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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 100,000
Max Cl/Cd: 24.38 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20403-il-100000.txt
Download as CSV file: xf-sc20403-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0403 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6872   0.11935   0.11450   0.0253   1.0000   0.0486
  -9.000  -0.6868   0.11638   0.11159   0.0210   1.0000   0.0491
  -8.750  -0.6863   0.11321   0.10847   0.0165   1.0000   0.0493
  -8.500  -0.6843   0.10957   0.10488   0.0108   1.0000   0.0495
  -8.250  -0.6756   0.10245   0.09764   0.0179   1.0000   0.0516
  -8.000  -0.6695   0.09846   0.09366   0.0182   1.0000   0.0539
  -7.750  -0.6656   0.09460   0.08984   0.0160   1.0000   0.0560
  -7.500  -0.6588   0.09025   0.08552   0.0113   1.0000   0.0584
  -7.250  -0.6472   0.08519   0.08045   0.0018   1.0000   0.0610
  -7.000  -0.6287   0.08083   0.07579  -0.0120   1.0000   0.0625
  -6.750  -0.6239   0.07456   0.06972  -0.0083   1.0000   0.0647
  -6.500  -0.6121   0.07053   0.06569  -0.0086   1.0000   0.0691
  -6.250  -0.5837   0.06651   0.06105  -0.0207   1.0000   0.0759
  -6.000  -0.5763   0.06064   0.05553  -0.0175   1.0000   0.0798
  -5.750  -0.5202   0.04301   0.03818  -0.0200   1.0000   0.0931
  -5.500  -0.5025   0.03792   0.03285  -0.0233   1.0000   0.1045
  -5.250  -0.4848   0.03353   0.02832  -0.0248   1.0000   0.1182
  -5.000  -0.4890   0.04386   0.03802  -0.0277   1.0000   0.1325
  -4.750  -0.4669   0.04045   0.03451  -0.0288   1.0000   0.1608
  -4.250  -0.4227   0.03420   0.02791  -0.0298   1.0000   0.2487
  -4.000  -0.3481   0.02796   0.01965  -0.0327   1.0000   0.0608
  -3.750  -0.3157   0.02423   0.01520  -0.0324   1.0000   0.0439
  -3.500  -0.2850   0.02168   0.01217  -0.0321   1.0000   0.0418
  -3.250  -0.2552   0.02062   0.01064  -0.0316   1.0000   0.0494
  -3.000  -0.2267   0.01836   0.00820  -0.0309   1.0000   0.0494
  -2.750  -0.1997   0.01600   0.00593  -0.0303   1.0000   0.0522
  -2.500  -0.1717   0.01458   0.00450  -0.0299   1.0000   0.0621
  -2.250  -0.1540   0.01029   0.00328  -0.0278   1.0000   0.7423
  -2.000  -0.1533   0.00947   0.00272  -0.0182   1.0000   1.0000
  -1.750  -0.1242   0.00940   0.00227  -0.0188   1.0000   1.0000
  -1.500  -0.0954   0.00935   0.00195  -0.0193   1.0000   1.0000
  -1.250  -0.0669   0.00931   0.00172  -0.0197   1.0000   1.0000
  -1.000  -0.0385   0.00929   0.00151  -0.0201   1.0000   1.0000
  -0.750  -0.0105   0.00929   0.00139  -0.0204   1.0000   1.0000
  -0.500   0.0174   0.00929   0.00133  -0.0206   1.0000   1.0000
  -0.250   0.0451   0.00930   0.00132  -0.0207   1.0000   1.0000
   0.000   0.0726   0.00932   0.00136  -0.0209   1.0000   1.0000
   0.250   0.1000   0.00936   0.00145  -0.0209   1.0000   1.0000
   0.500   0.1274   0.00940   0.00159  -0.0210   1.0000   1.0000
   0.750   0.1546   0.00945   0.00184  -0.0209   1.0000   1.0000
   1.000   0.1817   0.00951   0.00209  -0.0209   1.0000   1.0000
   1.250   0.2088   0.00959   0.00243  -0.0208   1.0000   1.0000
   1.500   0.2360   0.00968   0.00292  -0.0206   1.0000   1.0000
   1.750   0.2956   0.01515   0.00522  -0.0254   0.0564   1.0000
   2.000   0.3219   0.01702   0.00697  -0.0246   0.0497   1.0000
   2.250   0.3504   0.01945   0.00944  -0.0240   0.0486   1.0000
   2.500   0.3799   0.02193   0.01216  -0.0234   0.0489   1.0000
   2.750   0.4099   0.02295   0.01372  -0.0226   0.0420   1.0000
   3.000   0.4395   0.02580   0.01701  -0.0219   0.0456   1.0000
   3.250   0.4727   0.02970   0.02153  -0.0205   0.0731   1.0000
   4.750   0.6386   0.05206   0.04679  -0.0218   0.0937   1.0000
   5.000   0.6522   0.05797   0.05239  -0.0211   0.0883   1.0000
   5.250   0.6764   0.06045   0.05546  -0.0237   0.0772   1.0000
   5.500   0.6953   0.06548   0.06074  -0.0266   0.0719   1.0000
   5.750   0.7134   0.06975   0.06517  -0.0290   0.0656   1.0000
   6.000   0.7201   0.07558   0.07077  -0.0263   0.0622   1.0000
   6.250   0.7375   0.08014   0.07568  -0.0325   0.0606   1.0000
   6.500   0.7547   0.08483   0.08056  -0.0401   0.0568   1.0000
   6.750   0.7651   0.08959   0.08536  -0.0440   0.0541   1.0000
   7.000   0.7731   0.09410   0.08989  -0.0460   0.0517   1.0000
   7.250   0.7741   0.10158   0.09726  -0.0360   0.0488   1.0000
   7.500   0.7820   0.10575   0.10155  -0.0416   0.0486   1.0000
   7.750   0.7884   0.11000   0.10586  -0.0485   0.0484   1.0000
   8.000   0.7903   0.11397   0.10981  -0.0552   0.0481   1.0000
   8.250   0.7903   0.11757   0.11336  -0.0605   0.0476   1.0000
   8.500   0.7908   0.12113   0.11687  -0.0648   0.0468   1.0000
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