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NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il)
Reynolds number: 100,000
Max Cl/Cd: 38.8 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-k1-il-100000-n5.txt
Download as CSV file: xf-k1-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NYU/GRUMMAN K-1 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7298   0.08226   0.07638  -0.0461   1.0000   0.0364
 -12.250  -0.7573   0.07373   0.06768  -0.0527   1.0000   0.0362
 -12.000  -0.7813   0.06680   0.06055  -0.0579   1.0000   0.0361
 -11.750  -0.8015   0.06114   0.05467  -0.0617   1.0000   0.0360
 -11.500  -0.8183   0.05647   0.04976  -0.0643   1.0000   0.0360
 -11.250  -0.8321   0.05266   0.04571  -0.0657   1.0000   0.0360
 -11.000  -0.8421   0.04937   0.04215  -0.0664   1.0000   0.0362
 -10.750  -0.8469   0.04641   0.03887  -0.0661   1.0000   0.0364
 -10.500  -0.8493   0.04383   0.03596  -0.0649   1.0000   0.0366
 -10.250  -0.8434   0.04205   0.03408  -0.0633   1.0000   0.0370
 -10.000  -0.8357   0.04055   0.03251  -0.0617   1.0000   0.0376
  -9.750  -0.8281   0.03902   0.03083  -0.0601   1.0000   0.0384
  -9.500  -0.8199   0.03737   0.02898  -0.0585   1.0000   0.0392
  -9.250  -0.8099   0.03565   0.02698  -0.0569   1.0000   0.0401
  -9.000  -0.7974   0.03400   0.02505  -0.0555   1.0000   0.0408
  -8.750  -0.7823   0.03269   0.02371  -0.0541   1.0000   0.0414
  -8.500  -0.7667   0.03145   0.02241  -0.0528   1.0000   0.0421
  -8.250  -0.7504   0.03025   0.02112  -0.0516   1.0000   0.0430
  -8.000  -0.7334   0.02910   0.01985  -0.0504   1.0000   0.0440
  -7.750  -0.7156   0.02801   0.01862  -0.0492   1.0000   0.0452
  -7.500  -0.6978   0.02700   0.01766  -0.0483   1.0000   0.0464
  -7.250  -0.6789   0.02608   0.01669  -0.0475   1.0000   0.0483
  -7.000  -0.6593   0.02517   0.01572  -0.0469   1.0000   0.0506
  -6.750  -0.6300   0.02420   0.01472  -0.0482   0.9975   0.0538
  -6.500  -0.5984   0.02321   0.01372  -0.0500   0.9945   0.0572
  -6.250  -0.5654   0.02228   0.01275  -0.0521   0.9919   0.0623
  -6.000  -0.5347   0.02141   0.01189  -0.0537   0.9888   0.0702
  -5.750  -0.5038   0.02056   0.01112  -0.0553   0.9862   0.0830
  -5.500  -0.4719   0.01969   0.01037  -0.0571   0.9840   0.1106
  -5.250  -0.4390   0.01870   0.00970  -0.0594   0.9820   0.1610
  -5.000  -0.4051   0.01781   0.00916  -0.0620   0.9804   0.2348
  -4.750  -0.3723   0.01707   0.00883  -0.0641   0.9785   0.3175
  -4.500  -0.3422   0.01668   0.00875  -0.0652   0.9757   0.3878
  -4.250  -0.3115   0.01658   0.00884  -0.0660   0.9728   0.4458
  -4.000  -0.2795   0.01665   0.00897  -0.0668   0.9699   0.4864
  -3.750  -0.2465   0.01679   0.00911  -0.0678   0.9674   0.5127
  -3.500  -0.2150   0.01691   0.00918  -0.0685   0.9645   0.5320
  -3.250  -0.1873   0.01705   0.00927  -0.0684   0.9607   0.5502
  -3.000  -0.1576   0.01725   0.00945  -0.0687   0.9575   0.5693
  -2.750  -0.1260   0.01747   0.00962  -0.0694   0.9548   0.5870
  -2.500  -0.0940   0.01769   0.00982  -0.0701   0.9525   0.5991
  -2.250  -0.0661   0.01783   0.00992  -0.0702   0.9490   0.6100
  -2.000  -0.0395   0.01800   0.01008  -0.0699   0.9450   0.6202
  -1.750  -0.0092   0.01815   0.01020  -0.0705   0.9418   0.6303
  -1.500   0.0223   0.01833   0.01038  -0.0711   0.9390   0.6395
  -1.250   0.0579   0.01845   0.01046  -0.0728   0.9366   0.6495
  -1.000   0.0800   0.01861   0.01066  -0.0716   0.9304   0.6565
  -0.750   0.1113   0.01872   0.01074  -0.0725   0.9263   0.6659
  -0.500   0.1436   0.01884   0.01090  -0.0733   0.9231   0.6727
  -0.250   0.1777   0.01897   0.01107  -0.0745   0.9206   0.6797
   0.000   0.2021   0.01910   0.01119  -0.0742   0.9146   0.6883
   0.250   0.2301   0.01921   0.01139  -0.0742   0.9096   0.6937
   0.500   0.2658   0.01924   0.01147  -0.0755   0.9051   0.7003
   0.750   0.2965   0.01917   0.01142  -0.0759   0.8952   0.7082
   1.000   0.3357   0.01869   0.01102  -0.0766   0.8824   0.7132
   1.250   0.3693   0.01801   0.01039  -0.0760   0.8637   0.7192
   1.500   0.4013   0.01741   0.00981  -0.0754   0.8456   0.7261
   1.750   0.4288   0.01706   0.00955  -0.0745   0.8305   0.7317
   2.000   0.4533   0.01692   0.00952  -0.0733   0.8164   0.7373
   2.250   0.4812   0.01672   0.00940  -0.0728   0.8018   0.7438
   2.500   0.5085   0.01649   0.00926  -0.0721   0.7832   0.7497
   2.750   0.5337   0.01625   0.00913  -0.0708   0.7581   0.7551
   3.000   0.5605   0.01600   0.00892  -0.0698   0.7210   0.7613
   3.250   0.5932   0.01557   0.00829  -0.0691   0.6554   0.7674
   3.500   0.6153   0.01591   0.00790  -0.0665   0.4962   0.7723
   3.750   0.6326   0.01695   0.00824  -0.0646   0.3722   0.7783
   4.000   0.6542   0.01782   0.00869  -0.0639   0.2993   0.7848
   4.250   0.6757   0.01842   0.00911  -0.0627   0.2595   0.7900
   4.500   0.6992   0.01896   0.00956  -0.0621   0.2327   0.7962
   4.750   0.7239   0.01954   0.01003  -0.0617   0.2115   0.8029
   5.000   0.7465   0.02004   0.01048  -0.0608   0.1935   0.8084
   5.250   0.7702   0.02056   0.01096  -0.0603   0.1770   0.8150
   5.500   0.7942   0.02108   0.01144  -0.0598   0.1610   0.8218
   5.750   0.8174   0.02150   0.01187  -0.0591   0.1451   0.8285
   6.000   0.8419   0.02192   0.01232  -0.0587   0.1279   0.8358
   6.250   0.8645   0.02239   0.01280  -0.0579   0.1135   0.8430
   6.500   0.8878   0.02288   0.01336  -0.0573   0.0974   0.8513
   6.750   0.9098   0.02345   0.01394  -0.0563   0.0827   0.8598
   7.000   0.9309   0.02417   0.01468  -0.0553   0.0705   0.8694
   7.250   0.9505   0.02491   0.01540  -0.0540   0.0623   0.8805
   7.500   0.9693   0.02571   0.01625  -0.0526   0.0564   0.8953
   7.750   0.9866   0.02654   0.01716  -0.0509   0.0525   0.9208
   8.000   1.0073   0.02757   0.01831  -0.0500   0.0493   1.0000
   8.250   1.0298   0.02884   0.01960  -0.0498   0.0468   1.0000
   8.500   1.0523   0.03012   0.02097  -0.0495   0.0442   1.0000
   8.750   1.0740   0.03146   0.02239  -0.0490   0.0418   1.0000
   9.000   1.0948   0.03278   0.02378  -0.0486   0.0397   1.0000
   9.250   1.1150   0.03427   0.02539  -0.0479   0.0379   1.0000
   9.500   1.1341   0.03575   0.02700  -0.0472   0.0362   1.0000
   9.750   1.1521   0.03730   0.02858  -0.0464   0.0350   1.0000
  10.000   1.1692   0.03931   0.03088  -0.0454   0.0339   1.0000
  10.250   1.1844   0.04133   0.03313  -0.0442   0.0329   1.0000
  10.500   1.1981   0.04331   0.03526  -0.0430   0.0322   1.0000
  10.750   1.2113   0.04529   0.03732  -0.0419   0.0316   1.0000
  11.000   1.2152   0.04806   0.04048  -0.0396   0.0310   1.0000
  11.250   1.2135   0.05105   0.04386  -0.0371   0.0306   1.0000
  11.500   1.2077   0.05417   0.04734  -0.0346   0.0301   1.0000
  11.750   1.1989   0.05743   0.05091  -0.0325   0.0297   1.0000
  12.000   1.1884   0.06086   0.05460  -0.0308   0.0293   1.0000
  12.250   1.1764   0.06456   0.05854  -0.0297   0.0290   1.0000
  12.500   1.1642   0.06846   0.06263  -0.0294   0.0287   1.0000
  12.750   1.1488   0.07306   0.06744  -0.0299   0.0285   1.0000
  13.000   1.1168   0.08058   0.07531  -0.0327   0.0286   1.0000
  13.250   1.0372   0.10015   0.09547  -0.0465   0.0300   1.0000
  13.500   0.9738   0.12314   0.11865  -0.0626   0.0313   1.0000
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