Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il)
Reynolds number: 1,000,000
Max Cl/Cd: 62.64 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0011sc-il-1000000-n5.txt
Download as CSV file: xf-n0011sc-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA/LANGLEY SYMMETRICAL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -1.0182   0.11970   0.11704  -0.0312   1.0000   0.0139
 -19.000  -1.0692   0.10654   0.10373  -0.0382   1.0000   0.0139
 -18.750  -1.1276   0.09239   0.08938  -0.0457   1.0000   0.0139
 -18.500  -1.1825   0.07895   0.07574  -0.0531   1.0000   0.0138
 -18.250  -1.2232   0.06811   0.06469  -0.0594   1.0000   0.0137
 -18.000  -1.2483   0.06041   0.05682  -0.0638   1.0000   0.0138
 -17.750  -1.2680   0.05430   0.05055  -0.0667   1.0000   0.0138
 -17.500  -1.2825   0.04957   0.04568  -0.0683   1.0000   0.0138
 -17.250  -1.2956   0.04550   0.04147  -0.0690   1.0000   0.0138
 -17.000  -1.3030   0.04247   0.03833  -0.0687   1.0000   0.0139
 -16.750  -1.3115   0.03964   0.03537  -0.0678   1.0000   0.0139
 -16.500  -1.3142   0.03756   0.03319  -0.0664   1.0000   0.0140
 -16.250  -1.3155   0.03575   0.03128  -0.0647   1.0000   0.0141
 -16.000  -1.3183   0.03397   0.02940  -0.0626   1.0000   0.0142
 -15.750  -1.3177   0.03257   0.02791  -0.0603   1.0000   0.0142
 -15.500  -1.3199   0.03107   0.02631  -0.0575   1.0000   0.0142
 -15.250  -1.3180   0.02992   0.02507  -0.0548   1.0000   0.0143
 -15.000  -1.3186   0.02871   0.02377  -0.0516   1.0000   0.0143
 -14.750  -1.3183   0.02762   0.02260  -0.0482   1.0000   0.0143
 -14.500  -1.3206   0.02646   0.02135  -0.0443   1.0000   0.0146
 -14.250  -1.3180   0.02561   0.02043  -0.0408   1.0000   0.0146
 -14.000  -1.3060   0.02465   0.01941  -0.0392   0.9995   0.0148
 -13.750  -1.2915   0.02381   0.01848  -0.0379   0.9987   0.0150
 -13.500  -1.2758   0.02305   0.01765  -0.0366   0.9979   0.0150
 -13.250  -1.2588   0.02233   0.01688  -0.0355   0.9970   0.0152
 -13.000  -1.2397   0.02171   0.01620  -0.0347   0.9960   0.0154
 -12.750  -1.2199   0.02113   0.01556  -0.0339   0.9951   0.0156
 -12.500  -1.2000   0.02055   0.01493  -0.0331   0.9944   0.0158
 -12.250  -1.1832   0.01999   0.01430  -0.0316   0.9932   0.0159
 -12.000  -1.1663   0.01946   0.01371  -0.0300   0.9919   0.0160
 -11.750  -1.1470   0.01896   0.01316  -0.0288   0.9905   0.0163
 -11.500  -1.1257   0.01850   0.01266  -0.0280   0.9892   0.0165
 -11.250  -1.1045   0.01803   0.01213  -0.0272   0.9881   0.0166
 -11.000  -1.0823   0.01758   0.01162  -0.0265   0.9871   0.0168
 -10.750  -1.0589   0.01717   0.01117  -0.0260   0.9863   0.0170
 -10.500  -1.0349   0.01675   0.01070  -0.0257   0.9855   0.0173
 -10.250  -1.0103   0.01627   0.01020  -0.0255   0.9849   0.0178
 -10.000  -0.9887   0.01589   0.00979  -0.0245   0.9836   0.0181
  -9.750  -0.9742   0.01557   0.00945  -0.0219   0.9807   0.0184
  -9.500  -0.9529   0.01522   0.00907  -0.0208   0.9791   0.0186
  -9.250  -0.9290   0.01488   0.00871  -0.0202   0.9778   0.0191
  -9.000  -0.9036   0.01454   0.00834  -0.0200   0.9767   0.0196
  -8.750  -0.8772   0.01421   0.00799  -0.0199   0.9758   0.0200
  -8.500  -0.8505   0.01392   0.00766  -0.0199   0.9751   0.0204
  -8.250  -0.8238   0.01355   0.00728  -0.0199   0.9745   0.0210
  -8.000  -0.7960   0.01322   0.00696  -0.0201   0.9739   0.0217
  -7.750  -0.7674   0.01293   0.00666  -0.0205   0.9734   0.0225
  -7.500  -0.7564   0.01273   0.00645  -0.0169   0.9692   0.0229
  -7.250  -0.7327   0.01250   0.00619  -0.0161   0.9673   0.0237
  -7.000  -0.7068   0.01222   0.00591  -0.0158   0.9660   0.0246
  -6.750  -0.6799   0.01195   0.00565  -0.0158   0.9649   0.0257
  -6.500  -0.6523   0.01170   0.00541  -0.0158   0.9640   0.0272
  -6.250  -0.6238   0.01146   0.00517  -0.0161   0.9632   0.0283
  -6.000  -0.5950   0.01119   0.00492  -0.0164   0.9625   0.0300
  -5.750  -0.5657   0.01096   0.00470  -0.0168   0.9619   0.0317
  -5.500  -0.5362   0.01072   0.00447  -0.0173   0.9614   0.0336
  -5.250  -0.5062   0.01048   0.00426  -0.0178   0.9609   0.0363
  -5.000  -0.4977   0.01040   0.00417  -0.0135   0.9549   0.0377
  -4.750  -0.4714   0.01017   0.00398  -0.0132   0.9532   0.0412
  -4.500  -0.4436   0.00996   0.00379  -0.0132   0.9520   0.0452
  -4.250  -0.4146   0.00974   0.00361  -0.0135   0.9509   0.0500
  -4.000  -0.3850   0.00950   0.00342  -0.0139   0.9500   0.0566
  -3.750  -0.3544   0.00927   0.00324  -0.0146   0.9491   0.0643
  -3.500  -0.3231   0.00903   0.00307  -0.0154   0.9483   0.0748
  -3.250  -0.2908   0.00880   0.00291  -0.0164   0.9475   0.0858
  -3.000  -0.2814   0.00869   0.00283  -0.0122   0.9410   0.0948
  -2.750  -0.2538   0.00846   0.00269  -0.0121   0.9385   0.1104
  -2.500  -0.2234   0.00822   0.00254  -0.0127   0.9365   0.1305
  -2.250  -0.1911   0.00793   0.00238  -0.0137   0.9347   0.1588
  -2.000  -0.1555   0.00762   0.00223  -0.0156   0.9333   0.1956
  -1.750  -0.1448   0.00742   0.00213  -0.0116   0.9243   0.2249
  -1.500  -0.1017   0.00693   0.00188  -0.0151   0.9160   0.2892
  -1.250  -0.0713   0.00653   0.00168  -0.0157   0.8988   0.3526
  -1.000  -0.0424   0.00610   0.00151  -0.0160   0.8806   0.4354
  -0.750  -0.0180   0.00568   0.00135  -0.0153   0.8561   0.5281
  -0.500  -0.0030   0.00540   0.00123  -0.0124   0.8236   0.6043
  -0.250   0.0026   0.00525   0.00116  -0.0072   0.7824   0.6696
   0.000  -0.0014   0.00521   0.00114   0.0003   0.7265   0.7322
   0.250  -0.0007   0.00523   0.00116   0.0067   0.6751   0.7804
   0.500   0.0046   0.00536   0.00123   0.0120   0.6120   0.8256
   0.750   0.0204   0.00564   0.00135   0.0148   0.5359   0.8582
   1.000   0.0426   0.00608   0.00151   0.0160   0.4388   0.8801
   1.250   0.0714   0.00652   0.00168   0.0157   0.3551   0.8994
   1.500   0.1012   0.00695   0.00189   0.0152   0.2860   0.9161
   1.750   0.1447   0.00743   0.00213   0.0116   0.2226   0.9243
   2.000   0.1548   0.00764   0.00223   0.0157   0.1918   0.9333
   2.250   0.1910   0.00794   0.00238   0.0137   0.1566   0.9347
   2.500   0.2234   0.00821   0.00254   0.0127   0.1309   0.9365
   2.750   0.2538   0.00847   0.00269   0.0121   0.1099   0.9385
   3.000   0.2815   0.00869   0.00283   0.0121   0.0950   0.9410
   3.250   0.2910   0.00880   0.00291   0.0164   0.0862   0.9475
   3.500   0.3231   0.00904   0.00307   0.0154   0.0731   0.9483
   3.750   0.3544   0.00927   0.00324   0.0146   0.0632   0.9491
   4.000   0.3850   0.00951   0.00342   0.0139   0.0555   0.9500
   4.250   0.4146   0.00974   0.00361   0.0135   0.0490   0.9509
   4.500   0.4435   0.00997   0.00379   0.0132   0.0444   0.9520
   4.750   0.4714   0.01018   0.00398   0.0132   0.0405   0.9533
   5.000   0.4977   0.01040   0.00417   0.0135   0.0376   0.9550
   5.250   0.5063   0.01048   0.00426   0.0178   0.0361   0.9609
   5.500   0.5362   0.01073   0.00447   0.0173   0.0335   0.9614
   5.750   0.5658   0.01096   0.00470   0.0168   0.0316   0.9619
   6.000   0.5951   0.01120   0.00492   0.0164   0.0299   0.9625
   6.250   0.6239   0.01147   0.00517   0.0161   0.0282   0.9632
   6.500   0.6524   0.01170   0.00541   0.0158   0.0269   0.9640
   6.750   0.6799   0.01195   0.00565   0.0157   0.0255   0.9649
   7.000   0.7067   0.01223   0.00592   0.0158   0.0244   0.9660
   7.250   0.7328   0.01249   0.00619   0.0161   0.0235   0.9674
   7.500   0.7565   0.01273   0.00645   0.0169   0.0228   0.9692
   7.750   0.7678   0.01292   0.00666   0.0204   0.0224   0.9735
   8.000   0.7963   0.01323   0.00696   0.0201   0.0214   0.9739
   8.250   0.8240   0.01355   0.00729   0.0199   0.0208   0.9745
   8.500   0.8508   0.01391   0.00765   0.0198   0.0203   0.9751
   8.750   0.8775   0.01422   0.00799   0.0198   0.0198   0.9758
   9.000   0.9038   0.01454   0.00834   0.0199   0.0194   0.9767
   9.250   0.9293   0.01488   0.00871   0.0201   0.0190   0.9778
   9.500   0.9532   0.01523   0.00908   0.0207   0.0186   0.9791
   9.750   0.9746   0.01556   0.00944   0.0218   0.0182   0.9808
  10.000   0.9887   0.01589   0.00979   0.0245   0.0179   0.9837
  10.250   1.0105   0.01629   0.01021   0.0254   0.0175   0.9849
  10.500   1.0349   0.01680   0.01076   0.0256   0.0172   0.9856
  10.750   1.0594   0.01719   0.01119   0.0259   0.0170   0.9863
  11.000   1.0828   0.01760   0.01164   0.0264   0.0168   0.9871
  11.250   1.1049   0.01805   0.01215   0.0271   0.0166   0.9881
  11.500   1.1264   0.01850   0.01266   0.0278   0.0164   0.9893
  11.750   1.1473   0.01900   0.01320   0.0287   0.0162   0.9906
  12.000   1.1662   0.01951   0.01377   0.0300   0.0161   0.9920
  12.250   1.1830   0.02006   0.01438   0.0316   0.0160   0.9934
  12.500   1.2012   0.02053   0.01489   0.0329   0.0156   0.9944
  12.750   1.2206   0.02114   0.01558   0.0338   0.0156   0.9951
  13.000   1.2408   0.02170   0.01618   0.0345   0.0154   0.9960
  13.250   1.2594   0.02237   0.01692   0.0353   0.0152   0.9970
  13.500   1.2763   0.02308   0.01769   0.0365   0.0151   0.9980
  13.750   1.2924   0.02382   0.01850   0.0377   0.0149   0.9988
  14.000   1.3069   0.02468   0.01942   0.0390   0.0147   0.9995
  14.250   1.3190   0.02557   0.02039   0.0406   0.0147   1.0000
  14.500   1.3192   0.02654   0.02143   0.0444   0.0145   1.0000
  14.750   1.3207   0.02750   0.02247   0.0479   0.0145   1.0000
  15.000   1.3202   0.02863   0.02369   0.0514   0.0144   1.0000
  15.250   1.3172   0.02998   0.02513   0.0548   0.0143   1.0000
  15.500   1.3194   0.03113   0.02637   0.0575   0.0142   1.0000
  15.750   1.3190   0.03250   0.02784   0.0602   0.0142   1.0000
  16.000   1.3171   0.03409   0.02952   0.0626   0.0142   1.0000
  16.250   1.3154   0.03580   0.03134   0.0647   0.0141   1.0000
  16.500   1.3112   0.03785   0.03349   0.0665   0.0141   1.0000
  16.750   1.3049   0.04029   0.03604   0.0678   0.0141   1.0000
  17.000   1.2994   0.04290   0.03877   0.0686   0.0140   1.0000
  17.250   1.2908   0.04612   0.04210   0.0687   0.0140   1.0000
  17.500   1.2808   0.04988   0.04600   0.0680   0.0139   1.0000
  17.750   1.2650   0.05487   0.05113   0.0663   0.0139   1.0000
  18.000   1.2429   0.06143   0.05786   0.0630   0.0139   1.0000
  18.250   1.2189   0.06904   0.06564   0.0586   0.0138   1.0000
  18.500   1.1743   0.08065   0.07747   0.0519   0.0139   1.0000
  18.750   1.1230   0.09342   0.09042   0.0449   0.0140   1.0000
<< Back to NACA/LANGLEY SYMMETRICAL (n0011sc-il)

Polar data table (+)

Polar graphs


<< Back to NACA/LANGLEY SYMMETRICAL (n0011sc-il)