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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 100,000
Max Cl/Cd: 43.33 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7003-il-100000.txt
Download as CSV file: xf-sd7003-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5197   0.10154   0.09654  -0.0015   1.0000   0.1091
  -8.750  -0.5400   0.09832   0.09345  -0.0081   1.0000   0.1140
  -8.500  -0.5614   0.09446   0.08974  -0.0151   1.0000   0.1146
  -8.250  -0.5197   0.09015   0.08532  -0.0066   1.0000   0.1200
  -8.000  -0.5203   0.08668   0.08191  -0.0082   1.0000   0.1246
  -7.750  -0.5630   0.08141   0.07669  -0.0244   1.0000   0.1289
  -7.500  -0.5350   0.07783   0.07322  -0.0159   1.0000   0.1319
  -7.250  -0.5256   0.07454   0.06994  -0.0157   1.0000   0.1366
  -7.000  -0.5374   0.06830   0.06363  -0.0250   1.0000   0.1449
  -6.750  -0.5468   0.04834   0.04275  -0.0368   1.0000   0.0757
  -6.500  -0.5340   0.04258   0.03661  -0.0372   1.0000   0.0687
  -6.250  -0.5205   0.03708   0.03054  -0.0374   1.0000   0.0665
  -6.000  -0.5023   0.03347   0.02639  -0.0369   1.0000   0.0693
  -5.750  -0.4820   0.02998   0.02221  -0.0362   1.0000   0.0716
  -5.500  -0.4605   0.02681   0.01852  -0.0354   1.0000   0.0751
  -5.250  -0.4378   0.02525   0.01689  -0.0347   1.0000   0.0827
  -5.000  -0.4141   0.02305   0.01431  -0.0338   1.0000   0.0895
  -4.750  -0.3900   0.02176   0.01282  -0.0329   1.0000   0.0994
  -4.500  -0.3664   0.02028   0.01131  -0.0321   1.0000   0.1105
  -4.250  -0.3424   0.01896   0.00997  -0.0312   1.0000   0.1229
  -4.000  -0.3185   0.01793   0.00893  -0.0304   1.0000   0.1390
  -3.750  -0.2946   0.01700   0.00796  -0.0295   1.0000   0.1576
  -3.500  -0.2716   0.01599   0.00717  -0.0286   1.0000   0.1798
  -3.250  -0.2486   0.01512   0.00649  -0.0277   1.0000   0.2134
  -3.000  -0.2263   0.01412   0.00589  -0.0268   1.0000   0.2693
  -2.750  -0.2053   0.01298   0.00547  -0.0258   1.0000   0.3866
  -2.500  -0.1869   0.01207   0.00534  -0.0238   1.0000   0.5476
  -2.250  -0.1718   0.01163   0.00543  -0.0204   1.0000   0.6850
  -2.000  -0.1590   0.01144   0.00552  -0.0163   1.0000   0.7865
  -1.750  -0.1456   0.01133   0.00557  -0.0121   1.0000   0.8773
  -1.500  -0.0785   0.01120   0.00531  -0.0187   1.0000   1.0000
  -1.250  -0.0657   0.01122   0.00517  -0.0173   1.0000   1.0000
  -1.000  -0.0485   0.01134   0.00514  -0.0165   1.0000   1.0000
  -0.750  -0.0307   0.01155   0.00521  -0.0159   1.0000   1.0000
  -0.500  -0.0037   0.01186   0.00539  -0.0170   0.9966   1.0000
  -0.250   0.0572   0.01217   0.00558  -0.0241   0.9801   1.0000
   0.000   0.1155   0.01231   0.00564  -0.0303   0.9620   1.0000
   0.250   0.1754   0.01229   0.00557  -0.0364   0.9447   1.0000
   0.500   0.2321   0.01215   0.00541  -0.0416   0.9263   1.0000
   0.750   0.2775   0.01200   0.00524  -0.0443   0.9017   1.0000
   1.000   0.3164   0.01189   0.00508  -0.0456   0.8741   1.0000
   1.250   0.3480   0.01185   0.00497  -0.0453   0.8439   1.0000
   1.500   0.3750   0.01190   0.00492  -0.0441   0.8122   1.0000
   1.750   0.3999   0.01201   0.00491  -0.0426   0.7803   1.0000
   2.000   0.4240   0.01218   0.00495  -0.0410   0.7481   1.0000
   2.250   0.4478   0.01239   0.00503  -0.0396   0.7147   1.0000
   2.500   0.4718   0.01263   0.00513  -0.0382   0.6818   1.0000
   2.750   0.4959   0.01289   0.00524  -0.0369   0.6494   1.0000
   3.000   0.5202   0.01318   0.00540  -0.0357   0.6173   1.0000
   3.250   0.5446   0.01350   0.00557  -0.0346   0.5853   1.0000
   3.500   0.5690   0.01384   0.00579  -0.0336   0.5524   1.0000
   3.750   0.5935   0.01420   0.00603  -0.0326   0.5201   1.0000
   4.000   0.6180   0.01460   0.00633  -0.0317   0.4887   1.0000
   4.250   0.6425   0.01503   0.00663  -0.0308   0.4578   1.0000
   4.500   0.6669   0.01550   0.00698  -0.0300   0.4277   1.0000
   4.750   0.6914   0.01599   0.00737  -0.0292   0.3984   1.0000
   5.000   0.7158   0.01652   0.00783  -0.0285   0.3701   1.0000
   5.250   0.7401   0.01710   0.00832  -0.0278   0.3430   1.0000
   5.500   0.7644   0.01772   0.00885  -0.0271   0.3177   1.0000
   5.750   0.7886   0.01838   0.00943  -0.0264   0.2935   1.0000
   6.000   0.8127   0.01907   0.01013  -0.0258   0.2700   1.0000
   6.250   0.8367   0.01984   0.01077  -0.0251   0.2493   1.0000
   6.500   0.8605   0.02063   0.01163  -0.0244   0.2284   1.0000
   6.750   0.8842   0.02147   0.01247  -0.0238   0.2096   1.0000
   7.000   0.9078   0.02241   0.01333  -0.0232   0.1925   1.0000
   7.250   0.9311   0.02344   0.01437  -0.0225   0.1761   1.0000
   7.500   0.9539   0.02450   0.01553  -0.0218   0.1603   1.0000
   7.750   0.9761   0.02560   0.01672  -0.0210   0.1451   1.0000
   8.000   0.9978   0.02676   0.01798  -0.0202   0.1306   1.0000
   8.250   1.0187   0.02802   0.01933  -0.0193   0.1170   1.0000
   8.500   1.0391   0.02943   0.02080  -0.0185   0.1044   1.0000
   8.750   1.0589   0.03101   0.02241  -0.0176   0.0934   1.0000
   9.000   1.0786   0.03268   0.02421  -0.0166   0.0842   1.0000
   9.250   1.0953   0.03505   0.02699  -0.0154   0.0766   1.0000
   9.500   1.1144   0.03736   0.02918  -0.0148   0.0704   1.0000
   9.750   1.1253   0.04051   0.03299  -0.0131   0.0672   1.0000
  10.000   1.1349   0.04371   0.03665  -0.0116   0.0641   1.0000
  10.250   1.1479   0.04599   0.03908  -0.0106   0.0607   1.0000
  10.500   1.1546   0.05001   0.04321  -0.0098   0.0581   1.0000
  10.750   1.1483   0.05390   0.04766  -0.0079   0.0574   1.0000
  11.000   1.1363   0.05826   0.05245  -0.0063   0.0571   1.0000
  11.250   1.1180   0.06251   0.05701  -0.0048   0.0571   1.0000
  11.500   1.0958   0.06684   0.06156  -0.0040   0.0572   1.0000
  11.750   1.0727   0.07197   0.06687  -0.0053   0.0575   1.0000
  12.000   1.0484   0.07822   0.07326  -0.0085   0.0579   1.0000
  12.250   1.0257   0.08552   0.08067  -0.0128   0.0584   1.0000
  12.500   0.8646   0.13346   0.12860  -0.0485   0.0843   1.0000
  12.750   0.8815   0.13549   0.13070  -0.0461   0.0827   1.0000
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