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NASA SC(2)-0403 AIRFOIL (sc20403-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0403 AIRFOIL (sc20403-il)
Reynolds number: 50,000
Max Cl/Cd: 18.02 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20403-il-50000-n5.txt
Download as CSV file: xf-sc20403-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6841   0.11733   0.11043   0.0252   1.0000   0.0749
  -8.750  -0.6885   0.11479   0.10799   0.0200   1.0000   0.0775
  -8.500  -0.6919   0.11187   0.10516   0.0141   1.0000   0.0780
  -8.250  -0.6791   0.10578   0.09908   0.0181   1.0000   0.0805
  -8.000  -0.6732   0.10171   0.09504   0.0175   1.0000   0.0832
  -7.750  -0.6688   0.09771   0.09108   0.0144   1.0000   0.0862
  -7.500  -0.6659   0.09356   0.08694  -0.0004   1.0000   0.0914
  -7.250  -0.6559   0.08838   0.08181   0.0034   1.0000   0.0935
  -7.000  -0.6456   0.08389   0.07732   0.0016   1.0000   0.0960
  -6.750  -0.6338   0.07922   0.07261  -0.0024   1.0000   0.0992
  -6.500  -0.6064   0.07168   0.06480  -0.0090   1.0000   0.0464
  -6.250  -0.5862   0.06612   0.05903  -0.0131   1.0000   0.0351
  -6.000  -0.5677   0.06105   0.05379  -0.0163   1.0000   0.0321
  -5.750  -0.5452   0.05590   0.04835  -0.0199   1.0000   0.0300
  -5.500  -0.5209   0.05115   0.04324  -0.0227   1.0000   0.0293
  -5.250  -0.4969   0.04706   0.03881  -0.0248   1.0000   0.0313
  -5.000  -0.4699   0.04310   0.03440  -0.0268   1.0000   0.0335
  -4.750  -0.4409   0.03933   0.03008  -0.0284   1.0000   0.0351
  -4.500  -0.4112   0.03573   0.02593  -0.0294   1.0000   0.0353
  -4.250  -0.3812   0.03235   0.02200  -0.0300   1.0000   0.0343
  -4.000  -0.3510   0.02933   0.01844  -0.0301   1.0000   0.0337
  -3.750  -0.3217   0.02673   0.01533  -0.0298   1.0000   0.0337
  -3.500  -0.2936   0.02447   0.01226  -0.0288   1.0000   0.0344
  -3.250  -0.2672   0.02258   0.01005  -0.0274   1.0000   0.0368
  -3.000  -0.2420   0.02085   0.00808  -0.0261   1.0000   0.0412
  -2.750  -0.2149   0.01947   0.00657  -0.0260   1.0000   0.0633
  -2.500  -0.1849   0.01731   0.00469  -0.0267   1.0000   0.1242
  -2.000  -0.1588   0.01336   0.00350  -0.0167   1.0000   1.0000
  -1.750  -0.1313   0.01326   0.00296  -0.0170   1.0000   1.0000
  -1.500  -0.1038   0.01319   0.00256  -0.0172   1.0000   1.0000
  -1.250  -0.0765   0.01314   0.00225  -0.0174   1.0000   1.0000
  -1.000  -0.0491   0.01311   0.00194  -0.0175   1.0000   1.0000
  -0.750  -0.0219   0.01309   0.00177  -0.0176   1.0000   1.0000
  -0.500   0.0052   0.01309   0.00167  -0.0177   1.0000   1.0000
  -0.250   0.0322   0.01309   0.00163  -0.0177   1.0000   1.0000
   0.000   0.0591   0.01311   0.00167  -0.0177   1.0000   1.0000
   0.250   0.0860   0.01314   0.00177  -0.0177   1.0000   1.0000
   0.500   0.1127   0.01319   0.00194  -0.0176   1.0000   1.0000
   0.750   0.1395   0.01325   0.00226  -0.0175   1.0000   1.0000
   1.000   0.1661   0.01332   0.00256  -0.0174   1.0000   1.0000
   1.250   0.1926   0.01341   0.00295  -0.0173   1.0000   1.0000
   1.500   0.2191   0.01352   0.00345  -0.0170   1.0000   1.0000
   1.750   0.2458   0.01364   0.00415  -0.0167   1.0000   1.0000
   2.000   0.3064   0.01928   0.00640  -0.0218   0.0647   1.0000
   2.250   0.3342   0.02066   0.00800  -0.0215   0.0427   1.0000
   2.500   0.3635   0.02252   0.01011  -0.0210   0.0364   1.0000
   2.750   0.3932   0.02455   0.01251  -0.0202   0.0339   1.0000
   3.000   0.4230   0.02693   0.01570  -0.0194   0.0330   1.0000
   3.250   0.4524   0.02955   0.01886  -0.0188   0.0332   1.0000
   3.500   0.4814   0.03251   0.02236  -0.0183   0.0338   1.0000
   3.750   0.5094   0.03577   0.02615  -0.0180   0.0348   1.0000
   4.000   0.5366   0.03917   0.03009  -0.0178   0.0347   1.0000
   4.250   0.5629   0.04269   0.03415  -0.0179   0.0333   1.0000
   4.500   0.5876   0.04637   0.03828  -0.0184   0.0310   1.0000
   4.750   0.6097   0.05015   0.04240  -0.0190   0.0287   1.0000
   5.000   0.6322   0.05448   0.04711  -0.0200   0.0288   1.0000
   5.250   0.6548   0.05937   0.05237  -0.0217   0.0310   1.0000
   5.500   0.6741   0.06435   0.05759  -0.0236   0.0340   1.0000
   5.750   0.6949   0.06971   0.06322  -0.0258   0.0454   1.0000
   6.250   0.7376   0.08173   0.07569  -0.0331   0.0953   1.0000
   6.750   0.7592   0.09247   0.08634  -0.0323   0.0908   1.0000
   7.000   0.7647   0.09599   0.09007  -0.0438   0.0840   1.0000
   7.250   0.7720   0.10052   0.09460  -0.0459   0.0810   1.0000
   7.500   0.7817   0.10605   0.10011  -0.0418   0.0782   1.0000
   7.750   0.7854   0.11078   0.10481  -0.0468   0.0773   1.0000
   8.000   0.7812   0.11403   0.10799  -0.0553   0.0755   1.0000
   8.250   0.7809   0.11779   0.11170  -0.0591   0.0727   1.0000
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