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GRUMMAN K-3 AIRFOIL (k3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GRUMMAN K-3 AIRFOIL (k3-il)
Reynolds number: 50,000
Max Cl/Cd: 23.04 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k3-il-50000-n5.txt
Download as CSV file: xf-k3-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GRUMMAN K-3 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6054   0.10761   0.09805  -0.0529   0.9999   0.1342
 -12.750  -0.7632   0.07952   0.06966  -0.0644   0.9999   0.1386
 -12.500  -0.8360   0.06966   0.05952  -0.0657   0.9999   0.1396
 -12.250  -0.8818   0.06412   0.05373  -0.0644   0.9999   0.1409
 -12.000  -0.8904   0.06199   0.05159  -0.0624   0.9999   0.1431
 -11.750  -0.8904   0.06063   0.05027  -0.0603   0.9999   0.1458
 -11.500  -0.9081   0.05830   0.04785  -0.0575   0.9999   0.1480
 -11.250  -0.9296   0.05575   0.04516  -0.0545   0.9999   0.1501
 -11.000  -0.9471   0.05276   0.04188  -0.0527   0.9999   0.1530
 -10.750  -0.9345   0.05205   0.04131  -0.0510   0.9999   0.1564
 -10.500  -0.9316   0.05050   0.03971  -0.0494   0.9999   0.1604
 -10.250  -0.9337   0.04826   0.03719  -0.0482   0.9999   0.1649
 -10.000  -0.9199   0.04752   0.03658  -0.0466   0.9999   0.1691
  -9.750  -0.9118   0.04611   0.03508  -0.0454   0.9999   0.1744
  -9.500  -0.9013   0.04479   0.03369  -0.0444   0.9999   0.1799
  -9.250  -0.8880   0.04383   0.03275  -0.0432   0.9999   0.1855
  -9.000  -0.8757   0.04247   0.03124  -0.0425   0.9999   0.1924
  -8.750  -0.8600   0.04173   0.03059  -0.0414   0.9999   0.1986
  -8.500  -0.8450   0.04048   0.02918  -0.0410   0.9999   0.2066
  -8.250  -0.8281   0.03981   0.02863  -0.0399   0.9999   0.2136
  -8.000  -0.8107   0.03874   0.02745  -0.0397   0.9999   0.2226
  -7.750  -0.7928   0.03807   0.02690  -0.0389   0.9999   0.2308
  -7.500  -0.7738   0.03717   0.02598  -0.0387   0.9999   0.2411
  -7.250  -0.7542   0.03642   0.02528  -0.0385   0.9999   0.2526
  -7.000  -0.7340   0.03572   0.02469  -0.0384   0.9999   0.2650
  -6.750  -0.7125   0.03501   0.02405  -0.0385   0.9999   0.2791
  -6.500  -0.6901   0.03435   0.02346  -0.0388   0.9999   0.2950
  -6.250  -0.6674   0.03382   0.02304  -0.0389   0.9999   0.3119
  -6.000  -0.6447   0.03346   0.02287  -0.0388   0.9999   0.3299
  -5.750  -0.6217   0.03325   0.02281  -0.0386   0.9999   0.3502
  -5.500  -0.5994   0.03325   0.02299  -0.0380   0.9999   0.3714
  -5.250  -0.5778   0.03348   0.02336  -0.0370   0.9999   0.3922
  -5.000  -0.5564   0.03380   0.02378  -0.0359   0.9999   0.4128
  -4.750  -0.5345   0.03416   0.02418  -0.0349   0.9999   0.4327
  -4.500  -0.5050   0.03472   0.02472  -0.0353   0.9970   0.4530
  -4.250  -0.4747   0.03527   0.02524  -0.0360   0.9943   0.4722
  -4.000  -0.4441   0.03577   0.02566  -0.0369   0.9918   0.4908
  -3.750  -0.4194   0.03651   0.02641  -0.0358   0.9884   0.5034
  -3.500  -0.3910   0.03709   0.02696  -0.0359   0.9850   0.5174
  -3.250  -0.3580   0.03749   0.02727  -0.0376   0.9822   0.5338
  -3.000  -0.3351   0.03825   0.02806  -0.0360   0.9787   0.5432
  -2.750  -0.3051   0.03849   0.02824  -0.0371   0.9749   0.5574
  -2.500  -0.2800   0.03914   0.02891  -0.0361   0.9711   0.5670
  -2.250  -0.2455   0.03949   0.02921  -0.0382   0.9681   0.5803
  -2.000  -0.2255   0.03990   0.02966  -0.0363   0.9631   0.5887
  -1.750  -0.1917   0.04007   0.02978  -0.0385   0.9589   0.6022
  -1.500  -0.1663   0.04068   0.03045  -0.0374   0.9549   0.6100
  -1.250  -0.1365   0.04078   0.03052  -0.0388   0.9497   0.6220
  -1.000  -0.1109   0.04106   0.03085  -0.0385   0.9445   0.6296
  -0.750  -0.0792   0.04144   0.03127  -0.0393   0.9401   0.6379
  -0.500  -0.0462   0.04139   0.03119  -0.0419   0.9339   0.6483
  -0.250  -0.0201   0.04163   0.03150  -0.0414   0.9279   0.6536
   0.000   0.0101   0.04182   0.03174  -0.0422   0.9221   0.6602
   0.250   0.0434   0.04186   0.03180  -0.0445   0.9148   0.6680
   0.500   0.0822   0.04203   0.03202  -0.0471   0.9095   0.6740
   0.750   0.1041   0.04206   0.03214  -0.0463   0.9001   0.6790
   1.000   0.1429   0.04219   0.03234  -0.0488   0.8936   0.6850
   1.250   0.1749   0.04219   0.03240  -0.0507   0.8835   0.6914
   1.500   0.2166   0.04219   0.03249  -0.0535   0.8760   0.6965
   1.750   0.2419   0.04208   0.03250  -0.0530   0.8633   0.7010
   2.000   0.2782   0.04180   0.03233  -0.0545   0.8504   0.7062
   2.250   0.3238   0.04101   0.03164  -0.0571   0.8328   0.7120
   2.500   0.3667   0.03988   0.03061  -0.0586   0.8110   0.7174
   2.750   0.4007   0.03877   0.02964  -0.0580   0.7897   0.7217
   3.000   0.4342   0.03783   0.02884  -0.0579   0.7692   0.7265
   3.250   0.4678   0.03696   0.02811  -0.0580   0.7474   0.7318
   3.500   0.5040   0.03605   0.02734  -0.0587   0.7232   0.7376
   3.750   0.5202   0.03569   0.02715  -0.0559   0.6923   0.7417
   4.000   0.5405   0.03522   0.02684  -0.0539   0.6543   0.7463
   4.250   0.5767   0.03389   0.02558  -0.0532   0.6028   0.7515
   4.500   0.6470   0.03120   0.02216  -0.0555   0.4818   0.7578
   4.750   0.6678   0.03174   0.02201  -0.0534   0.3882   0.7622
   5.250   0.6992   0.03380   0.02333  -0.0500   0.2933   0.7720
   5.500   0.7222   0.03480   0.02407  -0.0499   0.2656   0.7773
   5.750   0.7450   0.03561   0.02475  -0.0493   0.2447   0.7822
   6.000   0.7680   0.03632   0.02539  -0.0485   0.2278   0.7876
   6.250   0.7959   0.03702   0.02608  -0.0486   0.2122   0.7938
   6.500   0.8282   0.03778   0.02681  -0.0496   0.1979   0.8001
   6.750   0.8559   0.03842   0.02742  -0.0493   0.1861   0.8057
   7.000   0.8853   0.03917   0.02814  -0.0496   0.1744   0.8119
   7.250   0.9160   0.04007   0.02913  -0.0503   0.1626   0.8188
   7.500   0.9396   0.04090   0.02999  -0.0496   0.1528   0.8254
   7.750   0.9635   0.04182   0.03084  -0.0492   0.1436   0.8331
   8.000   0.9845   0.04287   0.03209  -0.0485   0.1339   0.8408
   8.250   1.0041   0.04392   0.03323  -0.0474   0.1258   0.8488
   8.500   1.0252   0.04501   0.03425  -0.0469   0.1187   0.8575
   8.750   1.0396   0.04623   0.03576  -0.0450   0.1113   0.8666
   9.000   1.0555   0.04749   0.03713  -0.0437   0.1052   0.8772
   9.250   1.0690   0.04870   0.03844  -0.0420   0.0998   0.8895
   9.500   1.0795   0.05015   0.04012  -0.0398   0.0946   0.9035
   9.750   1.0900   0.05135   0.04141  -0.0379   0.0906   0.9213
  10.000   1.0979   0.05309   0.04342  -0.0358   0.0864   0.9476
  10.250   1.1074   0.05464   0.04512  -0.0347   0.0829   1.0001
  10.500   1.1200   0.05720   0.04790  -0.0345   0.0794   1.0001
  10.750   1.1283   0.05990   0.05084  -0.0340   0.0762   1.0001
  11.000   1.1416   0.06187   0.05277  -0.0339   0.0739   1.0001
  11.250   1.1336   0.06597   0.05735  -0.0325   0.0716   1.0001
  11.500   1.1297   0.06951   0.06116  -0.0316   0.0697   1.0001
  11.750   1.1299   0.07262   0.06440  -0.0312   0.0683   1.0001
  12.000   1.1293   0.07589   0.06775  -0.0309   0.0671   1.0001
  12.250   1.1020   0.08200   0.07430  -0.0307   0.0665   1.0001
  12.500   1.0699   0.08910   0.08180  -0.0319   0.0662   1.0001
  12.750   1.0299   0.09806   0.09113  -0.0353   0.0662   1.0001
  13.000   0.9794   0.11053   0.10394  -0.0425   0.0666   1.0001
  13.250   0.9075   0.13210   0.12584  -0.0576   0.0671   1.0001
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