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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 100,000
Max Cl/Cd: 45.06 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7003-il-100000-n5.txt
Download as CSV file: xf-sd7003-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7003-085-88                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5632   0.08759   0.08257  -0.0102   1.0000   0.0259
  -9.000  -0.5701   0.08168   0.07673  -0.0137   1.0000   0.0259
  -8.750  -0.5801   0.07514   0.07027  -0.0181   1.0000   0.0257
  -8.500  -0.6456   0.05301   0.04777  -0.0356   1.0000   0.0222
  -8.000  -0.6367   0.04607   0.04048  -0.0375   1.0000   0.0237
  -7.750  -0.6275   0.04268   0.03682  -0.0380   1.0000   0.0246
  -7.500  -0.6185   0.03829   0.03194  -0.0383   1.0000   0.0254
  -7.250  -0.6057   0.03415   0.02724  -0.0381   1.0000   0.0262
  -7.000  -0.5892   0.03056   0.02304  -0.0375   1.0000   0.0275
  -6.750  -0.5697   0.02765   0.01957  -0.0368   1.0000   0.0293
  -6.500  -0.5483   0.02655   0.01846  -0.0364   1.0000   0.0321
  -6.250  -0.5259   0.02497   0.01656  -0.0357   1.0000   0.0358
  -6.000  -0.5035   0.02326   0.01463  -0.0349   1.0000   0.0393
  -5.750  -0.4805   0.02236   0.01364  -0.0343   1.0000   0.0444
  -5.500  -0.4573   0.02103   0.01208  -0.0334   1.0000   0.0495
  -5.250  -0.4341   0.02019   0.01122  -0.0327   1.0000   0.0560
  -5.000  -0.4108   0.01912   0.01003  -0.0319   1.0000   0.0620
  -4.750  -0.3874   0.01839   0.00925  -0.0311   1.0000   0.0704
  -4.500  -0.3642   0.01757   0.00842  -0.0304   1.0000   0.0783
  -4.250  -0.3408   0.01689   0.00770  -0.0296   1.0000   0.0888
  -4.000  -0.3172   0.01630   0.00709  -0.0288   1.0000   0.1009
  -3.750  -0.2938   0.01571   0.00653  -0.0281   1.0000   0.1148
  -3.500  -0.2705   0.01514   0.00604  -0.0274   1.0000   0.1330
  -3.250  -0.2471   0.01463   0.00561  -0.0267   1.0000   0.1573
  -3.000  -0.2241   0.01410   0.00527  -0.0261   1.0000   0.1934
  -2.750  -0.2011   0.01362   0.00500  -0.0254   1.0000   0.2442
  -2.500  -0.1785   0.01315   0.00479  -0.0247   1.0000   0.3079
  -2.250  -0.1565   0.01270   0.00467  -0.0239   1.0000   0.3865
  -2.000  -0.1220   0.01221   0.00462  -0.0255   0.9906   0.4989
  -1.750  -0.0862   0.01180   0.00466  -0.0268   0.9775   0.6197
  -1.500  -0.0520   0.01155   0.00469  -0.0274   0.9631   0.7208
  -1.250  -0.0188   0.01137   0.00468  -0.0275   0.9475   0.7990
  -1.000   0.0160   0.01123   0.00462  -0.0278   0.9309   0.8647
  -0.750   0.0601   0.01110   0.00447  -0.0302   0.9145   0.9225
  -0.500   0.1137   0.01097   0.00425  -0.0348   0.8962   0.9687
  -0.250   0.1630   0.01087   0.00401  -0.0389   0.8721   1.0000
   0.000   0.1949   0.01087   0.00386  -0.0394   0.8433   1.0000
   0.250   0.2236   0.01091   0.00375  -0.0392   0.8134   1.0000
   0.500   0.2503   0.01099   0.00366  -0.0386   0.7832   1.0000
   0.750   0.2764   0.01110   0.00361  -0.0379   0.7531   1.0000
   1.000   0.3022   0.01124   0.00359  -0.0371   0.7231   1.0000
   1.250   0.3278   0.01140   0.00360  -0.0364   0.6931   1.0000
   1.500   0.3533   0.01157   0.00363  -0.0356   0.6635   1.0000
   1.750   0.3787   0.01177   0.00368  -0.0349   0.6340   1.0000
   2.000   0.4041   0.01198   0.00375  -0.0341   0.6048   1.0000
   2.250   0.4294   0.01221   0.00386  -0.0334   0.5760   1.0000
   2.500   0.4548   0.01246   0.00397  -0.0328   0.5474   1.0000
   2.750   0.4802   0.01272   0.00412  -0.0321   0.5192   1.0000
   3.000   0.5056   0.01300   0.00430  -0.0315   0.4917   1.0000
   3.250   0.5310   0.01330   0.00449  -0.0309   0.4644   1.0000
   3.500   0.5563   0.01361   0.00470  -0.0304   0.4376   1.0000
   3.750   0.5817   0.01394   0.00496  -0.0298   0.4108   1.0000
   4.000   0.6070   0.01428   0.00523  -0.0293   0.3850   1.0000
   4.250   0.6322   0.01465   0.00553  -0.0288   0.3599   1.0000
   4.500   0.6573   0.01505   0.00585  -0.0283   0.3360   1.0000
   4.750   0.6825   0.01545   0.00623  -0.0278   0.3119   1.0000
   5.000   0.7073   0.01590   0.00662  -0.0273   0.2900   1.0000
   5.250   0.7323   0.01635   0.00705  -0.0269   0.2682   1.0000
   5.500   0.7569   0.01685   0.00750  -0.0264   0.2484   1.0000
   5.750   0.7816   0.01735   0.00803  -0.0259   0.2288   1.0000
   6.000   0.8061   0.01789   0.00857  -0.0254   0.2106   1.0000
   6.250   0.8302   0.01847   0.00914  -0.0249   0.1935   1.0000
   6.500   0.8540   0.01908   0.00976  -0.0244   0.1778   1.0000
   6.750   0.8776   0.01973   0.01045  -0.0239   0.1629   1.0000
   7.000   0.9010   0.02042   0.01116  -0.0233   0.1490   1.0000
   7.250   0.9242   0.02113   0.01193  -0.0227   0.1357   1.0000
   7.500   0.9471   0.02188   0.01276  -0.0221   0.1232   1.0000
   7.750   0.9696   0.02269   0.01367  -0.0215   0.1114   1.0000
   8.000   0.9915   0.02355   0.01461  -0.0209   0.0999   1.0000
   8.250   1.0127   0.02447   0.01561  -0.0202   0.0891   1.0000
   8.500   1.0330   0.02548   0.01667  -0.0194   0.0792   1.0000
   8.750   1.0523   0.02655   0.01778  -0.0187   0.0699   1.0000
   9.000   1.0722   0.02764   0.01909  -0.0179   0.0614   1.0000
   9.250   1.0895   0.02900   0.02054  -0.0169   0.0549   1.0000
   9.500   1.1063   0.03034   0.02202  -0.0159   0.0494   1.0000
   9.750   1.1211   0.03195   0.02374  -0.0147   0.0450   1.0000
  10.000   1.1357   0.03349   0.02548  -0.0136   0.0409   1.0000
  10.250   1.1475   0.03522   0.02730  -0.0123   0.0384   1.0000
  10.500   1.1576   0.03734   0.02958  -0.0109   0.0365   1.0000
  10.750   1.1670   0.03951   0.03208  -0.0095   0.0347   1.0000
  11.000   1.1736   0.04166   0.03446  -0.0081   0.0329   1.0000
  11.250   1.1763   0.04369   0.03665  -0.0064   0.0315   1.0000
  11.500   1.1763   0.04578   0.03885  -0.0048   0.0304   1.0000
  11.750   1.1741   0.04829   0.04146  -0.0038   0.0295   1.0000
  12.000   1.1681   0.05155   0.04489  -0.0033   0.0288   1.0000
  12.250   1.1598   0.05532   0.04895  -0.0036   0.0284   1.0000
  12.500   1.1486   0.05978   0.05368  -0.0050   0.0281   1.0000
  12.750   1.1348   0.06503   0.05918  -0.0075   0.0279   1.0000
  13.000   1.1184   0.07117   0.06556  -0.0110   0.0278   1.0000
  13.250   1.0989   0.07845   0.07306  -0.0158   0.0278   1.0000
  13.500   1.0773   0.08667   0.08148  -0.0214   0.0280   1.0000
  13.750   1.0521   0.09632   0.09129  -0.0279   0.0282   1.0000
  14.000   1.0235   0.10738   0.10249  -0.0353   0.0285   1.0000
  14.250   0.9919   0.11999   0.11519  -0.0432   0.0289   1.0000
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