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cr001sm (cr001sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: cr001sm (cr001sm-il)
Reynolds number: 500,000
Max Cl/Cd: 120.16 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr001sm-il-500000.txt
Download as CSV file: xf-cr001sm-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3608   0.09535   0.09318  -0.0269   1.0000   0.0145
  -7.750  -0.3675   0.09347   0.09135  -0.0252   1.0000   0.0145
  -7.500  -0.3782   0.09194   0.08986  -0.0227   1.0000   0.0145
  -7.250  -0.3794   0.08950   0.08746  -0.0231   0.9989   0.0145
  -7.000  -0.3535   0.08417   0.08212  -0.0313   0.9956   0.0146
  -6.750  -0.3281   0.07879   0.07671  -0.0394   0.9917   0.0146
  -6.500  -0.3101   0.07113   0.06905  -0.0480   0.9879   0.0151
  -6.250  -0.2822   0.06649   0.06439  -0.0551   0.9856   0.0154
  -6.000  -0.2583   0.06261   0.06049  -0.0603   0.9811   0.0159
  -5.750  -0.2276   0.05804   0.05587  -0.0678   0.9773   0.0165
  -5.500  -0.1897   0.05255   0.05030  -0.0774   0.9747   0.0174
  -5.250  -0.1449   0.04601   0.04362  -0.0885   0.9729   0.0192
  -5.000  -0.1025   0.04041   0.03773  -0.0954   0.9667   0.0211
  -4.750  -0.0636   0.03532   0.03227  -0.1012   0.9635   0.0213
  -4.500  -0.0322   0.02815   0.02484  -0.1074   0.9613   0.0231
  -4.250   0.0036   0.02627   0.02283  -0.1107   0.9600   0.0252
  -4.000   0.0373   0.02452   0.02079  -0.1119   0.9558   0.0293
  -3.750   0.0712   0.02087   0.01656  -0.1140   0.9516   0.0315
  -3.500   0.1055   0.01843   0.01401  -0.1163   0.9491   0.0336
  -3.250   0.1449   0.01502   0.00987  -0.1171   0.9469   0.0216
  -3.000   0.1765   0.01349   0.00810  -0.1176   0.9425   0.0214
  -2.750   0.2055   0.01145   0.00583  -0.1177   0.9368   0.0221
  -2.500   0.2391   0.01049   0.00484  -0.1189   0.9329   0.0249
  -2.250   0.2673   0.00985   0.00415  -0.1188   0.9258   0.0268
  -2.000   0.2989   0.00927   0.00349  -0.1193   0.9197   0.0287
  -1.750   0.3276   0.00893   0.00310  -0.1192   0.9115   0.0304
  -1.500   0.3585   0.00831   0.00241  -0.1197   0.9044   0.0360
  -1.250   0.3856   0.00807   0.00212  -0.1193   0.8942   0.0410
  -1.000   0.4130   0.00736   0.00181  -0.1193   0.8844   0.1788
  -0.750   0.4398   0.00673   0.00177  -0.1193   0.8744   0.4007
  -0.500   0.4653   0.00635   0.00176  -0.1188   0.8630   0.5492
  -0.250   0.4872   0.00586   0.00179  -0.1173   0.8505   0.7361
   0.000   0.5288   0.00537   0.00169  -0.1199   0.8388   1.0000
   0.250   0.5555   0.00543   0.00163  -0.1195   0.8238   1.0000
   0.500   0.5817   0.00551   0.00159  -0.1189   0.8074   1.0000
   0.750   0.6075   0.00560   0.00156  -0.1182   0.7900   1.0000
   1.000   0.6331   0.00569   0.00156  -0.1176   0.7718   1.0000
   1.250   0.6586   0.00581   0.00156  -0.1169   0.7534   1.0000
   1.500   0.6839   0.00594   0.00159  -0.1162   0.7349   1.0000
   1.750   0.7090   0.00607   0.00163  -0.1155   0.7151   1.0000
   2.000   0.7340   0.00622   0.00168  -0.1147   0.6953   1.0000
   2.250   0.7589   0.00638   0.00175  -0.1140   0.6750   1.0000
   2.500   0.7836   0.00655   0.00183  -0.1132   0.6541   1.0000
   2.750   0.8082   0.00674   0.00193  -0.1124   0.6328   1.0000
   3.000   0.8327   0.00693   0.00204  -0.1116   0.6111   1.0000
   3.250   0.8571   0.00714   0.00216  -0.1109   0.5884   1.0000
   3.750   0.9055   0.00758   0.00246  -0.1093   0.5422   1.0000
   4.000   0.9293   0.00783   0.00262  -0.1084   0.5172   1.0000
   4.250   0.9529   0.00811   0.00280  -0.1075   0.4909   1.0000
   4.500   0.9763   0.00840   0.00300  -0.1067   0.4624   1.0000
   4.750   0.9994   0.00873   0.00321  -0.1057   0.4310   1.0000
   5.000   1.0220   0.00910   0.00347  -0.1047   0.3976   1.0000
   5.250   1.0442   0.00952   0.00375  -0.1037   0.3600   1.0000
   5.500   1.0658   0.01001   0.00406  -0.1026   0.3194   1.0000
   5.750   1.0872   0.01053   0.00440  -0.1015   0.2807   1.0000
   6.000   1.1085   0.01107   0.00478  -0.1005   0.2447   1.0000
   6.250   1.1297   0.01162   0.00519  -0.0994   0.2116   1.0000
   6.500   1.1511   0.01215   0.00560  -0.0983   0.1820   1.0000
   6.750   1.1725   0.01268   0.00601  -0.0973   0.1562   1.0000
   7.000   1.1936   0.01324   0.00646  -0.0963   0.1318   1.0000
   7.250   1.2144   0.01381   0.00695  -0.0951   0.1074   1.0000
   7.500   1.2342   0.01447   0.00750  -0.0939   0.0822   1.0000
   7.750   1.2522   0.01530   0.00817  -0.0923   0.0563   1.0000
   8.000   1.2690   0.01624   0.00898  -0.0906   0.0359   1.0000
   8.250   1.2856   0.01719   0.00991  -0.0887   0.0262   1.0000
   8.500   1.3039   0.01794   0.01075  -0.0870   0.0224   1.0000
   8.750   1.3205   0.01880   0.01167  -0.0852   0.0191   1.0000
   9.000   1.3332   0.01996   0.01294  -0.0827   0.0170   1.0000
   9.250   1.3497   0.02073   0.01381  -0.0809   0.0158   1.0000
   9.500   1.3642   0.02159   0.01475  -0.0788   0.0145   1.0000
   9.750   1.3758   0.02250   0.01573  -0.0763   0.0132   1.0000
  10.000   1.3736   0.02444   0.01780  -0.0716   0.0120   1.0000
  10.250   1.3845   0.02538   0.01886  -0.0691   0.0114   1.0000
  10.500   1.3947   0.02639   0.01998  -0.0666   0.0108   1.0000
  10.750   1.4017   0.02771   0.02142  -0.0637   0.0103   1.0000
  11.000   1.4093   0.02896   0.02280  -0.0612   0.0097   1.0000
  11.250   1.4152   0.03040   0.02435  -0.0586   0.0093   1.0000
  11.500   1.4198   0.03199   0.02605  -0.0561   0.0090   1.0000
  11.750   1.4215   0.03392   0.02808  -0.0536   0.0086   1.0000
  12.000   1.4204   0.03639   0.03071  -0.0510   0.0083   1.0000
  12.250   1.4160   0.03958   0.03410  -0.0484   0.0081   1.0000
  12.500   1.4061   0.04396   0.03875  -0.0459   0.0079   1.0000
  12.750   1.4055   0.04627   0.04125  -0.0444   0.0078   1.0000
  13.000   1.4018   0.04921   0.04440  -0.0430   0.0077   1.0000
  13.250   1.3954   0.05266   0.04805  -0.0420   0.0077   1.0000
  13.500   1.3870   0.05652   0.05211  -0.0415   0.0076   1.0000
  13.750   1.3770   0.06073   0.05654  -0.0415   0.0075   1.0000
  14.000   1.3633   0.06581   0.06183  -0.0421   0.0076   1.0000
  14.250   1.3488   0.07124   0.06746  -0.0434   0.0076   1.0000
  14.500   1.3334   0.07720   0.07363  -0.0455   0.0076   1.0000
  14.750   1.3158   0.08394   0.08057  -0.0484   0.0076   1.0000
  15.000   1.2980   0.09122   0.08804  -0.0520   0.0076   1.0000
  15.250   1.2792   0.09920   0.09619  -0.0564   0.0076   1.0000
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