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NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il)
Reynolds number: 50,000
Max Cl/Cd: 19.06 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20404-il-50000-n5.txt
Download as CSV file: xf-sc20404-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6728   0.11786   0.11099   0.0208   1.0000   0.0951
  -9.000  -0.6823   0.11545   0.10871   0.0149   1.0000   0.0984
  -8.750  -0.6763   0.11044   0.10375   0.0145   1.0000   0.1001
  -8.500  -0.6668   0.10595   0.09926   0.0153   1.0000   0.1032
  -8.250  -0.6641   0.10208   0.09544   0.0135   1.0000   0.1067
  -8.000  -0.6736   0.09832   0.09181   0.0011   1.0000   0.1122
  -7.750  -0.6610   0.09352   0.08702   0.0058   1.0000   0.1149
  -7.500  -0.5630   0.07388   0.06760  -0.0070   1.0000   0.0543
  -7.000  -0.6220   0.07418   0.06742  -0.0119   1.0000   0.0525
  -6.750  -0.6062   0.06810   0.06112  -0.0169   1.0000   0.0436
  -6.500  -0.5915   0.06290   0.05576  -0.0199   1.0000   0.0410
  -6.250  -0.5732   0.05740   0.04999  -0.0233   1.0000   0.0386
  -6.000  -0.5504   0.05172   0.04382  -0.0268   1.0000   0.0361
  -5.500  -0.4970   0.04305   0.03385  -0.0303   1.0000   0.0337
  -5.250  -0.4708   0.03893   0.02920  -0.0314   1.0000   0.0336
  -4.750  -0.4176   0.03162   0.02090  -0.0330   1.0000   0.0380
  -4.500  -0.3888   0.02936   0.01805  -0.0331   1.0000   0.0451
  -4.250  -0.3601   0.02692   0.01509  -0.0325   1.0000   0.0468
  -4.000  -0.3347   0.02442   0.01246  -0.0315   1.0000   0.0497
  -3.750  -0.3095   0.02267   0.01051  -0.0302   1.0000   0.0540
  -3.500  -0.2843   0.02124   0.00876  -0.0290   1.0000   0.0599
  -3.250  -0.2578   0.01985   0.00734  -0.0291   1.0000   0.0823
  -3.000  -0.2290   0.01785   0.00568  -0.0298   1.0000   0.1456
  -2.750  -0.2256   0.01502   0.00571  -0.0236   1.0000   0.7426
  -2.500  -0.2266   0.01450   0.00545  -0.0139   1.0000   0.8982
  -2.250  -0.1813   0.01391   0.00425  -0.0161   1.0000   1.0000
  -2.000  -0.1566   0.01376   0.00374  -0.0162   1.0000   1.0000
  -1.750  -0.1305   0.01364   0.00332  -0.0165   1.0000   1.0000
  -1.500  -0.1037   0.01355   0.00299  -0.0169   1.0000   1.0000
  -1.250  -0.0766   0.01349   0.00273  -0.0172   1.0000   1.0000
  -1.000  -0.0494   0.01345   0.00254  -0.0176   1.0000   1.0000
  -0.750  -0.0221   0.01343   0.00236  -0.0178   1.0000   1.0000
  -0.500   0.0051   0.01343   0.00227  -0.0181   1.0000   1.0000
  -0.250   0.0322   0.01345   0.00225  -0.0183   1.0000   1.0000
   0.000   0.0592   0.01347   0.00228  -0.0184   1.0000   1.0000
   0.250   0.0861   0.01352   0.00236  -0.0185   1.0000   1.0000
   0.500   0.1129   0.01358   0.00251  -0.0186   1.0000   1.0000
   0.750   0.1396   0.01365   0.00275  -0.0186   1.0000   1.0000
   1.000   0.1661   0.01374   0.00299  -0.0186   1.0000   1.0000
   1.250   0.1927   0.01384   0.00331  -0.0186   1.0000   1.0000
   1.500   0.2191   0.01397   0.00371  -0.0185   1.0000   1.0000
   1.750   0.2456   0.01411   0.00419  -0.0185   1.0000   1.0000
   2.000   0.2720   0.01427   0.00478  -0.0183   1.0000   1.0000
   2.250   0.3439   0.01845   0.00617  -0.0248   0.1169   1.0000
   2.500   0.3707   0.02010   0.00769  -0.0245   0.0759   1.0000
   2.750   0.3980   0.02151   0.00917  -0.0243   0.0571   1.0000
   3.000   0.4277   0.02313   0.01114  -0.0239   0.0514   1.0000
   3.250   0.4566   0.02515   0.01339  -0.0233   0.0476   1.0000
   3.500   0.4853   0.02792   0.01638  -0.0228   0.0453   1.0000
   3.750   0.5148   0.03063   0.01966  -0.0221   0.0442   1.0000
   4.000   0.5435   0.03321   0.02293  -0.0216   0.0391   1.0000
   4.250   0.5668   0.03616   0.02607  -0.0218   0.0332   1.0000
   4.750   0.6155   0.04417   0.03538  -0.0214   0.0329   1.0000
   5.000   0.6397   0.04787   0.03962  -0.0212   0.0335   1.0000
   5.250   0.6642   0.05260   0.04510  -0.0216   0.0356   1.0000
   5.500   0.6847   0.05786   0.05082  -0.0227   0.0378   1.0000
   5.750   0.7023   0.06309   0.05636  -0.0242   0.0403   1.0000
   6.000   0.7170   0.06819   0.06165  -0.0255   0.0429   1.0000
   7.000   0.7798   0.09323   0.08742  -0.0374   0.1120   1.0000
   7.250   0.7786   0.09790   0.09213  -0.0452   0.1056   1.0000
   7.500   0.7831   0.10246   0.09669  -0.0481   0.1020   1.0000
   7.750   0.7924   0.10729   0.10151  -0.0469   0.0989   1.0000
   8.000   0.7966   0.11263   0.10680  -0.0483   0.0973   1.0000
   8.250   0.7854   0.11589   0.10996  -0.0569   0.0943   1.0000
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