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

K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: K3311 (smoothed) (k3311sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.89 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k3311sm-il-1000000.txt
Download as CSV file: xf-k3311sm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: K3311 (smoothed)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4785   0.02502   0.02203  -0.0845   0.9736   0.0099
  -8.000  -0.4566   0.02030   0.01670  -0.0863   0.9685   0.0101
  -7.750  -0.4362   0.01647   0.01230  -0.0867   0.9601   0.0106
  -7.500  -0.4067   0.01526   0.01094  -0.0877   0.9535   0.0110
  -7.250  -0.3774   0.01452   0.01009  -0.0884   0.9449   0.0113
  -7.000  -0.3496   0.01390   0.00936  -0.0886   0.9347   0.0117
  -6.750  -0.3226   0.01324   0.00857  -0.0886   0.9236   0.0121
  -6.500  -0.2969   0.01258   0.00777  -0.0882   0.9114   0.0125
  -6.250  -0.2720   0.01199   0.00704  -0.0877   0.8987   0.0130
  -6.000  -0.2469   0.01158   0.00652  -0.0871   0.8855   0.0135
  -5.750  -0.2224   0.01109   0.00590  -0.0864   0.8723   0.0139
  -5.500  -0.1999   0.01029   0.00499  -0.0855   0.8592   0.0152
  -5.250  -0.1740   0.01013   0.00477  -0.0850   0.8463   0.0162
  -5.000  -0.1485   0.00989   0.00446  -0.0845   0.8336   0.0173
  -4.750  -0.1228   0.00969   0.00416  -0.0840   0.8206   0.0181
  -4.500  -0.0994   0.00912   0.00347  -0.0831   0.8077   0.0198
  -4.250  -0.0738   0.00893   0.00322  -0.0826   0.7950   0.0212
  -4.000  -0.0478   0.00878   0.00301  -0.0821   0.7823   0.0228
  -3.750  -0.0214   0.00868   0.00285  -0.0818   0.7700   0.0240
  -3.500   0.0037   0.00834   0.00243  -0.0812   0.7580   0.0269
  -3.250   0.0299   0.00821   0.00225  -0.0808   0.7466   0.0293
  -3.000   0.0564   0.00814   0.00212  -0.0804   0.7351   0.0315
  -2.750   0.0822   0.00791   0.00184  -0.0799   0.7238   0.0372
  -2.500   0.1089   0.00783   0.00170  -0.0796   0.7130   0.0417
  -2.250   0.1351   0.00766   0.00153  -0.0792   0.7027   0.0550
  -2.000   0.1606   0.00744   0.00140  -0.0788   0.6926   0.0933
  -1.750   0.1846   0.00694   0.00127  -0.0782   0.6827   0.2158
  -1.500   0.2089   0.00655   0.00119  -0.0777   0.6734   0.3288
  -1.250   0.2334   0.00627   0.00115  -0.0771   0.6638   0.4256
  -1.000   0.2589   0.00607   0.00115  -0.0767   0.6545   0.5029
  -0.750   0.2849   0.00599   0.00114  -0.0763   0.6455   0.5512
  -0.500   0.3111   0.00594   0.00114  -0.0759   0.6360   0.5867
  -0.250   0.3369   0.00584   0.00115  -0.0754   0.6270   0.6331
   0.000   0.3616   0.00575   0.00118  -0.0747   0.6180   0.6897
   0.250   0.3861   0.00562   0.00120  -0.0739   0.6091   0.7492
   0.500   0.4107   0.00554   0.00123  -0.0731   0.6004   0.7961
   0.750   0.4347   0.00545   0.00126  -0.0721   0.5914   0.8493
   1.000   0.4696   0.00531   0.00131  -0.0735   0.5822   0.9301
   1.250   0.5369   0.00538   0.00134  -0.0824   0.5713   0.9752
   1.500   0.5751   0.00549   0.00139  -0.0847   0.5615   0.9957
   1.750   0.6101   0.00557   0.00142  -0.0864   0.5515   1.0000
   2.000   0.6348   0.00566   0.00146  -0.0857   0.5424   1.0000
   2.250   0.6596   0.00576   0.00151  -0.0850   0.5329   1.0000
   2.500   0.6848   0.00584   0.00156  -0.0845   0.5238   1.0000
   2.750   0.7097   0.00594   0.00162  -0.0839   0.5147   1.0000
   3.000   0.7347   0.00605   0.00169  -0.0833   0.5047   1.0000
   3.250   0.7599   0.00615   0.00177  -0.0827   0.4954   1.0000
   3.500   0.7848   0.00627   0.00185  -0.0821   0.4854   1.0000
   3.750   0.8098   0.00639   0.00193  -0.0815   0.4748   1.0000
   4.000   0.8348   0.00651   0.00203  -0.0810   0.4636   1.0000
   4.250   0.8597   0.00665   0.00214  -0.0804   0.4520   1.0000
   4.500   0.8844   0.00679   0.00225  -0.0797   0.4406   1.0000
   4.750   0.9089   0.00695   0.00237  -0.0791   0.4287   1.0000
   5.500   0.9817   0.00750   0.00281  -0.0771   0.3852   1.0000
   5.750   1.0044   0.00778   0.00299  -0.0762   0.3597   1.0000
   6.000   1.0262   0.00814   0.00322  -0.0751   0.3300   1.0000
   6.250   1.0484   0.00847   0.00345  -0.0742   0.3045   1.0000
   6.500   1.0694   0.00888   0.00373  -0.0730   0.2746   1.0000
   6.750   1.0908   0.00927   0.00401  -0.0720   0.2491   1.0000
   7.000   1.1116   0.00969   0.00433  -0.0708   0.2235   1.0000
   7.250   1.1311   0.01021   0.00469  -0.0694   0.1928   1.0000
   7.500   1.1499   0.01076   0.00508  -0.0680   0.1633   1.0000
   7.750   1.1679   0.01135   0.00552  -0.0664   0.1343   1.0000
   8.000   1.1850   0.01198   0.00600  -0.0647   0.1062   1.0000
   8.250   1.2010   0.01266   0.00653  -0.0629   0.0788   1.0000
   8.500   1.2159   0.01339   0.00712  -0.0608   0.0541   1.0000
   8.750   1.2303   0.01412   0.00773  -0.0587   0.0359   1.0000
   9.000   1.2458   0.01475   0.00831  -0.0567   0.0263   1.0000
   9.250   1.2611   0.01534   0.00889  -0.0547   0.0213   1.0000
   9.500   1.2761   0.01583   0.00941  -0.0526   0.0189   1.0000
   9.750   1.2855   0.01654   0.01015  -0.0495   0.0162   1.0000
  10.000   1.3002   0.01701   0.01067  -0.0474   0.0153   1.0000
  10.250   1.3145   0.01752   0.01121  -0.0454   0.0142   1.0000
  10.500   1.3271   0.01814   0.01186  -0.0432   0.0134   1.0000
  10.750   1.3345   0.01907   0.01286  -0.0403   0.0122   1.0000
  11.000   1.3443   0.01991   0.01377  -0.0380   0.0116   1.0000
  11.250   1.3571   0.02060   0.01453  -0.0362   0.0111   1.0000
  11.500   1.3682   0.02143   0.01541  -0.0343   0.0106   1.0000
  11.750   1.3795   0.02228   0.01631  -0.0326   0.0101   1.0000
  12.000   1.3885   0.02332   0.01742  -0.0308   0.0097   1.0000
  12.250   1.3956   0.02457   0.01871  -0.0290   0.0092   1.0000
  12.500   1.3909   0.02679   0.02107  -0.0264   0.0086   1.0000
  12.750   1.3993   0.02812   0.02246  -0.0252   0.0084   1.0000
  13.000   1.4057   0.02968   0.02411  -0.0239   0.0083   1.0000
  13.250   1.4155   0.03100   0.02550  -0.0231   0.0079   1.0000
  13.500   1.4211   0.03277   0.02736  -0.0221   0.0077   1.0000
  13.750   1.4261   0.03465   0.02931  -0.0214   0.0074   1.0000
  14.000   1.4266   0.03704   0.03181  -0.0206   0.0073   1.0000
  14.250   1.4289   0.03933   0.03419  -0.0200   0.0071   1.0000
  14.500   1.4328   0.04152   0.03644  -0.0197   0.0068   1.0000
  14.750   1.4310   0.04437   0.03937  -0.0194   0.0066   1.0000
  15.000   1.4272   0.04754   0.04265  -0.0193   0.0066   1.0000
  15.250   1.4187   0.05138   0.04659  -0.0193   0.0063   1.0000
  15.500   1.4056   0.05586   0.05119  -0.0196   0.0061   1.0000
  15.750   1.3934   0.06040   0.05587  -0.0201   0.0060   1.0000
  16.000   1.3883   0.06419   0.05976  -0.0206   0.0059   1.0000
  16.250   1.3821   0.06819   0.06387  -0.0214   0.0059   1.0000
  16.500   1.3824   0.07150   0.06727  -0.0222   0.0058   1.0000
  16.750   1.3747   0.07588   0.07177  -0.0232   0.0058   1.0000
  17.000   1.3687   0.08013   0.07612  -0.0243   0.0057   1.0000
  17.250   1.3618   0.08464   0.08075  -0.0256   0.0056   1.0000
  17.500   1.3529   0.08952   0.08574  -0.0271   0.0056   1.0000
  17.750   1.3461   0.09416   0.09048  -0.0287   0.0055   1.0000
  18.000   1.3383   0.09909   0.09551  -0.0305   0.0054   1.0000
  18.250   1.3308   0.10407   0.10059  -0.0324   0.0054   1.0000
  18.500   1.3235   0.10916   0.10579  -0.0346   0.0052   1.0000
  18.750   1.3114   0.11503   0.11178  -0.0370   0.0052   1.0000
  19.000   1.3043   0.12031   0.11714  -0.0394   0.0051   1.0000
<< Back to K3311 (smoothed) (k3311sm-il)

Polar data table (+)

Polar graphs


<< Back to K3311 (smoothed) (k3311sm-il)