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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 100,000
Max Cl/Cd: 42.52 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nl722343-il-100000.txt
Download as CSV file: xf-nl722343-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-43 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4937   0.09714   0.09204  -0.0239   1.0000   0.0948
  -8.750  -0.5107   0.09350   0.08851  -0.0288   1.0000   0.0973
  -8.500  -0.5350   0.08975   0.08488  -0.0333   1.0000   0.0979
  -8.250  -0.5119   0.08563   0.08077  -0.0288   1.0000   0.1023
  -8.000  -0.5117   0.08267   0.07786  -0.0282   1.0000   0.1060
  -7.750  -0.5251   0.07901   0.07427  -0.0302   1.0000   0.1083
  -7.500  -0.5486   0.07551   0.07070  -0.0339   1.0000   0.1120
  -7.000  -0.5442   0.06822   0.06349  -0.0316   1.0000   0.1194
  -6.750  -0.5618   0.06685   0.06172  -0.0330   1.0000   0.1281
  -6.500  -0.5503   0.06165   0.05678  -0.0309   1.0000   0.1321
  -6.250  -0.5560   0.05999   0.05473  -0.0308   1.0000   0.1442
  -6.000  -0.5420   0.05589   0.05094  -0.0282   1.0000   0.1495
  -5.750  -0.5381   0.05306   0.04799  -0.0273   1.0000   0.1626
  -5.500  -0.5310   0.05039   0.04526  -0.0259   1.0000   0.1779
  -5.250  -0.5220   0.04784   0.04270  -0.0241   1.0000   0.1954
  -5.000  -0.5144   0.04552   0.04032  -0.0226   1.0000   0.2231
  -4.250  -0.4224   0.03157   0.02369  -0.0227   1.0000   0.0812
  -4.000  -0.3985   0.02853   0.02024  -0.0216   1.0000   0.0742
  -3.750  -0.3728   0.02703   0.01819  -0.0199   1.0000   0.0687
  -3.500  -0.3484   0.02472   0.01567  -0.0190   1.0000   0.0662
  -3.250  -0.3233   0.02299   0.01370  -0.0179   1.0000   0.0647
  -3.000  -0.2981   0.02158   0.01213  -0.0168   1.0000   0.0646
  -2.750  -0.2737   0.02044   0.01089  -0.0157   1.0000   0.0662
  -2.500  -0.2500   0.01947   0.00986  -0.0146   1.0000   0.0710
  -2.250  -0.2277   0.01834   0.00888  -0.0135   1.0000   0.0769
  -2.000  -0.2052   0.01754   0.00807  -0.0122   1.0000   0.0850
  -1.750  -0.1827   0.01663   0.00727  -0.0112   1.0000   0.1126
  -1.500  -0.1882   0.01457   0.00809  -0.0026   1.0000   0.7792
  -1.250  -0.0366   0.01569   0.00907  -0.0149   1.0000   1.0000
  -1.000  -0.0320   0.01555   0.00887  -0.0117   1.0000   1.0000
  -0.750  -0.0280   0.01541   0.00866  -0.0084   1.0000   1.0000
  -0.500  -0.0248   0.01525   0.00846  -0.0051   1.0000   1.0000
  -0.250  -0.0223   0.01507   0.00824  -0.0017   1.0000   1.0000
   0.000  -0.0198   0.01487   0.00801   0.0017   1.0000   1.0000
   0.250  -0.0146   0.01470   0.00781   0.0046   1.0000   1.0000
   0.500  -0.0017   0.01467   0.00773   0.0061   1.0000   1.0000
   0.750   0.0166   0.01476   0.00776   0.0066   1.0000   1.0000
   1.000   0.0374   0.01493   0.00789   0.0067   1.0000   1.0000
   1.250   0.1096   0.01568   0.00862  -0.0025   0.9818   1.0000
   1.500   0.1734   0.01603   0.00897  -0.0098   0.9642   1.0000
   1.750   0.2331   0.01614   0.00913  -0.0160   0.9484   1.0000
   2.000   0.2963   0.01603   0.00911  -0.0223   0.9322   1.0000
   2.250   0.3553   0.01565   0.00885  -0.0275   0.9128   1.0000
   2.500   0.4258   0.01497   0.00835  -0.0341   0.8920   1.0000
   2.750   0.4840   0.01409   0.00764  -0.0380   0.8610   1.0000
   3.000   0.5220   0.01328   0.00694  -0.0379   0.8057   1.0000
   3.250   0.5651   0.01329   0.00572  -0.0373   0.5252   1.0000
   3.500   0.5703   0.01445   0.00603  -0.0331   0.4093   1.0000
   3.750   0.5827   0.01526   0.00644  -0.0306   0.3633   1.0000
   4.000   0.6009   0.01599   0.00693  -0.0292   0.3361   1.0000
   4.250   0.6237   0.01667   0.00747  -0.0286   0.3155   1.0000
   4.500   0.6486   0.01736   0.00807  -0.0284   0.2994   1.0000
   4.750   0.6746   0.01808   0.00871  -0.0283   0.2854   1.0000
   5.000   0.7014   0.01886   0.00941  -0.0285   0.2732   1.0000
   5.250   0.7279   0.01955   0.01015  -0.0285   0.2612   1.0000
   5.500   0.7545   0.02032   0.01099  -0.0285   0.2497   1.0000
   5.750   0.7810   0.02118   0.01189  -0.0285   0.2384   1.0000
   6.000   0.8073   0.02209   0.01277  -0.0285   0.2266   1.0000
   6.250   0.8328   0.02295   0.01367  -0.0283   0.2139   1.0000
   6.500   0.8568   0.02376   0.01461  -0.0279   0.1999   1.0000
   6.750   0.8798   0.02452   0.01538  -0.0274   0.1839   1.0000
   7.000   0.9006   0.02510   0.01604  -0.0265   0.1660   1.0000
   7.250   0.9202   0.02559   0.01671  -0.0253   0.1468   1.0000
   7.500   0.9391   0.02600   0.01713  -0.0241   0.1268   1.0000
   7.750   0.9569   0.02675   0.01801  -0.0225   0.1052   1.0000
   8.000   0.9755   0.02728   0.01848  -0.0211   0.0894   1.0000
   8.250   0.9961   0.02885   0.02013  -0.0199   0.0788   1.0000
   8.500   1.0163   0.03095   0.02245  -0.0188   0.0714   1.0000
   8.750   1.0365   0.03285   0.02425  -0.0181   0.0655   1.0000
   9.000   1.0535   0.03573   0.02765  -0.0165   0.0627   1.0000
   9.250   1.0672   0.03880   0.03121  -0.0148   0.0605   1.0000
   9.500   1.0792   0.04166   0.03441  -0.0131   0.0584   1.0000
   9.750   1.0915   0.04415   0.03707  -0.0117   0.0562   1.0000
  10.000   1.0981   0.04833   0.04142  -0.0103   0.0545   1.0000
  10.250   1.0941   0.05209   0.04569  -0.0075   0.0542   1.0000
  10.500   1.0853   0.05637   0.05040  -0.0049   0.0542   1.0000
  10.750   1.0726   0.06075   0.05510  -0.0025   0.0543   1.0000
  11.000   1.0558   0.06499   0.05956   0.0000   0.0545   1.0000
  11.250   1.0324   0.06870   0.06355   0.0022   0.0549   1.0000
  11.500   0.9021   0.08956   0.08495  -0.0105   0.0630   1.0000
  11.750   0.8814   0.09982   0.09518  -0.0169   0.0643   1.0000
  12.000   0.8738   0.10671   0.10205  -0.0198   0.0650   1.0000
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