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NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il)
Reynolds number: 200,000
Max Cl/Cd: 53.76 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k1-il-200000.txt
Download as CSV file: xf-k1-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4541   0.10116   0.09751  -0.0358   1.0000   0.0954
 -10.750  -0.7775   0.06012   0.05578  -0.0655   1.0000   0.0597
 -10.500  -0.8265   0.04971   0.04481  -0.0658   1.0000   0.0482
 -10.250  -0.8756   0.04396   0.03813  -0.0615   1.0000   0.0449
 -10.000  -0.8717   0.04133   0.03532  -0.0596   1.0000   0.0447
  -9.750  -0.8666   0.03874   0.03247  -0.0579   1.0000   0.0445
  -9.500  -0.8593   0.03627   0.02966  -0.0565   1.0000   0.0446
  -9.250  -0.8492   0.03411   0.02707  -0.0552   1.0000   0.0449
  -9.000  -0.8343   0.03201   0.02474  -0.0543   1.0000   0.0455
  -8.750  -0.8160   0.03037   0.02309  -0.0533   1.0000   0.0460
  -8.500  -0.7974   0.02878   0.02133  -0.0525   1.0000   0.0463
  -8.250  -0.7778   0.02734   0.01976  -0.0516   1.0000   0.0468
  -8.000  -0.7573   0.02605   0.01833  -0.0509   1.0000   0.0473
  -7.750  -0.7361   0.02489   0.01703  -0.0502   1.0000   0.0482
  -7.500  -0.7141   0.02392   0.01585  -0.0496   1.0000   0.0494
  -7.250  -0.6920   0.02279   0.01473  -0.0490   1.0000   0.0506
  -7.000  -0.6693   0.02185   0.01381  -0.0485   1.0000   0.0518
  -6.750  -0.6458   0.02099   0.01294  -0.0481   1.0000   0.0532
  -6.250  -0.5971   0.01927   0.01126  -0.0479   1.0000   0.0570
  -6.000  -0.5715   0.01858   0.01053  -0.0481   1.0000   0.0601
  -5.750  -0.5443   0.01771   0.00976  -0.0489   1.0000   0.0644
  -5.500  -0.5088   0.01687   0.00898  -0.0514   0.9983   0.0731
  -5.250  -0.4722   0.01598   0.00827  -0.0541   0.9968   0.0953
  -5.000  -0.4325   0.01434   0.00735  -0.0584   0.9960   0.2083
  -4.750  -0.3943   0.01350   0.00699  -0.0617   0.9948   0.3142
  -4.500  -0.3569   0.01312   0.00694  -0.0643   0.9934   0.3943
  -4.250  -0.3207   0.01305   0.00704  -0.0664   0.9917   0.4514
  -4.000  -0.2892   0.01312   0.00721  -0.0673   0.9889   0.4952
  -3.750  -0.2570   0.01332   0.00747  -0.0682   0.9860   0.5292
  -3.500  -0.2235   0.01357   0.00775  -0.0693   0.9833   0.5527
  -3.250  -0.1887   0.01388   0.00804  -0.0707   0.9810   0.5723
  -3.000  -0.1547   0.01416   0.00830  -0.0719   0.9786   0.5884
  -2.750  -0.1275   0.01438   0.00853  -0.0718   0.9747   0.6005
  -2.500  -0.0962   0.01462   0.00876  -0.0725   0.9714   0.6118
  -2.250  -0.0605   0.01494   0.00904  -0.0741   0.9683   0.6268
  -2.000  -0.0271   0.01532   0.00951  -0.0748   0.9651   0.6366
  -1.750   0.0000   0.01552   0.00965  -0.0748   0.9599   0.6481
  -1.500   0.0309   0.01575   0.00995  -0.0752   0.9560   0.6548
  -1.250   0.0662   0.01599   0.01018  -0.0768   0.9533   0.6643
  -1.000   0.0974   0.01621   0.01042  -0.0775   0.9499   0.6720
  -0.750   0.1217   0.01643   0.01068  -0.0767   0.9441   0.6790
  -0.500   0.1586   0.01657   0.01079  -0.0787   0.9400   0.6889
  -0.250   0.1984   0.01661   0.01092  -0.0804   0.9348   0.6944
   0.000   0.2362   0.01644   0.01078  -0.0816   0.9242   0.7015
   0.250   0.2847   0.01595   0.01029  -0.0845   0.9123   0.7097
   0.500   0.3289   0.01534   0.00974  -0.0859   0.9039   0.7147
   0.750   0.3540   0.01519   0.00965  -0.0848   0.8931   0.7209
   1.000   0.3903   0.01480   0.00925  -0.0856   0.8869   0.7286
   1.250   0.4143   0.01460   0.00915  -0.0841   0.8769   0.7332
   1.500   0.4441   0.01419   0.00881  -0.0834   0.8693   0.7390
   1.750   0.4718   0.01394   0.00860  -0.0828   0.8588   0.7461
   2.000   0.5002   0.01347   0.00820  -0.0818   0.8498   0.7511
   2.250   0.5250   0.01318   0.00799  -0.0804   0.8363   0.7566
   2.500   0.5526   0.01280   0.00767  -0.0795   0.8216   0.7632
   2.750   0.5793   0.01241   0.00733  -0.0783   0.8020   0.7687
   3.000   0.6044   0.01206   0.00703  -0.0768   0.7748   0.7739
   3.250   0.6302   0.01179   0.00672  -0.0754   0.7249   0.7803
   3.500   0.6505   0.01210   0.00625  -0.0726   0.5595   0.7859
   3.750   0.6578   0.01387   0.00679  -0.0691   0.3442   0.7909
   4.000   0.6768   0.01488   0.00729  -0.0679   0.2649   0.7971
   4.250   0.7010   0.01551   0.00770  -0.0676   0.2296   0.8033
   4.500   0.7234   0.01597   0.00804  -0.0667   0.2079   0.8084
   4.750   0.7477   0.01641   0.00841  -0.0662   0.1909   0.8147
   5.000   0.7735   0.01681   0.00876  -0.0660   0.1766   0.8212
   5.250   0.7975   0.01711   0.00911  -0.0653   0.1643   0.8267
   5.500   0.8225   0.01746   0.00948  -0.0649   0.1520   0.8333
   5.750   0.8475   0.01778   0.00979  -0.0646   0.1381   0.8399
   6.000   0.8710   0.01808   0.01010  -0.0639   0.1209   0.8466
   6.250   0.8954   0.01857   0.01050  -0.0635   0.0950   0.8536
   6.500   0.9166   0.01928   0.01108  -0.0624   0.0744   0.8603
   6.750   0.9385   0.02004   0.01181  -0.0613   0.0646   0.8685
   7.000   0.9595   0.02079   0.01256  -0.0602   0.0590   0.8765
   7.250   0.9805   0.02159   0.01336  -0.0592   0.0545   0.8855
   7.500   1.0002   0.02244   0.01420  -0.0579   0.0512   0.8953
   7.750   1.0202   0.02324   0.01505  -0.0565   0.0485   0.9079
   8.000   1.0383   0.02416   0.01602  -0.0547   0.0466   0.9270
   8.250   1.0599   0.02505   0.01703  -0.0537   0.0447   1.0000
   8.500   1.0881   0.02656   0.01840  -0.0543   0.0431   1.0000
   8.750   1.1152   0.02797   0.02004  -0.0545   0.0416   1.0000
   9.000   1.1423   0.02950   0.02165  -0.0547   0.0402   1.0000
   9.250   1.1701   0.03133   0.02341  -0.0552   0.0391   1.0000
   9.500   1.1908   0.03320   0.02567  -0.0544   0.0379   1.0000
   9.750   1.2113   0.03487   0.02755  -0.0537   0.0365   1.0000
  10.000   1.2365   0.03665   0.02921  -0.0540   0.0353   1.0000
  10.250   1.2467   0.03900   0.03210  -0.0519   0.0343   1.0000
  10.500   1.2566   0.04135   0.03484  -0.0500   0.0333   1.0000
  10.750   1.2692   0.04347   0.03714  -0.0486   0.0324   1.0000
  11.000   1.2881   0.04556   0.03920  -0.0481   0.0318   1.0000
  11.250   1.2920   0.04885   0.04277  -0.0459   0.0314   1.0000
  11.500   1.2829   0.05229   0.04667  -0.0425   0.0313   1.0000
  11.750   1.2678   0.05567   0.05041  -0.0386   0.0312   1.0000
  12.000   1.2499   0.05923   0.05428  -0.0352   0.0313   1.0000
  12.250   1.2305   0.06313   0.05844  -0.0326   0.0313   1.0000
  12.500   1.2098   0.06747   0.06302  -0.0310   0.0313   1.0000
  12.750   1.1909   0.07211   0.06787  -0.0304   0.0314   1.0000
  13.000   1.1735   0.07710   0.07301  -0.0307   0.0315   1.0000
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