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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 100,000
Max Cl/Cd: 61.39 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e174-il-100000.txt
Download as CSV file: xf-e174-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E174  (Dicke 8.92%)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3385   0.09758   0.09291  -0.0306   1.0000   0.0787
  -8.000  -0.3479   0.09620   0.09167  -0.0343   1.0000   0.0799
  -7.750  -0.3606   0.09473   0.09035  -0.0398   1.0000   0.0805
  -7.500  -0.3311   0.08834   0.08390  -0.0324   1.0000   0.0847
  -7.250  -0.3298   0.08590   0.08155  -0.0320   1.0000   0.0888
  -7.000  -0.3357   0.08378   0.07955  -0.0327   1.0000   0.0912
  -6.750  -0.3495   0.08221   0.07815  -0.0374   1.0000   0.0936
  -6.500  -0.3693   0.08134   0.07739  -0.0383   1.0000   0.0941
  -6.250  -0.3894   0.08070   0.07679  -0.0377   1.0000   0.0944
  -6.000  -0.3906   0.07700   0.07322  -0.0341   0.9986   0.0958
  -5.750  -0.3646   0.07330   0.06954  -0.0332   0.9930   0.1008
  -5.500  -0.3227   0.06653   0.06257  -0.0488   0.9822   0.1108
  -5.250  -0.2803   0.06115   0.05694  -0.0609   0.9725   0.1239
  -5.000  -0.2556   0.05768   0.05357  -0.0604   0.9644   0.1291
  -4.750  -0.2140   0.05289   0.04862  -0.0685   0.9577   0.1434
  -4.500  -0.1808   0.04905   0.04463  -0.0736   0.9475   0.1586
  -4.000  -0.0750   0.03192   0.02523  -0.0901   0.9329   0.0656
  -3.750  -0.0325   0.02818   0.02099  -0.0935   0.9278   0.0630
  -3.500   0.0017   0.02583   0.01809  -0.0946   0.9183   0.0640
  -3.250   0.0412   0.02346   0.01523  -0.0963   0.9118   0.0638
  -3.000   0.0757   0.02179   0.01317  -0.0969   0.9031   0.0660
  -2.750   0.1084   0.02020   0.01153  -0.0975   0.8952   0.0726
  -2.500   0.1409   0.01903   0.01035  -0.0979   0.8872   0.0919
  -2.250   0.1675   0.01762   0.00932  -0.0975   0.8780   0.1671
  -2.000   0.1932   0.01565   0.00885  -0.0973   0.8712   0.4755
  -1.750   0.2363   0.01419   0.00849  -0.0979   0.8645   1.0000
  -1.500   0.2660   0.01427   0.00818  -0.0980   0.8566   1.0000
  -1.250   0.2905   0.01452   0.00814  -0.0975   0.8465   1.0000
  -1.000   0.3179   0.01468   0.00804  -0.0972   0.8386   1.0000
  -0.750   0.3437   0.01490   0.00802  -0.0968   0.8297   1.0000
  -0.500   0.3692   0.01516   0.00809  -0.0964   0.8212   1.0000
  -0.250   0.3963   0.01534   0.00808  -0.0961   0.8138   1.0000
   0.000   0.4210   0.01568   0.00829  -0.0957   0.8050   1.0000
   0.250   0.4485   0.01585   0.00829  -0.0953   0.7985   1.0000
   0.500   0.4727   0.01624   0.00859  -0.0949   0.7895   1.0000
   0.750   0.5004   0.01641   0.00863  -0.0946   0.7835   1.0000
   1.000   0.5243   0.01685   0.00903  -0.0942   0.7744   1.0000
   1.250   0.5521   0.01702   0.00909  -0.0938   0.7687   1.0000
   1.500   0.5757   0.01752   0.00957  -0.0935   0.7596   1.0000
   1.750   0.6036   0.01769   0.00966  -0.0931   0.7540   1.0000
   2.000   0.6269   0.01823   0.01022  -0.0928   0.7448   1.0000
   2.250   0.6549   0.01840   0.01033  -0.0923   0.7393   1.0000
   2.500   0.6779   0.01897   0.01094  -0.0920   0.7299   1.0000
   2.750   0.7051   0.01920   0.01114  -0.0916   0.7238   1.0000
   3.000   0.7288   0.01970   0.01172  -0.0912   0.7148   1.0000
   3.250   0.7546   0.02004   0.01207  -0.0907   0.7075   1.0000
   3.500   0.7800   0.02037   0.01244  -0.0902   0.6991   1.0000
   3.750   0.8042   0.02080   0.01293  -0.0896   0.6902   1.0000
   4.000   0.8319   0.02086   0.01304  -0.0889   0.6828   1.0000
   4.250   0.8552   0.02130   0.01358  -0.0882   0.6722   1.0000
   4.500   0.8810   0.02148   0.01382  -0.0875   0.6630   1.0000
   4.750   0.9085   0.02144   0.01383  -0.0867   0.6539   1.0000
   5.000   0.9324   0.02169   0.01422  -0.0858   0.6422   1.0000
   5.250   0.9576   0.02178   0.01442  -0.0848   0.6308   1.0000
   5.500   0.9840   0.02169   0.01441  -0.0838   0.6192   1.0000
   5.750   1.0112   0.02146   0.01426  -0.0828   0.6072   1.0000
   6.000   1.0376   0.02123   0.01415  -0.0816   0.5934   1.0000
   6.250   1.0625   0.02105   0.01410  -0.0804   0.5777   1.0000
   6.500   1.0871   0.02080   0.01401  -0.0790   0.5602   1.0000
   6.750   1.1126   0.02037   0.01371  -0.0776   0.5410   1.0000
   7.000   1.1359   0.01991   0.01337  -0.0759   0.5161   1.0000
   7.250   1.1572   0.01927   0.01276  -0.0736   0.4798   1.0000
   7.500   1.1737   0.01912   0.01257  -0.0711   0.4250   1.0000
   7.750   1.1845   0.01973   0.01283  -0.0682   0.3404   1.0000
   8.000   1.1876   0.02145   0.01393  -0.0650   0.2445   1.0000
   8.250   1.1840   0.02400   0.01578  -0.0614   0.1533   1.0000
   8.500   1.1721   0.02730   0.01839  -0.0568   0.0886   1.0000
   8.750   1.1681   0.02968   0.02057  -0.0530   0.0705   1.0000
   9.000   1.1700   0.03169   0.02258  -0.0498   0.0618   1.0000
   9.250   1.1749   0.03387   0.02465  -0.0473   0.0564   1.0000
   9.500   1.1881   0.03555   0.02647  -0.0455   0.0511   1.0000
   9.750   1.2069   0.03781   0.02861  -0.0445   0.0469   1.0000
  10.000   1.2444   0.04075   0.03169  -0.0450   0.0447   1.0000
  10.250   1.2756   0.04385   0.03514  -0.0452   0.0434   1.0000
  10.500   1.2974   0.04724   0.03889  -0.0444   0.0429   1.0000
  10.750   1.3109   0.05086   0.04292  -0.0430   0.0428   1.0000
  11.000   1.3160   0.05438   0.04684  -0.0410   0.0426   1.0000
  11.250   1.3134   0.05765   0.05048  -0.0384   0.0423   1.0000
  11.500   1.3061   0.06096   0.05412  -0.0358   0.0421   1.0000
  11.750   1.2951   0.06451   0.05798  -0.0336   0.0422   1.0000
  12.000   1.2808   0.06835   0.06212  -0.0320   0.0422   1.0000
  12.250   1.2641   0.07258   0.06663  -0.0311   0.0424   1.0000
  12.500   1.2456   0.07727   0.07158  -0.0310   0.0428   1.0000
  12.750   1.2255   0.08243   0.07697  -0.0317   0.0431   1.0000
  13.000   1.2043   0.08813   0.08289  -0.0333   0.0435   1.0000
  13.250   1.1830   0.09437   0.08931  -0.0356   0.0440   1.0000
  13.500   1.1611   0.10114   0.09625  -0.0387   0.0445   1.0000
  13.750   1.1412   0.10833   0.10357  -0.0422   0.0451   1.0000
  14.000   1.1237   0.11590   0.11122  -0.0459   0.0456   1.0000
  14.250   1.1119   0.12295   0.11840  -0.0494   0.0464   1.0000
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