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FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 79-W-151 A (fx79w151a-il)
Reynolds number: 200,000
Max Cl/Cd: 69.81 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx79w151a-il-200000.txt
Download as CSV file: xf-fx79w151a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 79-W-151 A                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3454   0.10643   0.10309  -0.0535   1.0000   0.0446
 -11.750  -0.4740   0.07210   0.06889  -0.0703   1.0000   0.0359
 -11.500  -0.5298   0.05861   0.05535  -0.0808   1.0000   0.0344
 -11.250  -0.5675   0.05560   0.05237  -0.0799   1.0000   0.0339
 -11.000  -0.6002   0.04535   0.04158  -0.0917   0.9832   0.0332
 -10.750  -0.6064   0.03973   0.03542  -0.0953   0.9714   0.0336
 -10.500  -0.6003   0.03576   0.03095  -0.0966   0.9603   0.0343
 -10.250  -0.5910   0.03299   0.02768  -0.0963   0.9489   0.0356
 -10.000  -0.5832   0.03024   0.02449  -0.0949   0.9376   0.0369
  -9.750  -0.5650   0.02870   0.02291  -0.0944   0.9288   0.0389
  -9.500  -0.5501   0.02814   0.02225  -0.0926   0.9179   0.0417
  -9.250  -0.5378   0.02713   0.02094  -0.0902   0.9073   0.0443
  -9.000  -0.5249   0.02529   0.01886  -0.0882   0.8991   0.0471
  -8.750  -0.5086   0.02478   0.01833  -0.0863   0.8893   0.0503
  -8.500  -0.4915   0.02418   0.01749  -0.0844   0.8809   0.0543
  -8.250  -0.4747   0.02307   0.01626  -0.0827   0.8727   0.0585
  -8.000  -0.4555   0.02276   0.01589  -0.0812   0.8643   0.0631
  -7.750  -0.4362   0.02202   0.01490  -0.0796   0.8569   0.0681
  -7.500  -0.4161   0.02156   0.01448  -0.0783   0.8488   0.0731
  -7.250  -0.3951   0.02127   0.01392  -0.0768   0.8416   0.0790
  -7.000  -0.3740   0.02053   0.01321  -0.0758   0.8340   0.0849
  -6.750  -0.3521   0.02029   0.01277  -0.0745   0.8269   0.0920
  -6.500  -0.3299   0.01963   0.01213  -0.0736   0.8198   0.0988
  -6.250  -0.3073   0.01942   0.01171  -0.0724   0.8125   0.1065
  -6.000  -0.2838   0.01879   0.01110  -0.0716   0.8064   0.1144
  -5.750  -0.2608   0.01844   0.01060  -0.0707   0.7985   0.1225
  -5.500  -0.2361   0.01799   0.01013  -0.0700   0.7932   0.1309
  -5.250  -0.2130   0.01761   0.00969  -0.0692   0.7849   0.1391
  -5.000  -0.1880   0.01729   0.00929  -0.0685   0.7792   0.1477
  -4.750  -0.1642   0.01689   0.00888  -0.0678   0.7717   0.1560
  -4.500  -0.1391   0.01663   0.00852  -0.0672   0.7655   0.1650
  -4.250  -0.1146   0.01623   0.00814  -0.0666   0.7593   0.1739
  -4.000  -0.0901   0.01594   0.00779  -0.0659   0.7522   0.1840
  -3.750  -0.0642   0.01561   0.00742  -0.0654   0.7472   0.1951
  -3.500  -0.0414   0.01530   0.00719  -0.0646   0.7394   0.2064
  -3.250  -0.0165   0.01496   0.00684  -0.0639   0.7338   0.2213
  -3.000   0.0066   0.01468   0.00663  -0.0630   0.7269   0.2405
  -2.750   0.0296   0.01431   0.00637  -0.0621   0.7207   0.2670
  -2.500   0.0519   0.01389   0.00612  -0.0610   0.7155   0.3127
  -2.250   0.0695   0.01341   0.00602  -0.0592   0.7083   0.3930
  -2.000   0.0861   0.01282   0.00588  -0.0569   0.7031   0.5147
  -1.750   0.1020   0.01239   0.00592  -0.0543   0.6967   0.6328
  -1.500   0.1267   0.01203   0.00595  -0.0531   0.6906   0.7491
  -1.250   0.1825   0.01193   0.00599  -0.0579   0.6856   0.8483
  -1.000   0.2373   0.01212   0.00616  -0.0630   0.6782   0.8935
  -0.750   0.2842   0.01229   0.00619  -0.0664   0.6727   0.9211
  -0.500   0.3312   0.01257   0.00638  -0.0699   0.6660   0.9381
  -0.250   0.3790   0.01277   0.00645  -0.0736   0.6596   0.9526
   0.000   0.4280   0.01296   0.00650  -0.0777   0.6540   0.9659
   0.250   0.4811   0.01310   0.00657  -0.0829   0.6467   0.9788
   0.500   0.5422   0.01308   0.00638  -0.0897   0.6411   0.9911
   0.750   0.5930   0.01301   0.00629  -0.0950   0.6335   1.0000
   1.000   0.6140   0.01301   0.00619  -0.0940   0.6280   1.0000
   1.250   0.6344   0.01306   0.00621  -0.0930   0.6219   1.0000
   1.500   0.6552   0.01311   0.00622  -0.0919   0.6156   1.0000
   1.750   0.6781   0.01315   0.00615  -0.0912   0.6109   1.0000
   2.000   0.6981   0.01327   0.00630  -0.0901   0.6042   1.0000
   2.250   0.7204   0.01333   0.00631  -0.0892   0.5986   1.0000
   2.500   0.7428   0.01344   0.00636  -0.0883   0.5933   1.0000
   2.750   0.7635   0.01357   0.00651  -0.0872   0.5867   1.0000
   3.000   0.7871   0.01367   0.00654  -0.0865   0.5817   1.0000
   3.250   0.8082   0.01386   0.00675  -0.0855   0.5759   1.0000
   3.500   0.8301   0.01400   0.00689  -0.0845   0.5700   1.0000
   3.750   0.8547   0.01414   0.00694  -0.0840   0.5654   1.0000
   4.000   0.8743   0.01436   0.00725  -0.0827   0.5589   1.0000
   4.250   0.8972   0.01451   0.00737  -0.0819   0.5534   1.0000
   4.500   0.9213   0.01471   0.00753  -0.0813   0.5489   1.0000
   4.750   0.9409   0.01496   0.00788  -0.0800   0.5426   1.0000
   5.000   0.9645   0.01513   0.00803  -0.0793   0.5376   1.0000
   5.250   0.9874   0.01537   0.00827  -0.0785   0.5326   1.0000
   5.500   1.0073   0.01564   0.00862  -0.0773   0.5266   1.0000
   5.750   1.0315   0.01584   0.00881  -0.0767   0.5221   1.0000
   6.000   1.0540   0.01613   0.00913  -0.0759   0.5173   1.0000
   6.250   1.0735   0.01643   0.00953  -0.0745   0.5115   1.0000
   6.500   1.0980   0.01663   0.00972  -0.0740   0.5069   1.0000
   6.750   1.1202   0.01696   0.01011  -0.0732   0.5022   1.0000
   7.000   1.1390   0.01729   0.01055  -0.0717   0.4965   1.0000
   7.250   1.1634   0.01752   0.01079  -0.0712   0.4921   1.0000
   7.500   1.1862   0.01786   0.01118  -0.0705   0.4876   1.0000
   7.750   1.2036   0.01823   0.01171  -0.0688   0.4818   1.0000
   8.000   1.2281   0.01843   0.01192  -0.0683   0.4768   1.0000
   8.250   1.2477   0.01875   0.01233  -0.0670   0.4710   1.0000
   8.500   1.2665   0.01894   0.01260  -0.0655   0.4639   1.0000
   8.750   1.2843   0.01898   0.01269  -0.0637   0.4546   1.0000
   9.000   1.2973   0.01877   0.01246  -0.0608   0.4403   1.0000
   9.250   1.3047   0.01869   0.01238  -0.0571   0.4244   1.0000
   9.500   1.3123   0.01882   0.01252  -0.0536   0.4104   1.0000
   9.750   1.3219   0.01907   0.01277  -0.0506   0.3986   1.0000
  10.000   1.3273   0.01945   0.01325  -0.0469   0.3875   1.0000
  10.250   1.3305   0.01988   0.01375  -0.0429   0.3768   1.0000
  10.500   1.3331   0.02041   0.01434  -0.0392   0.3641   1.0000
  10.750   1.3346   0.02114   0.01510  -0.0357   0.3492   1.0000
  11.000   1.3312   0.02220   0.01615  -0.0320   0.3279   1.0000
  11.250   1.3287   0.02352   0.01747  -0.0289   0.3043   1.0000
  11.500   1.3154   0.02569   0.01947  -0.0253   0.2663   1.0000
  11.750   1.2934   0.02886   0.02236  -0.0218   0.2180   1.0000
  12.000   1.2683   0.03274   0.02596  -0.0189   0.1754   1.0000
  12.250   1.2439   0.03695   0.02993  -0.0167   0.1379   1.0000
  12.500   1.2204   0.04140   0.03416  -0.0150   0.1029   1.0000
  12.750   1.1919   0.04670   0.03919  -0.0137   0.0688   1.0000
  13.000   1.1724   0.05139   0.04376  -0.0129   0.0528   1.0000
  13.250   1.1619   0.05534   0.04771  -0.0125   0.0450   1.0000
  13.500   1.1528   0.05928   0.05171  -0.0122   0.0405   1.0000
  13.750   1.1449   0.06315   0.05563  -0.0121   0.0366   1.0000
  14.000   1.1355   0.06730   0.05982  -0.0121   0.0332   1.0000
  14.250   1.1337   0.07058   0.06321  -0.0122   0.0323   1.0000
  14.500   1.1308   0.07402   0.06672  -0.0123   0.0301   1.0000
  14.750   1.1274   0.07754   0.07030  -0.0124   0.0287   1.0000
  15.000   1.1237   0.08103   0.07380  -0.0125   0.0276   1.0000
  15.250   1.1229   0.08391   0.07668  -0.0120   0.0265   1.0000
  15.500   1.1283   0.08617   0.07904  -0.0118   0.0258   1.0000
  15.750   1.1344   0.08833   0.08127  -0.0115   0.0250   1.0000
  16.000   1.1418   0.09022   0.08322  -0.0109   0.0241   1.0000
  16.250   1.1519   0.09166   0.08471  -0.0101   0.0237   1.0000
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