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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 100,000
Max Cl/Cd: 25.99 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20404-il-100000-n5.txt
Download as CSV file: xf-sc20404-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0404 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6673   0.11671   0.11170   0.0232   1.0000   0.0301
  -9.250  -0.6644   0.11267   0.10769   0.0212   1.0000   0.0303
  -9.000  -0.6615   0.10859   0.10364   0.0191   1.0000   0.0304
  -8.000  -0.5547   0.07829   0.07369   0.0001   1.0000   0.0189
  -7.500  -0.6373   0.08004   0.07526  -0.0027   1.0000   0.0193
  -7.250  -0.6287   0.07467   0.06985  -0.0075   1.0000   0.0184
  -7.000  -0.6175   0.06914   0.06424  -0.0123   1.0000   0.0176
  -6.750  -0.6036   0.06353   0.05852  -0.0169   1.0000   0.0168
  -6.500  -0.5870   0.05794   0.05274  -0.0210   1.0000   0.0161
  -6.250  -0.5676   0.05242   0.04696  -0.0244   1.0000   0.0154
  -6.000  -0.5455   0.04712   0.04134  -0.0273   1.0000   0.0151
  -5.750  -0.5210   0.04253   0.03637  -0.0294   1.0000   0.0167
  -5.500  -0.4933   0.03823   0.03156  -0.0310   1.0000   0.0192
  -5.250  -0.4646   0.03432   0.02708  -0.0321   1.0000   0.0204
  -5.000  -0.4358   0.03012   0.02213  -0.0330   1.0000   0.0204
  -4.750  -0.4063   0.02672   0.01814  -0.0335   1.0000   0.0206
  -4.500  -0.3772   0.02395   0.01484  -0.0336   1.0000   0.0210
  -4.250  -0.3487   0.02153   0.01203  -0.0334   1.0000   0.0217
  -4.000  -0.3217   0.01892   0.00921  -0.0333   1.0000   0.0239
  -3.750  -0.2947   0.01802   0.00815  -0.0332   1.0000   0.0325
  -3.500  -0.2677   0.01639   0.00642  -0.0329   1.0000   0.0349
  -3.250  -0.2400   0.01519   0.00512  -0.0330   1.0000   0.0400
  -3.000  -0.2116   0.01423   0.00404  -0.0331   1.0000   0.0534
  -2.750  -0.1834   0.01206   0.00317  -0.0345   1.0000   0.3216
  -2.500  -0.1674   0.01078   0.00326  -0.0313   1.0000   0.7184
  -2.250  -0.1526   0.01061   0.00325  -0.0272   1.0000   0.8070
  -2.000  -0.1425   0.01039   0.00310  -0.0220   1.0000   0.8718
  -1.750  -0.1290   0.01005   0.00277  -0.0179   1.0000   0.9231
  -1.500  -0.1008   0.00980   0.00241  -0.0178   1.0000   0.9594
  -1.250  -0.0703   0.00961   0.00212  -0.0186   1.0000   1.0000
  -1.000  -0.0412   0.00958   0.00198  -0.0194   1.0000   1.0000
  -0.750  -0.0122   0.00957   0.00186  -0.0201   1.0000   1.0000
  -0.500   0.0166   0.00958   0.00180  -0.0207   1.0000   1.0000
  -0.250   0.0451   0.00960   0.00179  -0.0212   1.0000   1.0000
   0.000   0.0734   0.00963   0.00183  -0.0216   1.0000   1.0000
   0.250   0.1014   0.00967   0.00191  -0.0219   1.0000   1.0000
   0.500   0.1292   0.00973   0.00206  -0.0222   1.0000   1.0000
   0.750   0.1569   0.00980   0.00222  -0.0224   1.0000   1.0000
   1.000   0.1844   0.00988   0.00243  -0.0226   1.0000   1.0000
   1.250   0.2117   0.00998   0.00270  -0.0227   1.0000   1.0000
   1.500   0.2390   0.01009   0.00303  -0.0227   1.0000   1.0000
   1.750   0.3111   0.01197   0.00311  -0.0297   0.3471   1.0000
   2.000   0.3346   0.01418   0.00402  -0.0297   0.0547   1.0000
   2.250   0.3620   0.01514   0.00507  -0.0294   0.0396   1.0000
   2.500   0.3887   0.01622   0.00627  -0.0291   0.0344   1.0000
   2.750   0.4148   0.01784   0.00798  -0.0286   0.0321   1.0000
   3.000   0.4426   0.01944   0.00979  -0.0281   0.0295   1.0000
   3.250   0.4699   0.02067   0.01117  -0.0280   0.0221   1.0000
   3.750   0.5252   0.02645   0.01777  -0.0270   0.0201   1.0000
   4.000   0.5525   0.02950   0.02139  -0.0264   0.0198   1.0000
   4.250   0.5787   0.03310   0.02557  -0.0258   0.0196   1.0000
   4.500   0.6031   0.03736   0.03053  -0.0253   0.0197   1.0000
   4.750   0.6289   0.04103   0.03473  -0.0249   0.0185   1.0000
   5.000   0.6535   0.04528   0.03946  -0.0248   0.0163   1.0000
   5.250   0.6754   0.04978   0.04433  -0.0254   0.0148   1.0000
   5.500   0.6952   0.05480   0.04966  -0.0263   0.0149   1.0000
   5.750   0.7132   0.06007   0.05519  -0.0278   0.0155   1.0000
   6.000   0.7290   0.06541   0.06074  -0.0298   0.0162   1.0000
   6.250   0.7424   0.07078   0.06627  -0.0323   0.0171   1.0000
   6.500   0.7531   0.07610   0.07170  -0.0349   0.0180   1.0000
   6.750   0.7574   0.08121   0.07684  -0.0360   0.0195   1.0000
   7.250   0.7793   0.09324   0.08907  -0.0478   0.0263   1.0000
   7.750   0.7823   0.10305   0.09883  -0.0557   0.0278   1.0000
   8.000   0.7832   0.10765   0.10340  -0.0587   0.0281   1.0000
   8.250   0.7844   0.11214   0.10785  -0.0613   0.0283   1.0000
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