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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 500,000
Max Cl/Cd: 103.38 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e176-il-500000-n5.txt
Download as CSV file: xf-e176-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4053   0.08838   0.08621  -0.0221   1.0000   0.0106
  -8.500  -0.4032   0.08487   0.08273  -0.0236   1.0000   0.0102
  -8.250  -0.4032   0.08092   0.07882  -0.0256   1.0000   0.0100
  -8.000  -0.3890   0.07476   0.07263  -0.0336   0.9413   0.0101
  -7.750  -0.3841   0.07011   0.06783  -0.0386   0.8812   0.0098
  -7.500  -0.3847   0.06568   0.06327  -0.0424   0.8465   0.0096
  -7.250  -0.3826   0.05993   0.05740  -0.0478   0.8224   0.0098
  -7.000  -0.3763   0.05364   0.05095  -0.0532   0.8042   0.0097
  -6.750  -0.3674   0.04641   0.04349  -0.0581   0.7895   0.0095
  -6.500  -0.3561   0.03863   0.03536  -0.0615   0.7771   0.0096
  -6.250  -0.3427   0.03125   0.02749  -0.0631   0.7666   0.0096
  -6.000  -0.3243   0.02648   0.02222  -0.0635   0.7566   0.0101
  -5.750  -0.3034   0.02293   0.01817  -0.0635   0.7467   0.0101
  -5.500  -0.2806   0.02013   0.01490  -0.0633   0.7376   0.0100
  -5.250  -0.2562   0.01809   0.01245  -0.0630   0.7291   0.0100
  -5.000  -0.2306   0.01649   0.01050  -0.0627   0.7206   0.0101
  -4.750  -0.2045   0.01525   0.00898  -0.0625   0.7128   0.0102
  -4.500  -0.1781   0.01424   0.00775  -0.0622   0.7049   0.0104
  -4.250  -0.1513   0.01343   0.00676  -0.0620   0.6978   0.0107
  -4.000  -0.1244   0.01278   0.00596  -0.0618   0.6905   0.0110
  -3.750  -0.0972   0.01228   0.00535  -0.0616   0.6839   0.0113
  -3.500  -0.0701   0.01178   0.00473  -0.0614   0.6773   0.0115
  -3.250  -0.0434   0.01103   0.00386  -0.0612   0.6713   0.0121
  -3.000  -0.0162   0.01055   0.00330  -0.0611   0.6649   0.0129
  -2.750   0.0112   0.01025   0.00293  -0.0610   0.6592   0.0140
  -2.500   0.0390   0.00997   0.00257  -0.0610   0.6532   0.0145
  -2.250   0.0667   0.00976   0.00227  -0.0609   0.6475   0.0149
  -2.000   0.0946   0.00957   0.00202  -0.0608   0.6422   0.0157
  -1.750   0.1226   0.00942   0.00180  -0.0608   0.6367   0.0170
  -1.500   0.1505   0.00929   0.00162  -0.0607   0.6315   0.0221
  -1.250   0.1782   0.00902   0.00149  -0.0607   0.6261   0.0599
  -1.000   0.2056   0.00871   0.00140  -0.0608   0.6209   0.1281
  -0.750   0.2328   0.00837   0.00134  -0.0608   0.6160   0.2231
  -0.500   0.2601   0.00809   0.00130  -0.0609   0.6106   0.3088
  -0.250   0.2861   0.00756   0.00131  -0.0609   0.6057   0.4869
   0.000   0.3106   0.00701   0.00134  -0.0603   0.6010   0.6730
   0.250   0.3337   0.00662   0.00137  -0.0591   0.5958   0.8072
   0.500   0.3656   0.00636   0.00137  -0.0594   0.5907   0.9527
   0.750   0.4061   0.00637   0.00134  -0.0622   0.5854   1.0000
   1.000   0.4335   0.00643   0.00135  -0.0620   0.5798   1.0000
   1.250   0.4607   0.00650   0.00136  -0.0619   0.5748   1.0000
   1.500   0.4883   0.00656   0.00140  -0.0618   0.5690   1.0000
   1.750   0.5156   0.00664   0.00143  -0.0617   0.5630   1.0000
   2.000   0.5431   0.00670   0.00148  -0.0616   0.5559   1.0000
   2.250   0.5704   0.00680   0.00152  -0.0615   0.5481   1.0000
   2.500   0.5979   0.00687   0.00158  -0.0614   0.5396   1.0000
   2.750   0.6252   0.00696   0.00164  -0.0613   0.5305   1.0000
   3.000   0.6524   0.00707   0.00173  -0.0612   0.5206   1.0000
   3.250   0.6798   0.00716   0.00181  -0.0611   0.5106   1.0000
   3.500   0.7070   0.00727   0.00191  -0.0610   0.5007   1.0000
   3.750   0.7341   0.00740   0.00202  -0.0609   0.4891   1.0000
   4.000   0.7611   0.00754   0.00215  -0.0607   0.4754   1.0000
   4.250   0.7880   0.00770   0.00228  -0.0606   0.4597   1.0000
   4.500   0.8146   0.00788   0.00243  -0.0604   0.4408   1.0000
   4.750   0.8396   0.00824   0.00262  -0.0601   0.3987   1.0000
   5.000   0.8599   0.00922   0.00309  -0.0593   0.2919   1.0000
   5.250   0.8795   0.01034   0.00370  -0.0585   0.1949   1.0000
   5.500   0.9016   0.01112   0.00419  -0.0579   0.1385   1.0000
   5.750   0.9247   0.01173   0.00463  -0.0574   0.1021   1.0000
   6.000   0.9462   0.01253   0.00518  -0.0568   0.0588   1.0000
   6.250   0.9683   0.01323   0.00576  -0.0561   0.0298   1.0000
   6.500   0.9895   0.01403   0.00642  -0.0553   0.0098   1.0000
   6.750   1.0132   0.01449   0.00693  -0.0548   0.0078   1.0000
   7.000   1.0366   0.01496   0.00746  -0.0542   0.0072   1.0000
   7.250   1.0595   0.01548   0.00805  -0.0536   0.0066   1.0000
   7.500   1.0817   0.01604   0.00869  -0.0529   0.0062   1.0000
   7.750   1.1026   0.01673   0.00948  -0.0520   0.0058   1.0000
   8.000   1.1217   0.01758   0.01043  -0.0509   0.0054   1.0000
   8.250   1.1391   0.01855   0.01151  -0.0496   0.0052   1.0000
   8.500   1.1540   0.01968   0.01274  -0.0479   0.0050   1.0000
   8.750   1.1703   0.02060   0.01375  -0.0465   0.0049   1.0000
   9.000   1.1847   0.02161   0.01486  -0.0449   0.0049   1.0000
   9.250   1.1977   0.02268   0.01601  -0.0431   0.0048   1.0000
   9.500   1.2098   0.02362   0.01704  -0.0412   0.0047   1.0000
   9.750   1.2186   0.02466   0.01820  -0.0388   0.0046   1.0000
  10.000   1.2275   0.02574   0.01937  -0.0367   0.0044   1.0000
  10.250   1.2352   0.02699   0.02072  -0.0347   0.0043   1.0000
  10.500   1.2426   0.02835   0.02219  -0.0329   0.0041   1.0000
  10.750   1.2491   0.02991   0.02386  -0.0313   0.0041   1.0000
  11.000   1.2551   0.03163   0.02571  -0.0298   0.0040   1.0000
  11.250   1.2608   0.03344   0.02764  -0.0285   0.0039   1.0000
  11.500   1.2658   0.03541   0.02974  -0.0273   0.0039   1.0000
  11.750   1.2701   0.03752   0.03200  -0.0263   0.0038   1.0000
  12.000   1.2741   0.03971   0.03432  -0.0255   0.0037   1.0000
  12.250   1.2763   0.04216   0.03693  -0.0248   0.0037   1.0000
  12.500   1.2776   0.04478   0.03971  -0.0243   0.0036   1.0000
  12.750   1.2769   0.04774   0.04284  -0.0240   0.0036   1.0000
  13.000   1.2756   0.05079   0.04604  -0.0240   0.0035   1.0000
  13.250   1.2732   0.05404   0.04945  -0.0243   0.0034   1.0000
  13.500   1.2677   0.05791   0.05351  -0.0247   0.0035   1.0000
  13.750   1.2619   0.06187   0.05761  -0.0256   0.0034   1.0000
  14.000   1.2532   0.06644   0.06238  -0.0267   0.0034   1.0000
  14.250   1.2442   0.07128   0.06738  -0.0284   0.0033   1.0000
  14.500   1.2348   0.07641   0.07267  -0.0304   0.0033   1.0000
  14.750   1.2232   0.08226   0.07869  -0.0330   0.0033   1.0000
  15.000   1.2103   0.08871   0.08532  -0.0361   0.0033   1.0000
  15.250   1.1965   0.09568   0.09245  -0.0397   0.0033   1.0000
  15.500   1.1791   0.10390   0.10087  -0.0442   0.0033   1.0000
  15.750   1.1637   0.11214   0.10927  -0.0489   0.0033   1.0000
  16.000   1.1457   0.12149   0.11879  -0.0545   0.0033   1.0000
  16.250   1.1262   0.13185   0.12932  -0.0607   0.0034   1.0000
  16.500   1.1022   0.14434   0.14199  -0.0682   0.0035   1.0000
  16.750   1.0701   0.16062   0.15845  -0.0776   0.0036   1.0000
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