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Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Eh 1.0/7.0 (eh1070-il)
Reynolds number: 100,000
Max Cl/Cd: 40.23 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1070-il-100000-n5.txt
Download as CSV file: xf-eh1070-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eh 1.0/7.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5953   0.10363   0.09891   0.0128   1.0000   0.0416
  -8.750  -0.6015   0.09953   0.09491   0.0069   1.0000   0.0448
  -8.500  -0.6086   0.09514   0.09060   0.0003   1.0000   0.0455
  -8.250  -0.5955   0.08910   0.08451   0.0050   1.0000   0.0289
  -8.000  -0.5988   0.08425   0.07974   0.0018   1.0000   0.0271
  -7.750  -0.6040   0.07916   0.07468  -0.0023   1.0000   0.0257
  -7.250  -0.5995   0.06673   0.06201  -0.0104   1.0000   0.0207
  -7.000  -0.5959   0.06194   0.05711  -0.0116   1.0000   0.0202
  -6.750  -0.5894   0.05721   0.05222  -0.0126   1.0000   0.0198
  -6.500  -0.5806   0.05246   0.04725  -0.0132   1.0000   0.0194
  -6.250  -0.5693   0.04785   0.04236  -0.0133   1.0000   0.0191
  -6.000  -0.5558   0.04340   0.03757  -0.0131   1.0000   0.0187
  -5.750  -0.5401   0.03914   0.03291  -0.0126   1.0000   0.0185
  -5.500  -0.5224   0.03519   0.02848  -0.0117   1.0000   0.0184
  -5.250  -0.5027   0.03166   0.02433  -0.0107   1.0000   0.0184
  -5.000  -0.4810   0.02844   0.02057  -0.0095   1.0000   0.0188
  -4.750  -0.4571   0.02617   0.01779  -0.0085   1.0000   0.0206
  -4.500  -0.4343   0.02370   0.01496  -0.0076   1.0000   0.0235
  -4.250  -0.4098   0.02168   0.01268  -0.0067   1.0000   0.0247
  -4.000  -0.3851   0.01995   0.01075  -0.0058   1.0000   0.0260
  -3.750  -0.3611   0.01850   0.00916  -0.0047   1.0000   0.0277
  -3.500  -0.3379   0.01729   0.00782  -0.0036   1.0000   0.0300
  -3.250  -0.3148   0.01629   0.00666  -0.0025   1.0000   0.0337
  -3.000  -0.2924   0.01532   0.00573  -0.0015   1.0000   0.0492
  -2.750  -0.2709   0.01416   0.00484  -0.0004   1.0000   0.1087
  -2.500  -0.2526   0.01265   0.00433   0.0007   1.0000   0.3031
  -2.250  -0.2407   0.01092   0.00423   0.0042   1.0000   0.6734
  -2.000  -0.2124   0.01068   0.00436   0.0062   1.0000   0.8593
  -1.750  -0.1624   0.01076   0.00425   0.0028   1.0000   0.9332
  -1.500  -0.0973   0.01083   0.00396  -0.0042   1.0000   0.9752
  -1.250  -0.0313   0.01072   0.00359  -0.0122   1.0000   1.0000
  -1.000  -0.0135   0.01064   0.00344  -0.0107   1.0000   1.0000
  -0.750   0.0028   0.01059   0.00335  -0.0090   1.0000   1.0000
  -0.500   0.0330   0.01058   0.00328  -0.0101   0.9827   1.0000
  -0.250   0.0763   0.01058   0.00317  -0.0136   0.9475   1.0000
   0.000   0.1178   0.01058   0.00307  -0.0165   0.9118   1.0000
   0.250   0.1524   0.01059   0.00299  -0.0177   0.8746   1.0000
   0.500   0.1796   0.01064   0.00293  -0.0173   0.8379   1.0000
   0.750   0.2034   0.01073   0.00291  -0.0162   0.8041   1.0000
   1.000   0.2262   0.01083   0.00290  -0.0149   0.7728   1.0000
   1.250   0.2489   0.01096   0.00292  -0.0137   0.7436   1.0000
   1.500   0.2719   0.01110   0.00297  -0.0125   0.7161   1.0000
   1.750   0.2950   0.01125   0.00305  -0.0114   0.6896   1.0000
   2.000   0.3185   0.01142   0.00321  -0.0104   0.6640   1.0000
   2.250   0.3422   0.01160   0.00334  -0.0094   0.6393   1.0000
   2.500   0.3659   0.01179   0.00349  -0.0084   0.6151   1.0000
   2.750   0.3896   0.01200   0.00367  -0.0075   0.5910   1.0000
   3.000   0.4134   0.01222   0.00388  -0.0066   0.5670   1.0000
   3.250   0.4375   0.01245   0.00413  -0.0058   0.5432   1.0000
   3.500   0.4617   0.01270   0.00449  -0.0050   0.5199   1.0000
   3.750   0.4858   0.01296   0.00479  -0.0041   0.4953   1.0000
   4.000   0.5099   0.01324   0.00512  -0.0033   0.4687   1.0000
   4.250   0.5340   0.01354   0.00548  -0.0025   0.4403   1.0000
   4.500   0.5580   0.01387   0.00587  -0.0017   0.4080   1.0000
   4.750   0.5786   0.01443   0.00608  -0.0005   0.3140   1.0000
   5.000   0.5958   0.01597   0.00662   0.0004   0.1352   1.0000
   5.250   0.6137   0.01802   0.00818   0.0015   0.0417   1.0000
   5.500   0.6351   0.01929   0.00955   0.0025   0.0293   1.0000
   5.750   0.6556   0.02066   0.01108   0.0036   0.0238   1.0000
   6.000   0.6762   0.02203   0.01267   0.0048   0.0217   1.0000
   6.250   0.6963   0.02361   0.01443   0.0061   0.0201   1.0000
   6.500   0.7170   0.02544   0.01641   0.0074   0.0190   1.0000
   6.750   0.7381   0.02755   0.01871   0.0085   0.0180   1.0000
   7.000   0.7571   0.03006   0.02140   0.0094   0.0161   1.0000
   7.250   0.7753   0.03283   0.02456   0.0104   0.0143   1.0000
   7.500   0.7937   0.03532   0.02750   0.0115   0.0134   1.0000
   7.750   0.8084   0.03856   0.03121   0.0127   0.0132   1.0000
   8.000   0.8194   0.04209   0.03523   0.0138   0.0131   1.0000
   8.250   0.8265   0.04588   0.03946   0.0148   0.0131   1.0000
   8.500   0.8292   0.04982   0.04391   0.0155   0.0131   1.0000
   8.750   0.8272   0.05384   0.04827   0.0160   0.0132   1.0000
   9.000   0.8200   0.05793   0.05264   0.0162   0.0133   1.0000
   9.250   0.8065   0.06183   0.05674   0.0161   0.0134   1.0000
   9.500   0.7908   0.06624   0.06127   0.0140   0.0135   1.0000
   9.750   0.7746   0.07213   0.06717   0.0093   0.0135   1.0000
  10.000   0.7611   0.07900   0.07411   0.0035   0.0137   1.0000
  10.250   0.7495   0.08674   0.08187  -0.0024   0.0139   1.0000
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