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CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il)
Reynolds number: 50,000
Max Cl/Cd: 32.79 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cast102-il-50000.txt
Download as CSV file: xf-cast102-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4661   0.13352   0.12608  -0.0250   1.0000   0.2428
 -11.000  -0.4809   0.13236   0.12501  -0.0258   1.0000   0.2545
 -10.750  -0.4715   0.12879   0.12146  -0.0248   1.0000   0.2695
 -10.500  -0.4650   0.12552   0.11823  -0.0239   1.0000   0.2846
 -10.250  -0.4627   0.12267   0.11543  -0.0229   1.0000   0.3002
 -10.000  -0.4664   0.12037   0.11320  -0.0219   1.0000   0.3162
  -9.750  -0.4401   0.11575   0.10854  -0.0201   1.0000   0.3366
  -9.500  -0.4350   0.11327   0.10611  -0.0184   1.0000   0.3587
  -9.250  -0.4353   0.11087   0.10378  -0.0165   1.0000   0.3801
  -9.000  -0.4287   0.10865   0.10160  -0.0142   1.0000   0.4064
  -8.750  -0.4108   0.10540   0.09837  -0.0122   1.0000   0.4336
  -8.500  -0.4008   0.10299   0.09600  -0.0098   1.0000   0.4641
  -8.250  -0.3922   0.10076   0.09378  -0.0073   1.0000   0.4952
  -8.000  -0.3777   0.09787   0.09093  -0.0055   1.0000   0.5237
  -7.750  -0.3694   0.09519   0.08829  -0.0036   1.0000   0.5472
  -7.500  -0.3606   0.09246   0.08559  -0.0021   1.0000   0.5664
  -7.250  -0.3588   0.08992   0.08311  -0.0003   1.0000   0.5792
  -6.500  -0.4524   0.08197   0.07559   0.0047   1.0000   0.4892
  -6.250  -0.5250   0.07862   0.07253   0.0075   1.0000   0.4424
  -6.000  -0.5954   0.07305   0.06718   0.0062   1.0000   0.4054
  -5.750  -0.6504   0.05894   0.05259  -0.0109   1.0000   0.3086
  -5.500  -0.6224   0.05106   0.04279  -0.0204   1.0000   0.1911
  -5.250  -0.5960   0.04742   0.03838  -0.0201   1.0000   0.1598
  -5.000  -0.5718   0.04465   0.03496  -0.0194   1.0000   0.1452
  -4.750  -0.5487   0.04169   0.03172  -0.0187   1.0000   0.1392
  -4.500  -0.5223   0.03997   0.02922  -0.0177   1.0000   0.1305
  -4.250  -0.4969   0.03745   0.02653  -0.0170   1.0000   0.1261
  -4.000  -0.4698   0.03552   0.02422  -0.0162   1.0000   0.1217
  -3.750  -0.4425   0.03405   0.02231  -0.0153   1.0000   0.1187
  -3.500  -0.4160   0.03262   0.02073  -0.0144   1.0000   0.1190
  -3.250  -0.3903   0.03137   0.01949  -0.0133   1.0000   0.1226
  -3.000  -0.3650   0.03041   0.01847  -0.0119   1.0000   0.1260
  -2.750  -0.3407   0.02961   0.01757  -0.0103   1.0000   0.1289
  -2.500  -0.3177   0.02876   0.01667  -0.0090   1.0000   0.1332
  -2.250  -0.2952   0.02785   0.01577  -0.0081   1.0000   0.1432
  -2.000  -0.0786   0.02927   0.01967  -0.0212   1.0000   1.0000
  -1.750  -0.0735   0.02896   0.01920  -0.0186   1.0000   1.0000
  -1.500  -0.0687   0.02865   0.01876  -0.0159   1.0000   1.0000
  -1.250  -0.0644   0.02834   0.01834  -0.0131   1.0000   1.0000
  -1.000  -0.0606   0.02801   0.01792  -0.0103   1.0000   1.0000
  -0.750  -0.0573   0.02768   0.01751  -0.0074   1.0000   1.0000
  -0.500  -0.0547   0.02734   0.01708  -0.0045   1.0000   1.0000
  -0.250  -0.0527   0.02698   0.01666  -0.0014   1.0000   1.0000
   0.000  -0.0512   0.02660   0.01623   0.0017   1.0000   1.0000
   0.250  -0.0498   0.02621   0.01580   0.0049   1.0000   1.0000
   0.500  -0.0478   0.02583   0.01537   0.0078   1.0000   1.0000
   0.750  -0.0403   0.02559   0.01507   0.0098   1.0000   1.0000
   1.000  -0.0258   0.02556   0.01496   0.0105   1.0000   1.0000
   1.250  -0.0067   0.02570   0.01502   0.0104   1.0000   1.0000
   1.500   0.0148   0.02597   0.01521   0.0099   1.0000   1.0000
   1.750   0.0376   0.02633   0.01552   0.0092   1.0000   1.0000
   2.000   0.0609   0.02678   0.01591   0.0084   1.0000   1.0000
   2.250   0.0842   0.02729   0.01640   0.0076   1.0000   1.0000
   2.500   0.1072   0.02788   0.01696   0.0068   1.0000   1.0000
   2.750   0.1298   0.02852   0.01762   0.0061   1.0000   1.0000
   3.000   0.1519   0.02924   0.01835   0.0054   1.0000   1.0000
   3.250   0.1732   0.03003   0.01918   0.0047   1.0000   1.0000
   3.500   0.1938   0.03092   0.02013   0.0040   1.0000   1.0000
   3.750   0.2134   0.03191   0.02120   0.0033   1.0000   1.0000
   4.000   0.2715   0.03376   0.02322  -0.0048   0.9802   1.0000
   4.250   0.3546   0.03536   0.02508  -0.0161   0.9388   1.0000
   4.500   0.4347   0.03587   0.02589  -0.0252   0.8989   1.0000
   4.750   0.4962   0.03529   0.02565  -0.0298   0.8576   1.0000
   5.000   0.5605   0.03365   0.02439  -0.0332   0.8151   1.0000
   5.250   0.6245   0.03064   0.02184  -0.0346   0.7668   1.0000
   5.500   0.6778   0.02661   0.01819  -0.0325   0.6981   1.0000
   5.750   0.7666   0.02338   0.01396  -0.0345   0.5165   1.0000
   6.000   0.7984   0.02505   0.01490  -0.0345   0.4398   1.0000
   6.250   0.8322   0.02666   0.01623  -0.0354   0.3917   1.0000
   6.500   0.8646   0.02824   0.01763  -0.0361   0.3569   1.0000
   6.750   0.8947   0.02989   0.01928  -0.0365   0.3300   1.0000
   7.000   0.9235   0.03161   0.02091  -0.0367   0.3058   1.0000
   7.250   0.9454   0.03330   0.02281  -0.0357   0.2834   1.0000
   7.500   0.9658   0.03483   0.02427  -0.0346   0.2578   1.0000
   7.750   0.9831   0.03609   0.02535  -0.0331   0.2296   1.0000
   8.000   0.9970   0.03768   0.02714  -0.0309   0.2038   1.0000
   8.250   1.0139   0.04008   0.02964  -0.0292   0.1808   1.0000
   8.500   1.0290   0.04253   0.03228  -0.0273   0.1619   1.0000
   8.750   1.0434   0.04546   0.03548  -0.0254   0.1493   1.0000
   9.000   1.0625   0.04853   0.03858  -0.0244   0.1402   1.0000
   9.250   1.0632   0.05200   0.04274  -0.0209   0.1347   1.0000
   9.500   1.0859   0.05479   0.04535  -0.0207   0.1268   1.0000
   9.750   1.0802   0.05881   0.05002  -0.0169   0.1254   1.0000
  10.000   1.0724   0.06313   0.05483  -0.0135   0.1247   1.0000
  10.250   1.0598   0.06759   0.05969  -0.0101   0.1245   1.0000
  10.500   1.0435   0.07211   0.06453  -0.0069   0.1247   1.0000
  10.750   1.0242   0.07660   0.06925  -0.0039   0.1252   1.0000
  11.000   1.0038   0.08115   0.07396  -0.0014   0.1258   1.0000
  11.250   0.9855   0.08616   0.07909   0.0001   0.1264   1.0000
  11.500   0.7530   0.13612   0.12895  -0.0407   0.3058   1.0000
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