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=500,000 Ncrit=5


Details Polar file
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il)
Reynolds number: 500,000
Max Cl/Cd: 50.39 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0011sc-il-500000-n5.txt
Download as CSV file: xf-n0011sc-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.9413   0.10763   0.10426  -0.0367   1.0000   0.0172
 -17.250  -1.0002   0.09207   0.08847  -0.0455   1.0000   0.0171
 -17.000  -1.0382   0.08101   0.07721  -0.0520   1.0000   0.0171
 -16.750  -1.0675   0.07194   0.06795  -0.0574   1.0000   0.0171
 -16.500  -1.0904   0.06451   0.06034  -0.0617   1.0000   0.0171
 -16.250  -1.1090   0.05846   0.05409  -0.0647   1.0000   0.0172
 -16.000  -1.1243   0.05357   0.04903  -0.0665   1.0000   0.0172
 -15.750  -1.1379   0.04945   0.04477  -0.0671   1.0000   0.0173
 -15.500  -1.1482   0.04612   0.04130  -0.0668   1.0000   0.0172
 -15.250  -1.1590   0.04309   0.03816  -0.0658   1.0000   0.0174
 -15.000  -1.1663   0.04063   0.03557  -0.0642   1.0000   0.0174
 -14.750  -1.1719   0.03852   0.03334  -0.0621   1.0000   0.0175
 -14.500  -1.1754   0.03678   0.03151  -0.0598   1.0000   0.0176
 -14.250  -1.1792   0.03508   0.02969  -0.0569   1.0000   0.0176
 -14.000  -1.1791   0.03382   0.02836  -0.0541   1.0000   0.0179
 -13.750  -1.1795   0.03257   0.02702  -0.0510   1.0000   0.0180
 -13.500  -1.1801   0.03134   0.02568  -0.0476   1.0000   0.0180
 -13.250  -1.1787   0.03035   0.02461  -0.0442   1.0000   0.0182
 -13.000  -1.1765   0.02944   0.02361  -0.0407   1.0000   0.0183
 -12.750  -1.1739   0.02860   0.02269  -0.0371   1.0000   0.0185
 -12.500  -1.1716   0.02777   0.02177  -0.0333   1.0000   0.0186
 -12.250  -1.1689   0.02701   0.02092  -0.0293   1.0000   0.0188
 -12.000  -1.1663   0.02627   0.02009  -0.0252   1.0000   0.0189
 -11.750  -1.1633   0.02562   0.01936  -0.0211   1.0000   0.0191
 -11.500  -1.1578   0.02500   0.01865  -0.0173   0.9998   0.0193
 -11.250  -1.1390   0.02423   0.01777  -0.0163   0.9986   0.0195
 -11.000  -1.1205   0.02353   0.01698  -0.0152   0.9972   0.0198
 -10.750  -1.1006   0.02295   0.01629  -0.0142   0.9958   0.0202
 -10.500  -1.0804   0.02231   0.01556  -0.0133   0.9946   0.0205
 -10.250  -1.0623   0.02161   0.01483  -0.0120   0.9930   0.0209
 -10.000  -1.0422   0.02100   0.01417  -0.0109   0.9912   0.0212
  -9.750  -1.0209   0.02047   0.01359  -0.0100   0.9897   0.0216
  -9.500  -0.9989   0.01993   0.01300  -0.0093   0.9882   0.0219
  -9.250  -0.9754   0.01943   0.01245  -0.0088   0.9869   0.0224
  -9.000  -0.9505   0.01893   0.01190  -0.0086   0.9858   0.0229
  -8.750  -0.9242   0.01846   0.01136  -0.0087   0.9849   0.0235
  -8.500  -0.9029   0.01804   0.01088  -0.0076   0.9831   0.0240
  -8.250  -0.8844   0.01754   0.01035  -0.0059   0.9808   0.0245
  -8.000  -0.8616   0.01711   0.00992  -0.0051   0.9789   0.0252
  -7.750  -0.8364   0.01673   0.00951  -0.0048   0.9773   0.0259
  -7.500  -0.8105   0.01636   0.00911  -0.0047   0.9760   0.0267
  -7.250  -0.7837   0.01604   0.00875  -0.0047   0.9749   0.0279
  -7.000  -0.7566   0.01564   0.00835  -0.0048   0.9740   0.0290
  -6.750  -0.7304   0.01532   0.00802  -0.0046   0.9727   0.0303
  -6.500  -0.7142   0.01504   0.00772  -0.0022   0.9691   0.0313
  -6.250  -0.6903   0.01476   0.00742  -0.0015   0.9669   0.0327
  -6.000  -0.6644   0.01442   0.00709  -0.0012   0.9652   0.0343
  -5.750  -0.6369   0.01415   0.00682  -0.0013   0.9638   0.0363
  -5.500  -0.6086   0.01387   0.00654  -0.0015   0.9627   0.0384
  -5.250  -0.5794   0.01359   0.00628  -0.0019   0.9617   0.0416
  -5.000  -0.5495   0.01333   0.00604  -0.0025   0.9609   0.0449
  -4.750  -0.5370   0.01314   0.00586   0.0008   0.9558   0.0481
  -4.500  -0.5120   0.01291   0.00565   0.0014   0.9534   0.0521
  -4.250  -0.4845   0.01267   0.00544   0.0014   0.9516   0.0579
  -4.000  -0.4558   0.01241   0.00524   0.0011   0.9502   0.0657
  -3.750  -0.4260   0.01215   0.00503   0.0007   0.9490   0.0750
  -3.500  -0.3956   0.01189   0.00484   0.0000   0.9480   0.0871
  -3.250  -0.3767   0.01170   0.00471   0.0020   0.9440   0.0989
  -2.750  -0.3280   0.01118   0.00439   0.0035   0.9377   0.1370
  -2.500  -0.2992   0.01085   0.00421   0.0032   0.9360   0.1688
  -2.250  -0.2693   0.01050   0.00402   0.0027   0.9346   0.2067
  -2.000  -0.2392   0.01005   0.00382   0.0021   0.9334   0.2623
  -1.750  -0.2284   0.00978   0.00374   0.0058   0.9263   0.3101
  -1.500  -0.2063   0.00923   0.00354   0.0070   0.9228   0.3939
  -1.250  -0.1846   0.00854   0.00329   0.0083   0.9202   0.5031
  -1.000  -0.1640   0.00782   0.00303   0.0099   0.9180   0.6154
  -0.750  -0.1644   0.00741   0.00295   0.0165   0.9076   0.6940
  -0.500  -0.1231   0.00671   0.00272   0.0142   0.9024   0.8013
  -0.250  -0.0682   0.00659   0.00279   0.0087   0.8891   0.8558
   0.000   0.0007   0.00662   0.00287  -0.0001   0.8776   0.8781
   0.250   0.0664   0.00659   0.00279  -0.0083   0.8564   0.8889
   0.500   0.1225   0.00671   0.00273  -0.0140   0.8051   0.9024
   0.750   0.1653   0.00738   0.00295  -0.0167   0.7005   0.9075
   1.000   0.1647   0.00781   0.00304  -0.0101   0.6168   0.9180
   1.250   0.1845   0.00855   0.00329  -0.0082   0.5013   0.9202
   1.500   0.2062   0.00924   0.00354  -0.0070   0.3925   0.9228
   1.750   0.2282   0.00979   0.00374  -0.0058   0.3079   0.9263
   2.000   0.2390   0.01008   0.00383  -0.0020   0.2573   0.9334
   2.250   0.2692   0.01050   0.00402  -0.0027   0.2061   0.9346
   2.500   0.2988   0.01089   0.00421  -0.0031   0.1629   0.9360
   2.750   0.3280   0.01118   0.00439  -0.0035   0.1366   0.9377
   3.250   0.3766   0.01170   0.00470  -0.0020   0.0989   0.9440
   3.500   0.3957   0.01189   0.00484  -0.0001   0.0872   0.9480
   3.750   0.4261   0.01215   0.00503  -0.0007   0.0754   0.9490
   4.000   0.4558   0.01241   0.00523  -0.0012   0.0652   0.9502
   4.250   0.4846   0.01267   0.00544  -0.0015   0.0578   0.9516
   4.500   0.5120   0.01291   0.00564  -0.0014   0.0520   0.9534
   4.750   0.5369   0.01315   0.00586  -0.0008   0.0475   0.9559
   5.000   0.5495   0.01333   0.00604   0.0025   0.0447   0.9609
   5.250   0.5795   0.01359   0.00628   0.0019   0.0413   0.9617
   5.500   0.6087   0.01387   0.00654   0.0015   0.0383   0.9627
   5.750   0.6370   0.01415   0.00682   0.0013   0.0362   0.9638
   6.000   0.6644   0.01443   0.00710   0.0012   0.0342   0.9652
   6.250   0.6903   0.01477   0.00742   0.0015   0.0325   0.9670
   6.500   0.7143   0.01504   0.00772   0.0022   0.0313   0.9691
   6.750   0.7294   0.01531   0.00801   0.0049   0.0301   0.9730
   7.000   0.7567   0.01565   0.00835   0.0047   0.0288   0.9740
   7.250   0.7841   0.01602   0.00873   0.0046   0.0276   0.9749
   7.500   0.8106   0.01637   0.00912   0.0047   0.0267   0.9760
   7.750   0.8366   0.01672   0.00950   0.0048   0.0258   0.9773
   8.000   0.8617   0.01712   0.00992   0.0051   0.0250   0.9789
   8.250   0.8844   0.01755   0.01036   0.0059   0.0243   0.9808
   8.500   0.9029   0.01805   0.01089   0.0076   0.0239   0.9832
   8.750   0.9246   0.01847   0.01138   0.0086   0.0232   0.9849
   9.000   0.9507   0.01895   0.01191   0.0086   0.0228   0.9859
   9.250   0.9756   0.01946   0.01248   0.0088   0.0223   0.9870
   9.500   0.9991   0.01994   0.01301   0.0092   0.0219   0.9883
   9.750   1.0213   0.02047   0.01359   0.0100   0.0215   0.9897
  10.000   1.0426   0.02101   0.01417   0.0108   0.0211   0.9913
  10.250   1.0624   0.02163   0.01484   0.0119   0.0208   0.9931
  10.500   1.0803   0.02237   0.01562   0.0133   0.0205   0.9946
  10.750   1.1008   0.02300   0.01634   0.0141   0.0201   0.9959
  11.000   1.1204   0.02361   0.01706   0.0151   0.0199   0.9973
  11.250   1.1390   0.02430   0.01785   0.0163   0.0196   0.9986
  11.500   1.1583   0.02502   0.01866   0.0172   0.0193   0.9999
  11.750   1.1631   0.02565   0.01938   0.0211   0.0191   1.0000
  12.000   1.1657   0.02634   0.02017   0.0253   0.0190   1.0000
  12.250   1.1683   0.02707   0.02098   0.0294   0.0188   1.0000
  12.500   1.1721   0.02774   0.02173   0.0332   0.0185   1.0000
  12.750   1.1740   0.02862   0.02271   0.0371   0.0185   1.0000
  13.000   1.1769   0.02943   0.02360   0.0406   0.0183   1.0000
  13.250   1.1784   0.03039   0.02465   0.0442   0.0182   1.0000
  13.500   1.1791   0.03146   0.02583   0.0477   0.0181   1.0000
  13.750   1.1807   0.03249   0.02693   0.0509   0.0179   1.0000
  14.000   1.1811   0.03366   0.02818   0.0539   0.0177   1.0000
  14.250   1.1791   0.03514   0.02977   0.0569   0.0177   1.0000
  14.500   1.1775   0.03662   0.03133   0.0596   0.0176   1.0000
  14.750   1.1723   0.03856   0.03340   0.0621   0.0176   1.0000
  15.000   1.1666   0.04068   0.03563   0.0641   0.0175   1.0000
  15.250   1.1603   0.04302   0.03808   0.0657   0.0174   1.0000
  15.500   1.1495   0.04605   0.04122   0.0667   0.0172   1.0000
  15.750   1.1375   0.04958   0.04490   0.0670   0.0172   1.0000
  16.000   1.1269   0.05335   0.04881   0.0664   0.0172   1.0000
  16.250   1.1087   0.05865   0.05430   0.0645   0.0171   1.0000
  16.500   1.0901   0.06467   0.06050   0.0615   0.0171   1.0000
  16.750   1.0678   0.07195   0.06795   0.0573   0.0172   1.0000
  17.000   1.0394   0.08100   0.07719   0.0518   0.0171   1.0000
  17.250   1.0026   0.09182   0.08821   0.0455   0.0172   1.0000
  17.500   0.9348   0.10947   0.10616   0.0354   0.0173   1.0000
<< Back to NACA/LANGLEY SYMMETRICAL (n0011sc-il)

Polar data table (+)

Polar graphs


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