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

GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GRUMMAN K-2 AIRFOIL (k2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 66.71 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k2-il-1000000-n5.txt
Download as CSV file: xf-k2-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-2 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.0895   0.08171   0.07886  -0.0422   1.0000   0.0091
 -15.750  -1.1251   0.07050   0.06743  -0.0492   1.0000   0.0091
 -15.500  -1.1486   0.06242   0.05917  -0.0541   1.0000   0.0091
 -15.250  -1.1656   0.05624   0.05282  -0.0574   1.0000   0.0091
 -15.000  -1.1783   0.05133   0.04776  -0.0594   1.0000   0.0091
 -14.750  -1.1885   0.04730   0.04358  -0.0605   1.0000   0.0091
 -14.500  -1.1961   0.04393   0.04008  -0.0607   1.0000   0.0092
 -14.250  -1.2015   0.04110   0.03712  -0.0604   1.0000   0.0092
 -14.000  -1.2055   0.03860   0.03450  -0.0596   1.0000   0.0092
 -13.750  -1.2078   0.03645   0.03224  -0.0584   1.0000   0.0093
 -13.500  -1.2090   0.03456   0.03023  -0.0568   1.0000   0.0093
 -13.250  -1.2094   0.03287   0.02844  -0.0550   1.0000   0.0093
 -13.000  -1.2091   0.03137   0.02684  -0.0529   1.0000   0.0094
 -12.750  -1.2087   0.03000   0.02538  -0.0504   1.0000   0.0094
 -12.500  -1.2077   0.02879   0.02408  -0.0478   1.0000   0.0095
 -12.250  -1.2068   0.02771   0.02291  -0.0448   1.0000   0.0095
 -12.000  -1.2072   0.02673   0.02185  -0.0414   1.0000   0.0095
 -11.750  -1.2104   0.02590   0.02094  -0.0373   1.0000   0.0096
 -11.500  -1.1943   0.02484   0.01979  -0.0370   0.9990   0.0096
 -11.250  -1.1737   0.02380   0.01866  -0.0373   0.9979   0.0097
 -11.000  -1.1515   0.02283   0.01761  -0.0379   0.9969   0.0097
 -10.750  -1.1282   0.02193   0.01662  -0.0385   0.9959   0.0098
 -10.500  -1.1039   0.02113   0.01574  -0.0391   0.9952   0.0098
 -10.250  -1.0798   0.02017   0.01470  -0.0398   0.9945   0.0099
 -10.000  -1.0547   0.01925   0.01371  -0.0406   0.9939   0.0101
  -9.750  -1.0324   0.01851   0.01291  -0.0405   0.9926   0.0102
  -9.500  -1.0086   0.01786   0.01221  -0.0405   0.9914   0.0103
  -9.250  -0.9837   0.01727   0.01159  -0.0407   0.9904   0.0105
  -9.000  -0.9579   0.01673   0.01100  -0.0410   0.9894   0.0106
  -8.750  -0.9310   0.01622   0.01045  -0.0415   0.9885   0.0108
  -8.500  -0.9032   0.01573   0.00993  -0.0422   0.9877   0.0109
  -8.250  -0.8743   0.01526   0.00943  -0.0430   0.9869   0.0111
  -8.000  -0.8448   0.01480   0.00894  -0.0439   0.9862   0.0113
  -7.750  -0.8146   0.01436   0.00848  -0.0449   0.9855   0.0115
  -7.500  -0.7840   0.01395   0.00803  -0.0459   0.9849   0.0118
  -7.250  -0.7536   0.01356   0.00762  -0.0469   0.9845   0.0120
  -7.000  -0.7233   0.01319   0.00723  -0.0479   0.9841   0.0122
  -6.750  -0.6926   0.01284   0.00686  -0.0489   0.9837   0.0125
  -6.500  -0.6702   0.01246   0.00647  -0.0481   0.9816   0.0129
  -6.250  -0.6439   0.01214   0.00615  -0.0481   0.9801   0.0134
  -6.000  -0.6159   0.01185   0.00586  -0.0484   0.9790   0.0139
  -5.750  -0.5869   0.01157   0.00558  -0.0489   0.9780   0.0144
  -5.500  -0.5574   0.01131   0.00531  -0.0496   0.9771   0.0150
  -5.250  -0.5272   0.01104   0.00504  -0.0503   0.9763   0.0158
  -5.000  -0.4965   0.01078   0.00481  -0.0512   0.9756   0.0168
  -4.750  -0.4654   0.01055   0.00458  -0.0521   0.9750   0.0180
  -4.500  -0.4338   0.01031   0.00436  -0.0531   0.9744   0.0193
  -4.250  -0.4019   0.01008   0.00416  -0.0542   0.9739   0.0209
  -4.000  -0.3697   0.00987   0.00396  -0.0553   0.9734   0.0226
  -3.750  -0.3374   0.00966   0.00378  -0.0564   0.9730   0.0249
  -3.500  -0.3052   0.00946   0.00362  -0.0575   0.9726   0.0278
  -3.250  -0.2729   0.00927   0.00346  -0.0586   0.9723   0.0317
  -3.000  -0.2404   0.00907   0.00331  -0.0598   0.9720   0.0367
  -2.500  -0.1901   0.00869   0.00305  -0.0588   0.9665   0.0544
  -2.250  -0.1587   0.00843   0.00291  -0.0598   0.9656   0.0766
  -2.000  -0.1259   0.00805   0.00274  -0.0612   0.9648   0.1243
  -1.750  -0.0911   0.00758   0.00257  -0.0632   0.9641   0.1955
  -1.500  -0.0530   0.00706   0.00236  -0.0659   0.9631   0.2755
  -1.250  -0.0081   0.00635   0.00202  -0.0700   0.9605   0.3723
  -1.000   0.0320   0.00534   0.00161  -0.0734   0.9507   0.5369
  -0.750   0.0723   0.00471   0.00144  -0.0763   0.9384   0.6700
  -0.500   0.1105   0.00454   0.00125  -0.0782   0.9098   0.6869
  -0.250   0.1419   0.00467   0.00112  -0.0786   0.8379   0.6970
   0.000   0.1564   0.00564   0.00127  -0.0755   0.6319   0.7041
   0.250   0.1800   0.00615   0.00139  -0.0746   0.5258   0.7104
   0.500   0.2058   0.00655   0.00148  -0.0742   0.4440   0.7163
   0.750   0.2322   0.00689   0.00159  -0.0739   0.3749   0.7224
   1.000   0.2590   0.00721   0.00171  -0.0737   0.3190   0.7306
   1.250   0.2861   0.00751   0.00182  -0.0735   0.2637   0.7373
   1.500   0.3134   0.00775   0.00194  -0.0734   0.2244   0.7416
   1.750   0.3410   0.00800   0.00204  -0.0733   0.1870   0.7447
   2.000   0.3686   0.00826   0.00215  -0.0732   0.1514   0.7474
   2.250   0.3960   0.00857   0.00227  -0.0731   0.1129   0.7498
   2.500   0.4238   0.00879   0.00239  -0.0731   0.0917   0.7519
   2.750   0.4515   0.00897   0.00252  -0.0730   0.0794   0.7538
   3.000   0.4794   0.00915   0.00266  -0.0729   0.0694   0.7558
   3.250   0.5069   0.00938   0.00280  -0.0728   0.0525   0.7578
   3.500   0.5338   0.00972   0.00301  -0.0726   0.0306   0.7597
   3.750   0.5614   0.00996   0.00321  -0.0725   0.0228   0.7617
   4.000   0.5891   0.01021   0.00341  -0.0724   0.0164   0.7637
   4.250   0.6168   0.01045   0.00361  -0.0723   0.0134   0.7655
   4.500   0.6446   0.01067   0.00382  -0.0723   0.0119   0.7671
   4.750   0.6721   0.01092   0.00407  -0.0721   0.0108   0.7687
   5.000   0.6993   0.01116   0.00432  -0.0719   0.0101   0.7703
   5.250   0.7265   0.01140   0.00458  -0.0717   0.0096   0.7718
   5.500   0.7536   0.01167   0.00486  -0.0715   0.0091   0.7734
   5.750   0.7805   0.01196   0.00516  -0.0712   0.0086   0.7750
   6.000   0.8071   0.01232   0.00553  -0.0709   0.0082   0.7767
   6.250   0.8338   0.01265   0.00589  -0.0706   0.0080   0.7782
   6.500   0.8606   0.01297   0.00624  -0.0704   0.0078   0.7797
   6.750   0.8872   0.01332   0.00661  -0.0701   0.0076   0.7814
   7.000   0.9136   0.01370   0.00702  -0.0698   0.0074   0.7829
   7.250   0.9399   0.01409   0.00744  -0.0695   0.0073   0.7843
   7.500   0.9658   0.01451   0.00789  -0.0691   0.0071   0.7855
   7.750   0.9914   0.01494   0.00838  -0.0686   0.0070   0.7868
   8.000   1.0167   0.01538   0.00886  -0.0681   0.0069   0.7881
   8.250   1.0419   0.01584   0.00936  -0.0676   0.0067   0.7896
   8.500   1.0669   0.01631   0.00989  -0.0671   0.0066   0.7910
   8.750   1.0917   0.01681   0.01043  -0.0666   0.0065   0.7925
   9.000   1.1161   0.01734   0.01102  -0.0660   0.0064   0.7939
   9.250   1.1400   0.01795   0.01168  -0.0653   0.0063   0.7952
   9.500   1.1633   0.01860   0.01240  -0.0646   0.0062   0.7966
   9.750   1.1858   0.01936   0.01324  -0.0637   0.0061   0.7980
  10.000   1.2075   0.02022   0.01419  -0.0627   0.0061   0.7994
  10.250   1.2283   0.02116   0.01524  -0.0616   0.0060   0.8008
  10.500   1.2478   0.02225   0.01645  -0.0603   0.0060   0.8019
  10.750   1.2675   0.02321   0.01753  -0.0590   0.0059   0.8032
  11.000   1.2872   0.02411   0.01854  -0.0578   0.0059   0.8044
  11.250   1.3061   0.02506   0.01961  -0.0565   0.0059   0.8057
  11.500   1.3241   0.02606   0.02074  -0.0551   0.0059   0.8069
  11.750   1.3408   0.02716   0.02197  -0.0535   0.0059   0.8082
  12.000   1.3562   0.02834   0.02328  -0.0518   0.0059   0.8097
  12.250   1.3706   0.02955   0.02463  -0.0499   0.0058   0.8112
  12.500   1.3832   0.03085   0.02607  -0.0479   0.0058   0.8126
  12.750   1.3932   0.03231   0.02768  -0.0456   0.0058   0.8140
  13.000   1.4020   0.03373   0.02924  -0.0432   0.0058   0.8154
  13.250   1.4036   0.03536   0.03104  -0.0397   0.0058   0.8167
  13.500   1.4014   0.03710   0.03292  -0.0359   0.0058   0.8180
  13.750   1.3979   0.03903   0.03501  -0.0324   0.0058   0.8191
  14.000   1.3911   0.04131   0.03746  -0.0290   0.0058   0.8206
  14.250   1.3812   0.04404   0.04037  -0.0261   0.0058   0.8221
  14.500   1.3701   0.04718   0.04368  -0.0241   0.0057   0.8236
  14.750   1.3546   0.05126   0.04795  -0.0233   0.0057   0.8249
  15.000   1.3314   0.05736   0.05426  -0.0250   0.0057   0.8262
  15.250   1.2975   0.06879   0.06597  -0.0339   0.0058   0.8272
  15.500   1.1957   0.10011   0.09770  -0.0557   0.0058   0.8272
<< Back to GRUMMAN K-2 AIRFOIL (k2-il)

Polar data table (+)

Polar graphs


<< Back to GRUMMAN K-2 AIRFOIL (k2-il)