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NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il)
Reynolds number: 50,000
Max Cl/Cd: 30.56 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-k1-il-50000.txt
Download as CSV file: xf-k1-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4552   0.11097   0.10324  -0.0120   1.0000   0.3154
  -9.250  -0.6305   0.07559   0.06820  -0.0498   1.0000   0.1434
  -9.000  -0.6466   0.07037   0.06301  -0.0515   1.0000   0.1409
  -8.750  -0.7154   0.06177   0.05396  -0.0553   1.0000   0.1323
  -8.500  -0.7205   0.05771   0.04969  -0.0547   1.0000   0.1317
  -8.250  -0.7228   0.05366   0.04532  -0.0544   1.0000   0.1314
  -8.000  -0.7204   0.04973   0.04096  -0.0541   1.0000   0.1316
  -7.750  -0.7123   0.04601   0.03673  -0.0540   1.0000   0.1322
  -7.500  -0.6983   0.04264   0.03289  -0.0538   1.0000   0.1331
  -7.250  -0.6799   0.04000   0.03019  -0.0530   1.0000   0.1355
  -7.000  -0.6609   0.03772   0.02771  -0.0523   1.0000   0.1401
  -6.750  -0.6403   0.03528   0.02483  -0.0520   1.0000   0.1458
  -6.500  -0.6190   0.03340   0.02297  -0.0511   1.0000   0.1529
  -6.250  -0.5970   0.03153   0.02101  -0.0502   1.0000   0.1625
  -6.000  -0.5750   0.02986   0.01937  -0.0492   1.0000   0.1768
  -5.750  -0.5527   0.02823   0.01780  -0.0482   1.0000   0.1994
  -5.500  -0.5311   0.02641   0.01637  -0.0473   1.0000   0.2399
  -5.250  -0.5091   0.02431   0.01522  -0.0470   1.0000   0.3440
  -5.000  -0.4937   0.02465   0.01635  -0.0428   1.0000   0.4481
  -4.750  -0.4807   0.02604   0.01789  -0.0374   1.0000   0.5051
  -4.500  -0.4702   0.02774   0.01963  -0.0310   1.0000   0.5447
  -4.250  -0.4640   0.02965   0.02163  -0.0227   1.0000   0.5715
  -4.000  -0.4511   0.03063   0.02250  -0.0178   1.0000   0.6057
  -3.750  -0.4400   0.03128   0.02310  -0.0123   1.0000   0.6289
  -3.500  -0.4281   0.03161   0.02333  -0.0074   1.0000   0.6520
  -3.250  -0.4158   0.03172   0.02336  -0.0029   1.0000   0.6758
  -3.000  -0.4030   0.03163   0.02318   0.0012   1.0000   0.7010
  -2.750  -0.3873   0.03127   0.02270   0.0035   1.0000   0.7288
  -2.500  -0.3757   0.03081   0.02217   0.0077   1.0000   0.7509
  -2.250  -0.3622   0.03019   0.02145   0.0108   1.0000   0.7727
  -2.000  -0.3470   0.02947   0.02063   0.0131   1.0000   0.7940
  -1.750  -0.3307   0.02871   0.01978   0.0150   1.0000   0.8149
  -1.500  -0.3137   0.02794   0.01892   0.0165   1.0000   0.8352
  -1.250  -0.2964   0.02718   0.01807   0.0178   1.0000   0.8549
  -1.000  -0.2796   0.02639   0.01721   0.0194   1.0000   0.8734
  -0.750  -0.2610   0.02566   0.01641   0.0206   1.0000   0.8918
  -0.500  -0.2399   0.02500   0.01569   0.0211   1.0000   0.9102
  -0.250  -0.2144   0.02444   0.01509   0.0206   1.0000   0.9287
   0.000  -0.1821   0.02406   0.01465   0.0186   1.0000   0.9473
   0.250  -0.1403   0.02389   0.01443   0.0146   1.0000   0.9659
   0.500  -0.0871   0.02395   0.01446   0.0081   1.0000   0.9830
   0.750  -0.0376   0.02403   0.01454   0.0019   1.0000   0.9998
   1.000  -0.0360   0.02364   0.01417   0.0040   1.0000   1.0000
   1.250  -0.0243   0.02347   0.01401   0.0043   1.0000   1.0000
   1.500  -0.0031   0.02353   0.01408   0.0030   1.0000   1.0000
   1.750   0.0235   0.02378   0.01435   0.0007   1.0000   1.0000
   2.000   0.0531   0.02416   0.01477  -0.0020   1.0000   1.0000
   2.250   0.0839   0.02466   0.01531  -0.0050   1.0000   1.0000
   2.500   0.1153   0.02526   0.01598  -0.0081   1.0000   1.0000
   2.750   0.1465   0.02595   0.01675  -0.0111   1.0000   1.0000
   3.000   0.1772   0.02674   0.01764  -0.0142   1.0000   1.0000
   3.250   0.2070   0.02764   0.01866  -0.0171   1.0000   1.0000
   3.500   0.2833   0.02945   0.02070  -0.0280   0.9731   1.0000
   3.750   0.3714   0.03067   0.02223  -0.0390   0.9289   1.0000
   4.000   0.4538   0.03067   0.02261  -0.0468   0.8862   1.0000
   4.250   0.5154   0.02957   0.02189  -0.0498   0.8412   1.0000
   4.500   0.5825   0.02660   0.01943  -0.0502   0.7821   1.0000
   4.750   0.6428   0.02136   0.01431  -0.0443   0.6212   1.0000
   5.000   0.6825   0.02233   0.01352  -0.0421   0.4455   1.0000
   5.250   0.7153   0.02404   0.01475  -0.0428   0.3881   1.0000
   5.500   0.7491   0.02560   0.01605  -0.0439   0.3468   1.0000
   5.750   0.7811   0.02719   0.01750  -0.0447   0.3115   1.0000
   6.000   0.8111   0.02891   0.01899  -0.0453   0.2775   1.0000
   6.250   0.8392   0.03077   0.02074  -0.0456   0.2449   1.0000
   6.500   0.8652   0.03290   0.02290  -0.0455   0.2135   1.0000
   6.750   0.8907   0.03520   0.02510  -0.0455   0.1871   1.0000
   7.000   0.9155   0.03773   0.02782  -0.0453   0.1677   1.0000
   7.250   0.9397   0.04052   0.03080  -0.0450   0.1544   1.0000
   7.500   0.9637   0.04340   0.03382  -0.0448   0.1449   1.0000
   7.750   0.9814   0.04685   0.03782  -0.0438   0.1391   1.0000
   8.000   1.0021   0.05007   0.04114  -0.0435   0.1334   1.0000
   8.250   1.0093   0.05423   0.04598  -0.0419   0.1306   1.0000
   8.500   1.0148   0.05878   0.05103  -0.0405   0.1295   1.0000
   8.750   1.0149   0.06385   0.05656  -0.0392   0.1301   1.0000
   9.000   1.0112   0.06916   0.06223  -0.0381   0.1315   1.0000
   9.250   1.0060   0.07448   0.06782  -0.0373   0.1328   1.0000
   9.500   1.0020   0.07980   0.07330  -0.0368   0.1339   1.0000
   9.750   0.9377   0.08853   0.08243  -0.0378   0.1440   1.0000
  10.000   0.9451   0.09411   0.08802  -0.0382   0.1464   1.0000
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