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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 200,000
Max Cl/Cd: 32.54 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20403-il-200000.txt
Download as CSV file: xf-sc20403-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6892   0.12317   0.11962   0.0334   1.0000   0.0201
  -9.500  -0.6853   0.11933   0.11580   0.0317   1.0000   0.0207
  -9.250  -0.6815   0.11551   0.11200   0.0297   1.0000   0.0212
  -9.000  -0.6775   0.11173   0.10824   0.0276   1.0000   0.0217
  -8.750  -0.6735   0.10802   0.10455   0.0251   1.0000   0.0223
  -8.500  -0.6694   0.10436   0.10092   0.0222   1.0000   0.0227
  -8.250  -0.6651   0.10070   0.09729   0.0187   1.0000   0.0230
  -8.000  -0.6606   0.09691   0.09346   0.0148   1.0000   0.0233
  -7.750  -0.6514   0.09242   0.08899   0.0086   1.0000   0.0234
  -7.500  -0.6382   0.08733   0.08387   0.0012   1.0000   0.0236
  -7.250  -0.6240   0.08244   0.07892  -0.0044   1.0000   0.0237
  -7.000  -0.6090   0.07766   0.07404  -0.0091   1.0000   0.0238
  -6.750  -0.5930   0.07298   0.06924  -0.0130   1.0000   0.0239
  -6.500  -0.5819   0.06599   0.06216  -0.0168   1.0000   0.0243
  -6.250  -0.5751   0.05973   0.05592  -0.0183   1.0000   0.0256
  -6.000  -0.5600   0.05554   0.05168  -0.0199   1.0000   0.0271
  -5.750  -0.5395   0.05126   0.04725  -0.0224   1.0000   0.0289
  -5.500  -0.5152   0.04693   0.04269  -0.0250   1.0000   0.0314
  -5.250  -0.4808   0.04416   0.03940  -0.0272   1.0000   0.0359
  -5.000  -0.4547   0.03871   0.03352  -0.0297   1.0000   0.0378
  -4.750  -0.4331   0.03453   0.02935  -0.0310   1.0000   0.0408
  -4.500  -0.3982   0.03505   0.02910  -0.0310   1.0000   0.0496
  -4.250  -0.3757   0.02825   0.02240  -0.0333   1.0000   0.0549
  -4.000  -0.3456   0.02555   0.01911  -0.0342   1.0000   0.0661
  -3.750  -0.3168   0.02311   0.01644  -0.0350   1.0000   0.0806
  -3.500  -0.2774   0.01976   0.01227  -0.0320   1.0000   0.0232
  -3.250  -0.2475   0.01657   0.00873  -0.0320   1.0000   0.0201
  -3.000  -0.2185   0.01457   0.00648  -0.0316   1.0000   0.0189
  -2.750  -0.1898   0.01296   0.00476  -0.0313   1.0000   0.0199
  -2.500  -0.1614   0.01187   0.00367  -0.0315   1.0000   0.0310
  -2.250  -0.1309   0.01067   0.00238  -0.0319   1.0000   0.0423
  -2.000  -0.1189   0.00726   0.00209  -0.0282   1.0000   0.8534
  -1.750  -0.1134   0.00692   0.00185  -0.0219   1.0000   0.9329
  -1.500  -0.0878   0.00666   0.00149  -0.0211   1.0000   1.0000
  -1.250  -0.0577   0.00663   0.00132  -0.0219   1.0000   1.0000
  -1.000  -0.0282   0.00662   0.00117  -0.0226   1.0000   1.0000
  -0.750   0.0008   0.00662   0.00109  -0.0231   1.0000   1.0000
  -0.500   0.0295   0.00663   0.00105  -0.0235   1.0000   1.0000
  -0.250   0.0579   0.00665   0.00105  -0.0238   1.0000   1.0000
   0.000   0.0860   0.00667   0.00109  -0.0240   1.0000   1.0000
   0.250   0.1139   0.00670   0.00117  -0.0242   1.0000   1.0000
   0.500   0.1417   0.00674   0.00129  -0.0243   1.0000   1.0000
   0.750   0.1694   0.00678   0.00148  -0.0243   1.0000   1.0000
   1.000   0.1970   0.00684   0.00169  -0.0243   1.0000   1.0000
   1.250   0.2245   0.00690   0.00199  -0.0243   1.0000   1.0000
   1.500   0.2776   0.01181   0.00361  -0.0291   0.0319   1.0000
   1.750   0.3044   0.01314   0.00492  -0.0288   0.0220   1.0000
   2.000   0.3325   0.01434   0.00621  -0.0284   0.0184   1.0000
   2.250   0.3611   0.01624   0.00832  -0.0277   0.0188   1.0000
   2.500   0.3901   0.01872   0.01111  -0.0270   0.0210   1.0000
   3.000   0.4566   0.02504   0.01856  -0.0236   0.0667   1.0000
   3.250   0.4834   0.02759   0.02144  -0.0234   0.0551   1.0000
   3.500   0.5078   0.03082   0.02493  -0.0235   0.0504   1.0000
   3.750   0.5361   0.03341   0.02814  -0.0231   0.0416   1.0000
   4.000   0.5586   0.03670   0.03155  -0.0233   0.0378   1.0000
   4.250   0.5754   0.04403   0.03900  -0.0243   0.0357   1.0000
   4.500   0.6102   0.04464   0.04029  -0.0237   0.0318   1.0000
   4.750   0.6346   0.04862   0.04455  -0.0245   0.0291   1.0000
   5.000   0.6560   0.05272   0.04884  -0.0255   0.0270   1.0000
   5.250   0.6735   0.05683   0.05308  -0.0265   0.0253   1.0000
   5.500   0.6843   0.06185   0.05810  -0.0270   0.0240   1.0000
   5.750   0.6911   0.07035   0.06668  -0.0293   0.0231   1.0000
   6.000   0.7083   0.07489   0.07140  -0.0313   0.0230   1.0000
   6.250   0.7250   0.07947   0.07613  -0.0339   0.0229   1.0000
   6.500   0.7412   0.08405   0.08084  -0.0372   0.0227   1.0000
   6.750   0.7569   0.08876   0.08565  -0.0420   0.0225   1.0000
   7.000   0.7710   0.09357   0.09053  -0.0480   0.0221   1.0000
   7.250   0.7814   0.09840   0.09538  -0.0543   0.0217   1.0000
   7.500   0.7858   0.10285   0.09981  -0.0593   0.0214   1.0000
   7.750   0.7881   0.10705   0.10407  -0.0629   0.0210   1.0000
   8.000   0.7906   0.11118   0.10817  -0.0658   0.0206   1.0000
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