00281  -0.0058   0.6875   0.0234
  -3.750  -0.3049   0.00925   0.00261  -0.0056   0.6821   0.0269
  -3.500  -0.2773   0.00903   0.00241  -0.0054   0.6736   0.0330
  -3.250  -0.2498   0.00883   0.00223  -0.0052   0.6653   0.0415
  -3.000  -0.2220   0.00866   0.00209  -0.0050   0.6570   0.0507
  -2.750  -0.1941   0.00852   0.00197  -0.0049   0.6501   0.0588
  -2.500  -0.1659   0.00842   0.00186  -0.0047   0.6418   0.0648
  -2.250  -0.1377   0.00832   0.00177  -0.0046   0.6331   0.0711
  -2.000  -0.1094   0.00825   0.00168  -0.0046   0.6246   0.0752
  -1.750  -0.0812   0.00816   0.00161  -0.0045   0.6158   0.0822
  -1.500  -0.0528   0.00812   0.00154  -0.0044   0.6051   0.0869
  -1.250  -0.0245   0.00806   0.00149  -0.0043   0.5942   0.0933
  -1.000   0.0039   0.00802   0.00144  -0.0043   0.5843   0.0990
  -0.750   0.0322   0.00800   0.00139  -0.0042   0.5713   0.1033
  -0.500   0.0605   0.00799   0.00135  -0.0042   0.5533   0.1077
  -0.250   0.0887   0.00802   0.00131  -0.0041   0.5290   0.1122
   0.000   0.1167   0.00812   0.00129  -0.0041   0.4938   0.1149
   0.250   0.1420   0.00888   0.00146  -0.0040   0.3270   0.1195
   0.500   0.1693   0.00914   0.00154  -0.0039   0.2741   0.1247
   0.750   0.1971   0.00930   0.00159  -0.0039   0.2434   0.1293
   1.000   0.2251   0.00939   0.00162  -0.0039   0.2249   0.1344
   1.250   0.2531   0.00945   0.00165  -0.0039   0.2122   0.1407
   1.750   0.3091   0.00956   0.00174  -0.0038   0.1933   0.1576
   2.000   0.3371   0.00960   0.00178  -0.0038   0.1854   0.1697
   2.250   0.3649   0.00963   0.00184  -0.0037   0.1779   0.1928
   2.500   0.3850   0.00849   0.00185  -0.0027   0.1740   0.6168
   2.750   0.4098   0.00825   0.00191  -0.0020   0.1689   0.7146
   3.000   0.4298   0.00783   0.00202  -0.0001   0.1638   0.8758
   3.250   0.4591   0.00782   0.00215  -0.0001   0.1595   0.9397
   3.500   0.4997   0.00798   0.00230  -0.0029   0.1538   0.9645
   3.750   0.5374   0.00816   0.00244  -0.0050   0.1485   0.9765
   4.250   0.6045   0.00844   0.00268  -0.0074   0.1418   0.9881
   4.500   0.6378   0.00862   0.00281  -0.0086   0.1370   0.9924
   4.750   0.6721   0.00879   0.00295  -0.0100   0.1330   0.9950
   5.000   0.7071   0.00893   0.00309  -0.0116   0.1305   0.9970
   5.250   0.7426   0.00909   0.00323  -0.0133   0.1270   0.9990
   5.500   0.7742   0.00928   0.00337  -0.0142   0.1229   1.0000
   5.750   0.7992   0.00945   0.00353  -0.0137   0.1195   1.0000
   6.000   0.8244   0.00960   0.00368  -0.0131   0.1178   1.0000
   6.250   0.8496   0.00976   0.00384  -0.0126   0.1154   1.0000
   6.500   0.8745   0.00994   0.00401  -0.0121   0.1122   1.0000
   6.750   0.8993   0.01015   0.00419  -0.0115   0.1087   1.0000
   7.000   0.9241   0.01035   0.00439  -0.0110   0.1063   1.0000
   7.250   0.9492   0.01052   0.00458  -0.0105   0.1047   1.0000
   7.500   0.9740   0.01072   0.00478  -0.0099   0.1023   1.0000
   7.750   0.9986   0.01094   0.00499  -0.0094   0.0993   1.0000
   8.000   1.0230   0.01119   0.00522  -0.0088   0.0962   1.0000
   8.250   1.0475   0.01142   0.00547  -0.0083   0.0939   1.0000
   8.500   1.0722   0.01163   0.00570  -0.0078   0.0922   1.0000
   8.750   1.0965   0.01187   0.00595  -0.0072   0.0896   1.0000
   9.000   1.1205   0.01214   0.00621  -0.0067   0.0867   1.0000
   9.250   1.1441   0.01245   0.00651  -0.0061   0.0832   1.0000
   9.500   1.1683   0.01270   0.00679  -0.0055   0.0815   1.0000
   9.750   1.1923   0.01297   0.00707  -0.0050   0.0792   1.0000
  10.000   1.2160   0.01327   0.00739  -0.0044   0.0766   1.0000
  10.250   1.2392   0.01363   0.00773  -0.0039   0.0734   1.0000
  10.500   1.2627   0.01395   0.00808  -0.0033   0.0712   1.0000
  10.750   1.2863   0.01426   0.00842  -0.0028   0.0690   1.0000
  11.000   1.3090   0.01466   0.00881  -0.0022   0.0654   1.0000
  11.250   1.3313   0.01509   0.00923  -0.0016   0.0615   1.0000
  11.500   1.3537   0.01549   0.00964  -0.0011   0.0579   1.0000
  11.750   1.3749   0.01601   0.01014  -0.0004   0.0538   1.0000
  12.000   1.3967   0.01645   0.01060   0.0002   0.0510   1.0000
  12.250   1.4173   0.01698   0.01114   0.0009   0.0474   1.0000
  12.500   1.4375   0.01753   0.01169   0.0017   0.0443   1.0000
  12.750   1.4574   0.01809   0.01227   0.0025   0.0412   1.0000
  13.000   1.4755   0.01877   0.01295   0.0034   0.0379   1.0000
  13.250   1.4940   0.01937   0.01358   0.0043   0.0355   1.0000
  13.500   1.5099   0.02012   0.01435   0.0054   0.0326   1.0000
  13.750   1.5238   0.02084   0.01511   0.0068   0.0305   1.0000
  14.000   1.5363   0.02168   0.01598   0.0082   0.0282   1.0000
  14.250   1.5474   0.02270   0.01703   0.0095   0.0260   1.0000
  14.500   1.5593   0.02372   0.01810   0.0105   0.0241   1.0000
  14.750   1.5690   0.02498   0.01939   0.0114   0.0221   1.0000
  15.000   1.5791   0.02624   0.02071   0.0122   0.0204   1.0000
  15.250   1.5870   0.02775   0.02226   0.0130   0.0185   1.0000
  15.500   1.5945   0.02931   0.02388   0.0136   0.0170   1.0000
  15.750   1.6009   0.03102   0.02565   0.0142   0.0156   1.0000
  16.000   1.6047   0.03300   0.02769   0.0147   0.0143   1.0000
  16.250   1.6094   0.03493   0.02970   0.0151   0.0134   1.0000
  16.500   1.6114   0.03717   0.03201   0.0153   0.0124   1.0000
  17.000   1.6101   0.04238   0.03739   0.0154   0.0109   1.0000
  17.250   1.6075   0.04532   0.04043   0.0152   0.0103   1.0000
  17.500   1.6013   0.04875   0.04396   0.0147   0.0098   1.0000
  17.750   1.5924   0.05266   0.04798   0.0139   0.0094   1.0000
  18.000   1.5810   0.05710   0.05254   0.0126   0.0090   1.0000
  18.250   1.5682   0.06205   0.05762   0.0109   0.0088   1.0000
  18.500   1.5505   0.06802   0.06374   0.0084   0.0087   1.0000
  18.750   1.5247   0.07568   0.07158   0.0048   0.0086   1.0000
  19.000   1.4840   0.08660   0.08273  -0.0008   0.0088   1.0000
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