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NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-206 (naca63206-il)
Reynolds number: 100,000
Max Cl/Cd: 41.48 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63206-il-100000-n5.txt
Download as CSV file: xf-naca63206-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5597   0.08871   0.08401  -0.0080   1.0000   0.0354
  -7.750  -0.5586   0.08484   0.08019  -0.0103   1.0000   0.0358
  -7.500  -0.5560   0.08036   0.07576  -0.0142   1.0000   0.0363
  -7.250  -0.5507   0.07559   0.07099  -0.0188   1.0000   0.0365
  -7.000  -0.5439   0.07080   0.06616  -0.0228   1.0000   0.0370
  -6.750  -0.5350   0.06589   0.06117  -0.0266   1.0000   0.0369
  -6.500  -0.5235   0.06033   0.05542  -0.0307   1.0000   0.0354
  -6.000  -0.4851   0.04969   0.04412  -0.0340   1.0000   0.0193
  -5.750  -0.4697   0.04500   0.03907  -0.0351   1.0000   0.0188
  -5.500  -0.4512   0.04074   0.03447  -0.0359   1.0000   0.0185
  -5.250  -0.4303   0.03676   0.03010  -0.0364   1.0000   0.0183
  -5.000  -0.4077   0.03314   0.02602  -0.0365   1.0000   0.0183
  -4.750  -0.3820   0.03093   0.02327  -0.0360   1.0000   0.0197
  -4.500  -0.3602   0.02698   0.01892  -0.0364   1.0000   0.0222
  -4.250  -0.3353   0.02454   0.01610  -0.0360   1.0000   0.0234
  -4.000  -0.3097   0.02228   0.01345  -0.0353   1.0000   0.0244
  -3.750  -0.2843   0.02033   0.01121  -0.0344   1.0000   0.0259
  -3.500  -0.2594   0.01894   0.00959  -0.0335   1.0000   0.0299
  -3.250  -0.2353   0.01757   0.00807  -0.0326   1.0000   0.0339
  -3.000  -0.2121   0.01619   0.00660  -0.0318   1.0000   0.0366
  -2.750  -0.1882   0.01526   0.00557  -0.0311   1.0000   0.0407
  -2.500  -0.1638   0.01448   0.00463  -0.0305   1.0000   0.0476
  -2.250  -0.1394   0.01371   0.00394  -0.0301   1.0000   0.0749
  -2.000  -0.1190   0.01120   0.00345  -0.0299   1.0000   0.5408
  -1.750  -0.1124   0.01053   0.00371  -0.0240   1.0000   0.7934
  -1.500  -0.0876   0.01013   0.00356  -0.0210   1.0000   0.9782
  -1.250  -0.0606   0.01007   0.00322  -0.0216   1.0000   1.0000
  -1.000  -0.0375   0.01010   0.00305  -0.0214   1.0000   1.0000
  -0.750  -0.0141   0.01016   0.00295  -0.0212   1.0000   1.0000
  -0.500   0.0205   0.01026   0.00291  -0.0232   0.9934   1.0000
  -0.250   0.0599   0.01037   0.00288  -0.0261   0.9839   1.0000
   0.000   0.0990   0.01047   0.00290  -0.0288   0.9746   1.0000
   0.250   0.1387   0.01057   0.00295  -0.0316   0.9657   1.0000
   0.500   0.1772   0.01065   0.00302  -0.0341   0.9558   1.0000
   0.750   0.2139   0.01073   0.00313  -0.0361   0.9447   1.0000
   1.000   0.2501   0.01081   0.00324  -0.0380   0.9332   1.0000
   1.250   0.2853   0.01088   0.00338  -0.0396   0.9211   1.0000
   1.500   0.3192   0.01096   0.00355  -0.0408   0.9082   1.0000
   1.750   0.3519   0.01105   0.00380  -0.0417   0.8944   1.0000
   2.000   0.3835   0.01113   0.00402  -0.0423   0.8793   1.0000
   2.250   0.4142   0.01121   0.00424  -0.0425   0.8621   1.0000
   2.500   0.4421   0.01128   0.00447  -0.0420   0.8389   1.0000
   2.750   0.4629   0.01116   0.00418  -0.0383   0.7544   1.0000
   3.000   0.4792   0.01163   0.00398  -0.0341   0.5725   1.0000
   3.250   0.4893   0.01427   0.00444  -0.0315   0.1434   1.0000
   3.500   0.5114   0.01573   0.00543  -0.0308   0.0564   1.0000
   3.750   0.5357   0.01672   0.00652  -0.0302   0.0460   1.0000
   4.000   0.5597   0.01773   0.00771  -0.0294   0.0413   1.0000
   4.250   0.5815   0.01929   0.00928  -0.0285   0.0366   1.0000
   4.500   0.6067   0.02026   0.01046  -0.0279   0.0307   1.0000
   4.750   0.6313   0.02196   0.01237  -0.0270   0.0280   1.0000
   5.000   0.6565   0.02410   0.01465  -0.0263   0.0260   1.0000
   5.250   0.6812   0.02718   0.01801  -0.0256   0.0237   1.0000
   5.500   0.7071   0.02896   0.02032  -0.0247   0.0204   1.0000
   5.750   0.7310   0.03211   0.02401  -0.0236   0.0195   1.0000
   6.000   0.7527   0.03567   0.02814  -0.0224   0.0191   1.0000
   6.250   0.7719   0.03963   0.03264  -0.0213   0.0189   1.0000
   6.500   0.7886   0.04394   0.03747  -0.0203   0.0190   1.0000
   6.750   0.8025   0.04847   0.04245  -0.0195   0.0190   1.0000
   7.000   0.8139   0.05298   0.04736  -0.0190   0.0184   1.0000
   7.250   0.8227   0.05743   0.05214  -0.0188   0.0175   1.0000
   7.500   0.8284   0.06194   0.05692  -0.0190   0.0167   1.0000
   7.750   0.8310   0.06646   0.06165  -0.0195   0.0161   1.0000
   8.000   0.8293   0.07144   0.06682  -0.0206   0.0161   1.0000
   8.250   0.8231   0.07688   0.07240  -0.0225   0.0165   1.0000
   8.500   0.8120   0.08231   0.07789  -0.0250   0.0174   1.0000
   8.750   0.8020   0.08865   0.08424  -0.0302   0.0183   1.0000
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