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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 200,000
Max Cl/Cd: 35.18 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20404-il-200000.txt
Download as CSV file: xf-sc20404-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6592   0.09901   0.09552   0.0167   1.0000   0.0258
  -8.250  -0.6566   0.09487   0.09142   0.0140   1.0000   0.0265
  -8.000  -0.6541   0.09065   0.08723   0.0108   1.0000   0.0272
  -7.750  -0.6494   0.08595   0.08256   0.0057   1.0000   0.0279
  -7.500  -0.6378   0.07999   0.07659  -0.0036   1.0000   0.0287
  -7.250  -0.6202   0.07411   0.07058  -0.0130   1.0000   0.0296
  -7.000  -0.6025   0.06940   0.06566  -0.0186   1.0000   0.0300
  -6.750  -0.5858   0.06494   0.06097  -0.0220   1.0000   0.0302
  -6.500  -0.5761   0.05696   0.05283  -0.0258   1.0000   0.0310
  -6.250  -0.5643   0.05195   0.04788  -0.0268   1.0000   0.0325
  -6.000  -0.5460   0.04814   0.04395  -0.0284   1.0000   0.0346
  -5.750  -0.5229   0.04405   0.03962  -0.0304   1.0000   0.0377
  -5.500  -0.4870   0.04317   0.03790  -0.0318   1.0000   0.0430
  -5.250  -0.4695   0.03532   0.03011  -0.0343   1.0000   0.0462
  -5.000  -0.4392   0.03265   0.02673  -0.0356   1.0000   0.0571
  -4.750  -0.4149   0.02918   0.02322  -0.0368   1.0000   0.0716
  -4.500  -0.3889   0.02687   0.02081  -0.0376   1.0000   0.0907
  -4.250  -0.3473   0.02100   0.01388  -0.0362   1.0000   0.0384
  -4.000  -0.3155   0.01881   0.01109  -0.0353   1.0000   0.0308
  -3.750  -0.2871   0.01664   0.00870  -0.0350   1.0000   0.0299
  -3.500  -0.2590   0.01475   0.00666  -0.0347   1.0000   0.0306
  -3.250  -0.2312   0.01292   0.00486  -0.0349   1.0000   0.0372
  -3.000  -0.2023   0.01186   0.00374  -0.0351   1.0000   0.0453
  -2.750  -0.1685   0.00927   0.00226  -0.0376   1.0000   0.3085
  -2.500  -0.1479   0.00787   0.00244  -0.0358   1.0000   0.7507
  -2.250  -0.1299   0.00781   0.00250  -0.0326   1.0000   0.8198
  -2.000  -0.1101   0.00773   0.00241  -0.0302   1.0000   0.8527
  -1.750  -0.0948   0.00760   0.00231  -0.0267   1.0000   0.8887
  -1.500  -0.0884   0.00730   0.00209  -0.0209   1.0000   0.9323
  -1.250  -0.0668   0.00696   0.00176  -0.0190   1.0000   0.9881
  -1.000  -0.0366   0.00689   0.00162  -0.0201   1.0000   1.0000
  -0.750  -0.0050   0.00688   0.00153  -0.0215   1.0000   1.0000
  -0.500   0.0261   0.00688   0.00149  -0.0227   1.0000   1.0000
  -0.250   0.0567   0.00690   0.00149  -0.0237   1.0000   1.0000
   0.000   0.0867   0.00694   0.00152  -0.0245   1.0000   1.0000
   0.250   0.1162   0.00698   0.00159  -0.0252   1.0000   1.0000
   0.500   0.1452   0.00703   0.00172  -0.0257   1.0000   1.0000
   0.750   0.1739   0.00709   0.00186  -0.0261   1.0000   1.0000
   1.000   0.2022   0.00717   0.00203  -0.0264   1.0000   1.0000
   1.250   0.2305   0.00725   0.00225  -0.0267   1.0000   1.0000
   1.500   0.2586   0.00735   0.00253  -0.0269   1.0000   1.0000
   1.750   0.3176   0.01109   0.00288  -0.0326   0.0641   1.0000
   2.000   0.3451   0.01236   0.00423  -0.0323   0.0419   1.0000
   2.250   0.3724   0.01368   0.00560  -0.0319   0.0391   1.0000
   2.500   0.4001   0.01463   0.00654  -0.0319   0.0302   1.0000
   2.750   0.4276   0.01742   0.00949  -0.0314   0.0286   1.0000
   3.000   0.4566   0.01906   0.01135  -0.0309   0.0292   1.0000
   3.250   0.4880   0.02164   0.01454  -0.0296   0.0365   1.0000
   3.500   0.5264   0.02728   0.02124  -0.0268   0.0869   1.0000
   3.750   0.5521   0.02982   0.02406  -0.0266   0.0737   1.0000
   4.000   0.5767   0.03284   0.02736  -0.0265   0.0623   1.0000
   4.250   0.6000   0.03532   0.03011  -0.0265   0.0462   1.0000
   4.500   0.6197   0.03934   0.03414  -0.0269   0.0422   1.0000
   4.750   0.6457   0.04343   0.03896  -0.0265   0.0374   1.0000
   5.000   0.6688   0.04738   0.04321  -0.0269   0.0337   1.0000
   5.250   0.6879   0.05123   0.04724  -0.0273   0.0314   1.0000
   5.500   0.7023   0.05534   0.05139  -0.0277   0.0297   1.0000
   5.750   0.7068   0.06424   0.06034  -0.0292   0.0284   1.0000
   6.000   0.7233   0.06865   0.06501  -0.0304   0.0283   1.0000
   6.250   0.7406   0.07292   0.06951  -0.0323   0.0280   1.0000
   6.500   0.7620   0.07750   0.07435  -0.0369   0.0270   1.0000
   6.750   0.7767   0.08293   0.07990  -0.0422   0.0258   1.0000
   7.000   0.7859   0.08832   0.08534  -0.0472   0.0250   1.0000
   7.250   0.7920   0.09360   0.09065  -0.0522   0.0243   1.0000
   7.500   0.7936   0.09853   0.09557  -0.0569   0.0239   1.0000
   7.750   0.7938   0.10313   0.10013  -0.0604   0.0235   1.0000
   8.000   0.7945   0.10759   0.10457  -0.0633   0.0230   1.0000
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