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CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il)
Reynolds number: 1,000,000
Max Cl/Cd: 93.9 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cast102-il-1000000.txt
Download as CSV file: xf-cast102-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CAST 10-2/DOA 2 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5060   0.07657   0.07489  -0.0640   0.9955   0.0120
 -10.000  -0.5189   0.06829   0.06651  -0.0726   0.9902   0.0120
  -9.750  -0.5290   0.06258   0.06068  -0.0778   0.9834   0.0121
  -9.500  -0.5404   0.05875   0.05674  -0.0783   0.9729   0.0121
  -9.250  -0.5454   0.05556   0.05342  -0.0776   0.9645   0.0122
  -9.000  -0.5460   0.05251   0.05024  -0.0767   0.9579   0.0123
  -8.750  -0.5430   0.04950   0.04710  -0.0759   0.9519   0.0125
  -8.500  -0.5377   0.04652   0.04395  -0.0749   0.9468   0.0128
  -8.250  -0.5294   0.04342   0.04067  -0.0739   0.9424   0.0133
  -8.000  -0.5161   0.03894   0.03570  -0.0714   0.9378   0.0148
  -7.750  -0.5055   0.03590   0.03236  -0.0699   0.9337   0.0148
  -7.500  -0.5024   0.03012   0.02626  -0.0684   0.9295   0.0153
  -7.250  -0.4826   0.02853   0.02458  -0.0681   0.9268   0.0155
  -7.000  -0.4617   0.02708   0.02301  -0.0678   0.9240   0.0158
  -6.750  -0.4400   0.02563   0.02143  -0.0674   0.9211   0.0162
  -6.500  -0.4177   0.02411   0.01975  -0.0669   0.9184   0.0168
  -6.250  -0.3906   0.02427   0.01961  -0.0661   0.9159   0.0187
  -6.000  -0.3723   0.01735   0.01201  -0.0640   0.9132   0.0151
  -5.750  -0.3465   0.01573   0.01025  -0.0637   0.9113   0.0151
  -5.500  -0.3207   0.01443   0.00887  -0.0636   0.9091   0.0153
  -5.250  -0.2948   0.01354   0.00795  -0.0634   0.9067   0.0156
  -5.000  -0.2687   0.01286   0.00724  -0.0633   0.9044   0.0159
  -4.750  -0.2426   0.01227   0.00662  -0.0632   0.9023   0.0162
  -4.500  -0.2162   0.01179   0.00612  -0.0631   0.9003   0.0167
  -4.250  -0.1895   0.01142   0.00573  -0.0630   0.8981   0.0175
  -4.000  -0.1627   0.01097   0.00526  -0.0630   0.8962   0.0181
  -3.750  -0.1357   0.01060   0.00487  -0.0631   0.8941   0.0186
  -3.500  -0.1089   0.01018   0.00443  -0.0631   0.8917   0.0190
  -3.250  -0.0830   0.00956   0.00378  -0.0630   0.8895   0.0198
  -3.000  -0.0553   0.00927   0.00348  -0.0632   0.8876   0.0206
  -2.750  -0.0272   0.00905   0.00326  -0.0634   0.8858   0.0217
  -2.500   0.0010   0.00890   0.00309  -0.0637   0.8839   0.0231
  -2.250   0.0294   0.00871   0.00288  -0.0639   0.8819   0.0241
  -2.000   0.0576   0.00844   0.00261  -0.0642   0.8797   0.0263
  -1.750   0.0861   0.00827   0.00244  -0.0645   0.8766   0.0288
  -1.500   0.1143   0.00805   0.00221  -0.0646   0.8724   0.0365
  -1.250   0.1356   0.00581   0.00177  -0.0649   0.8677   0.6084
  -1.000   0.1638   0.00571   0.00176  -0.0649   0.8627   0.6480
  -0.750   0.1924   0.00565   0.00171  -0.0651   0.8574   0.6631
  -0.500   0.2209   0.00562   0.00167  -0.0651   0.8514   0.6732
  -0.250   0.2493   0.00557   0.00162  -0.0652   0.8436   0.6841
   0.000   0.2778   0.00557   0.00159  -0.0653   0.8368   0.6945
   0.250   0.3065   0.00552   0.00157  -0.0655   0.8298   0.7002
   0.500   0.3353   0.00551   0.00155  -0.0657   0.8242   0.7056
   0.750   0.3643   0.00551   0.00155  -0.0660   0.8178   0.7104
   1.000   0.3931   0.00550   0.00153  -0.0663   0.8108   0.7139
   1.250   0.4219   0.00548   0.00154  -0.0666   0.8040   0.7177
   1.500   0.4505   0.00548   0.00153  -0.0668   0.7947   0.7215
   1.750   0.4787   0.00550   0.00152  -0.0668   0.7790   0.7253
   2.000   0.5062   0.00555   0.00151  -0.0668   0.7533   0.7290
   2.250   0.5324   0.00567   0.00153  -0.0665   0.7175   0.7331
   2.500   0.5535   0.00615   0.00165  -0.0651   0.6240   0.7376
   2.750   0.5703   0.00704   0.00197  -0.0632   0.4936   0.7421
   3.000   0.5901   0.00772   0.00225  -0.0619   0.3957   0.7465
   3.250   0.6131   0.00817   0.00246  -0.0613   0.3368   0.7512
   3.500   0.6376   0.00851   0.00264  -0.0608   0.2949   0.7562
   3.750   0.6621   0.00885   0.00282  -0.0604   0.2567   0.7611
   4.000   0.6868   0.00914   0.00301  -0.0600   0.2262   0.7666
   4.250   0.7121   0.00941   0.00319  -0.0598   0.2032   0.7724
   4.500   0.7374   0.00965   0.00337  -0.0595   0.1842   0.7781
   4.750   0.7628   0.00988   0.00357  -0.0592   0.1671   0.7842
   5.250   0.8134   0.01035   0.00397  -0.0586   0.1396   0.7976
   5.500   0.8385   0.01060   0.00419  -0.0583   0.1277   0.8054
   5.750   0.8635   0.01082   0.00441  -0.0580   0.1159   0.8135
   6.000   0.8886   0.01105   0.00463  -0.0577   0.1058   0.8224
   6.250   0.9131   0.01129   0.00487  -0.0572   0.0951   0.8324
   6.500   0.9370   0.01157   0.00514  -0.0567   0.0828   0.8434
   6.750   0.9598   0.01193   0.00545  -0.0560   0.0671   0.8567
   7.000   0.9791   0.01255   0.00593  -0.0546   0.0377   0.8737
   7.250   0.9994   0.01301   0.00639  -0.0533   0.0285   0.8960
   7.500   1.0190   0.01325   0.00676  -0.0517   0.0265   0.9284
   7.750   1.0397   0.01356   0.00715  -0.0504   0.0243   1.0000
   8.000   1.0625   0.01407   0.00769  -0.0497   0.0225   1.0000
   8.250   1.0860   0.01446   0.00811  -0.0492   0.0217   1.0000
   8.500   1.1089   0.01489   0.00858  -0.0486   0.0206   1.0000
   8.750   1.1309   0.01539   0.00909  -0.0478   0.0196   1.0000
   9.000   1.1506   0.01609   0.00983  -0.0467   0.0184   1.0000
   9.250   1.1692   0.01683   0.01066  -0.0453   0.0177   1.0000
   9.500   1.1904   0.01728   0.01115  -0.0444   0.0174   1.0000
   9.750   1.2097   0.01778   0.01170  -0.0432   0.0169   1.0000
  10.000   1.2279   0.01833   0.01230  -0.0417   0.0164   1.0000
  10.250   1.2454   0.01893   0.01296  -0.0402   0.0159   1.0000
  10.500   1.2624   0.01957   0.01365  -0.0387   0.0155   1.0000
  10.750   1.2787   0.02026   0.01439  -0.0371   0.0151   1.0000
  11.000   1.2933   0.02105   0.01523  -0.0353   0.0147   1.0000
  11.250   1.3029   0.02224   0.01649  -0.0328   0.0142   1.0000
  11.500   1.3087   0.02373   0.01810  -0.0299   0.0138   1.0000
  11.750   1.3246   0.02442   0.01886  -0.0284   0.0137   1.0000
  12.000   1.3387   0.02523   0.01975  -0.0268   0.0135   1.0000
  12.250   1.3514   0.02616   0.02076  -0.0251   0.0132   1.0000
  12.500   1.3629   0.02717   0.02185  -0.0233   0.0130   1.0000
  12.750   1.3733   0.02827   0.02305  -0.0214   0.0128   1.0000
  13.000   1.3832   0.02942   0.02428  -0.0196   0.0125   1.0000
  13.250   1.3918   0.03067   0.02562  -0.0177   0.0123   1.0000
  13.500   1.3995   0.03201   0.02706  -0.0159   0.0121   1.0000
  13.750   1.4065   0.03341   0.02855  -0.0141   0.0119   1.0000
  14.000   1.4125   0.03492   0.03015  -0.0123   0.0118   1.0000
  14.250   1.4184   0.03645   0.03176  -0.0107   0.0116   1.0000
  14.500   1.4226   0.03818   0.03356  -0.0092   0.0114   1.0000
  14.750   1.4233   0.04026   0.03573  -0.0076   0.0112   1.0000
  15.000   1.4194   0.04288   0.03846  -0.0059   0.0110   1.0000
  15.250   1.4092   0.04628   0.04200  -0.0042   0.0109   1.0000
  15.500   1.3925   0.05055   0.04645  -0.0027   0.0107   1.0000
  15.750   1.3802   0.05467   0.05074  -0.0020   0.0106   1.0000
  16.000   1.3766   0.05801   0.05420  -0.0022   0.0106   1.0000
  16.250   1.3698   0.06199   0.05832  -0.0028   0.0105   1.0000
  16.500   1.3619   0.06647   0.06295  -0.0040   0.0105   1.0000
  16.750   1.3515   0.07167   0.06829  -0.0059   0.0104   1.0000
  17.000   1.3389   0.07756   0.07434  -0.0085   0.0104   1.0000
  17.250   1.3245   0.08412   0.08105  -0.0118   0.0104   1.0000
  17.500   1.3073   0.09149   0.08858  -0.0157   0.0104   1.0000
  17.750   1.2885   0.09939   0.09663  -0.0201   0.0104   1.0000
  18.000   1.2675   0.10777   0.10515  -0.0247   0.0103   1.0000
  18.250   1.2450   0.11658   0.11410  -0.0296   0.0103   1.0000
  18.500   1.2217   0.12575   0.12340  -0.0348   0.0104   1.0000
  18.750   1.1986   0.13510   0.13289  -0.0402   0.0104   1.0000
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