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cr001sm (cr001sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.86 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr001sm-il-1000000.txt
Download as CSV file: xf-cr001sm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: cr001sm                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3015   0.13330   0.13166  -0.0278   1.0000   0.0067
 -12.250  -0.2993   0.13036   0.12873  -0.0283   1.0000   0.0068
 -12.000  -0.2970   0.12740   0.12578  -0.0286   1.0000   0.0068
  -6.500  -0.1774   0.04206   0.04057  -0.0722   0.9763   0.0105
  -6.250  -0.1526   0.03659   0.03507  -0.0808   0.9744   0.0106
  -6.000  -0.1232   0.03131   0.02974  -0.0896   0.9730   0.0109
  -5.750  -0.0987   0.02678   0.02514  -0.0960   0.9673   0.0113
  -5.500  -0.0686   0.02141   0.01964  -0.1037   0.9630   0.0118
  -5.250  -0.0320   0.01655   0.01457  -0.1099   0.9600   0.0143
  -4.250   0.0671   0.01685   0.01323  -0.1223   0.9481   0.0149
  -4.000   0.0950   0.01381   0.00989  -0.1230   0.9423   0.0135
  -3.750   0.1219   0.01100   0.00663  -0.1227   0.9349   0.0124
  -3.500   0.1505   0.00973   0.00515  -0.1226   0.9282   0.0128
  -3.250   0.1789   0.00912   0.00442  -0.1226   0.9205   0.0138
  -3.000   0.2073   0.00896   0.00419  -0.1225   0.9123   0.0145
  -2.500   0.2608   0.00742   0.00245  -0.1219   0.8938   0.0172
  -2.250   0.2882   0.00726   0.00226  -0.1217   0.8840   0.0195
  -2.000   0.3155   0.00706   0.00198  -0.1214   0.8738   0.0208
  -1.750   0.3423   0.00682   0.00165  -0.1210   0.8627   0.0219
  -1.500   0.3687   0.00655   0.00130  -0.1206   0.8510   0.0257
  -1.250   0.3953   0.00645   0.00115  -0.1201   0.8390   0.0289
  -1.000   0.4218   0.00635   0.00098  -0.1197   0.8261   0.0362
  -0.750   0.4469   0.00590   0.00088  -0.1192   0.8122   0.1762
  -0.500   0.4716   0.00559   0.00088  -0.1186   0.7965   0.3148
  -0.250   0.4964   0.00543   0.00089  -0.1180   0.7789   0.4146
   0.000   0.5208   0.00526   0.00092  -0.1173   0.7605   0.5216
   0.250   0.5429   0.00491   0.00100  -0.1160   0.7418   0.7078
   0.500   0.5799   0.00442   0.00102  -0.1179   0.7226   1.0000
   0.750   0.6052   0.00453   0.00104  -0.1173   0.7036   1.0000
   1.000   0.6304   0.00466   0.00106  -0.1166   0.6833   1.0000
   1.250   0.6555   0.00481   0.00109  -0.1159   0.6635   1.0000
   1.500   0.6809   0.00494   0.00113  -0.1153   0.6432   1.0000
   2.000   0.7314   0.00525   0.00125  -0.1141   0.6023   1.0000
   2.250   0.7565   0.00542   0.00132  -0.1134   0.5815   1.0000
   2.500   0.7818   0.00559   0.00140  -0.1129   0.5603   1.0000
   2.750   0.8068   0.00577   0.00151  -0.1122   0.5388   1.0000
   3.000   0.8321   0.00595   0.00160  -0.1117   0.5172   1.0000
   3.250   0.8569   0.00617   0.00172  -0.1110   0.4947   1.0000
   3.500   0.8819   0.00638   0.00184  -0.1104   0.4702   1.0000
   3.750   0.9065   0.00661   0.00198  -0.1098   0.4444   1.0000
   4.000   0.9310   0.00687   0.00213  -0.1091   0.4175   1.0000
   4.250   0.9551   0.00716   0.00230  -0.1084   0.3866   1.0000
   4.500   0.9787   0.00750   0.00249  -0.1076   0.3539   1.0000
   4.750   1.0022   0.00785   0.00271  -0.1069   0.3190   1.0000
   5.000   1.0249   0.00828   0.00297  -0.1060   0.2817   1.0000
   5.250   1.0480   0.00868   0.00322  -0.1051   0.2491   1.0000
   5.500   1.0708   0.00910   0.00350  -0.1043   0.2175   1.0000
   5.750   1.0931   0.00957   0.00380  -0.1033   0.1857   1.0000
   6.000   1.1162   0.00996   0.00410  -0.1026   0.1618   1.0000
   6.250   1.1394   0.01033   0.00440  -0.1018   0.1420   1.0000
   6.500   1.1621   0.01075   0.00472  -0.1009   0.1213   1.0000
   6.750   1.1846   0.01118   0.00506  -0.1000   0.1013   1.0000
   7.000   1.2060   0.01170   0.00546  -0.0990   0.0796   1.0000
   7.250   1.2271   0.01226   0.00592  -0.0979   0.0592   1.0000
   7.500   1.2479   0.01282   0.00640  -0.0967   0.0422   1.0000
   7.750   1.2680   0.01345   0.00693  -0.0955   0.0281   1.0000
   8.000   1.2881   0.01408   0.00751  -0.0942   0.0194   1.0000
   8.250   1.3092   0.01459   0.00806  -0.0930   0.0159   1.0000
   8.500   1.3295   0.01515   0.00863  -0.0918   0.0136   1.0000
   8.750   1.3485   0.01584   0.00941  -0.0903   0.0116   1.0000
   9.000   1.3694   0.01629   0.00990  -0.0892   0.0108   1.0000
   9.250   1.3894   0.01680   0.01046  -0.0879   0.0098   1.0000
   9.500   1.4066   0.01755   0.01125  -0.0862   0.0087   1.0000
   9.750   1.4205   0.01855   0.01238  -0.0839   0.0078   1.0000
  10.000   1.4387   0.01911   0.01300  -0.0824   0.0074   1.0000
  10.250   1.4549   0.01978   0.01374  -0.0806   0.0068   1.0000
  10.500   1.4693   0.02044   0.01447  -0.0785   0.0064   1.0000
  10.750   1.4808   0.02121   0.01532  -0.0759   0.0060   1.0000
  11.000   1.4884   0.02222   0.01640  -0.0727   0.0055   1.0000
  11.250   1.4849   0.02397   0.01833  -0.0680   0.0052   1.0000
  11.500   1.4854   0.02552   0.02002  -0.0642   0.0050   1.0000
  11.750   1.4978   0.02625   0.02083  -0.0622   0.0049   1.0000
  12.000   1.5035   0.02750   0.02219  -0.0595   0.0048   1.0000
  12.250   1.5068   0.02897   0.02378  -0.0567   0.0047   1.0000
  12.500   1.5106   0.03046   0.02539  -0.0542   0.0045   1.0000
  12.750   1.5133   0.03212   0.02716  -0.0518   0.0043   1.0000
  13.000   1.5139   0.03403   0.02921  -0.0496   0.0042   1.0000
  13.250   1.5161   0.03588   0.03118  -0.0477   0.0041   1.0000
  13.500   1.5168   0.03797   0.03339  -0.0461   0.0040   1.0000
  13.750   1.5139   0.04054   0.03610  -0.0445   0.0039   1.0000
  14.000   1.5134   0.04301   0.03867  -0.0435   0.0038   1.0000
  14.250   1.5102   0.04591   0.04170  -0.0427   0.0037   1.0000
  14.500   1.5036   0.04940   0.04534  -0.0422   0.0037   1.0000
  14.750   1.4987   0.05290   0.04896  -0.0422   0.0036   1.0000
  15.000   1.4883   0.05735   0.05357  -0.0427   0.0036   1.0000
  15.250   1.4803   0.06176   0.05811  -0.0436   0.0036   1.0000
  15.500   1.4669   0.06730   0.06381  -0.0452   0.0035   1.0000
  15.750   1.4563   0.07269   0.06934  -0.0472   0.0035   1.0000
  16.000   1.4412   0.07918   0.07599  -0.0499   0.0035   1.0000
  16.250   1.4255   0.08612   0.08309  -0.0531   0.0035   1.0000
  16.500   1.4106   0.09324   0.09035  -0.0567   0.0035   1.0000
  16.750   1.3909   0.10166   0.09895  -0.0610   0.0035   1.0000
  17.000   1.3722   0.11023   0.10767  -0.0658   0.0035   1.0000
  17.250   1.3547   0.11885   0.11644  -0.0706   0.0035   1.0000
  17.500   1.3338   0.12857   0.12632  -0.0763   0.0036   1.0000
  17.750   1.3140   0.13837   0.13626  -0.0821   0.0036   1.0000
  18.000   1.2914   0.14917   0.14722  -0.0887   0.0036   1.0000
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