Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E193 (10.22%) (e193-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 200,000
Max Cl/Cd: 80.33 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e193-il-200000-n5.txt
Download as CSV file: xf-e193-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E193  (10.22%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3667   0.08710   0.08360  -0.0403   1.0000   0.0173
  -8.750  -0.3649   0.08449   0.08104  -0.0405   1.0000   0.0170
  -8.500  -0.3669   0.08127   0.07788  -0.0411   1.0000   0.0167
  -8.250  -0.3716   0.07804   0.07472  -0.0416   1.0000   0.0165
  -8.000  -0.3806   0.07494   0.07171  -0.0417   1.0000   0.0162
  -7.750  -0.3869   0.07103   0.06788  -0.0440   0.9951   0.0159
  -7.500  -0.3707   0.06257   0.05938  -0.0565   0.9784   0.0155
  -7.250  -0.3556   0.05117   0.04777  -0.0701   0.9596   0.0148
  -7.000  -0.3502   0.03749   0.03338  -0.0790   0.9370   0.0141
  -6.750  -0.3294   0.03249   0.02785  -0.0818   0.9210   0.0144
  -6.500  -0.3054   0.02909   0.02397  -0.0834   0.9056   0.0152
  -6.250  -0.2815   0.02582   0.02011  -0.0841   0.8899   0.0156
  -6.000  -0.2572   0.02314   0.01689  -0.0842   0.8746   0.0157
  -5.750  -0.2322   0.02108   0.01436  -0.0839   0.8595   0.0158
  -5.500  -0.2070   0.01950   0.01239  -0.0835   0.8448   0.0160
  -5.250  -0.1818   0.01822   0.01081  -0.0830   0.8307   0.0163
  -5.000  -0.1566   0.01717   0.00952  -0.0824   0.8175   0.0166
  -4.750  -0.1314   0.01630   0.00844  -0.0818   0.8050   0.0171
  -4.500  -0.1062   0.01554   0.00752  -0.0813   0.7933   0.0176
  -4.250  -0.0813   0.01482   0.00667  -0.0807   0.7823   0.0186
  -4.000  -0.0556   0.01438   0.00614  -0.0804   0.7714   0.0205
  -3.750  -0.0296   0.01395   0.00556  -0.0799   0.7615   0.0225
  -3.500  -0.0038   0.01348   0.00497  -0.0795   0.7523   0.0245
  -3.250   0.0226   0.01312   0.00449  -0.0791   0.7430   0.0284
  -3.000   0.0486   0.01268   0.00406  -0.0787   0.7347   0.0429
  -2.750   0.0745   0.01227   0.00376  -0.0784   0.7262   0.0829
  -2.500   0.1003   0.01188   0.00355  -0.0782   0.7187   0.1398
  -2.250   0.1261   0.01154   0.00339  -0.0780   0.7109   0.2046
  -2.000   0.1517   0.01120   0.00327  -0.0778   0.7039   0.2809
  -1.750   0.1774   0.01091   0.00316  -0.0775   0.6967   0.3547
  -1.500   0.2025   0.01061   0.00308  -0.0770   0.6903   0.4403
  -1.250   0.2268   0.01028   0.00305  -0.0763   0.6833   0.5385
  -1.000   0.2502   0.00997   0.00302  -0.0752   0.6777   0.6422
  -0.750   0.2727   0.00964   0.00304  -0.0736   0.6710   0.7586
  -0.500   0.3109   0.00942   0.00303  -0.0750   0.6651   0.9002
  -0.250   0.3605   0.00941   0.00293  -0.0794   0.6590   0.9753
   0.000   0.4025   0.00944   0.00285  -0.0825   0.6525   1.0000
   0.250   0.4275   0.00954   0.00282  -0.0820   0.6473   1.0000
   0.500   0.4526   0.00962   0.00284  -0.0814   0.6410   1.0000
   0.750   0.4779   0.00973   0.00285  -0.0809   0.6354   1.0000
   1.000   0.5033   0.00983   0.00289  -0.0804   0.6299   1.0000
   1.250   0.5288   0.00993   0.00295  -0.0800   0.6240   1.0000
   1.500   0.5545   0.01006   0.00299  -0.0796   0.6190   1.0000
   1.750   0.5803   0.01016   0.00308  -0.0792   0.6130   1.0000
   2.000   0.6061   0.01028   0.00317  -0.0788   0.6074   1.0000
   2.250   0.6320   0.01041   0.00326  -0.0784   0.6023   1.0000
   2.500   0.6579   0.01053   0.00339  -0.0780   0.5961   1.0000
   2.750   0.6839   0.01066   0.00350  -0.0776   0.5905   1.0000
   3.000   0.7098   0.01080   0.00364  -0.0773   0.5844   1.0000
   3.250   0.7357   0.01092   0.00378  -0.0769   0.5776   1.0000
   3.500   0.7615   0.01106   0.00392  -0.0765   0.5707   1.0000
   3.750   0.7871   0.01119   0.00407  -0.0761   0.5627   1.0000
   4.000   0.8127   0.01132   0.00424  -0.0756   0.5544   1.0000
   4.250   0.8381   0.01145   0.00437  -0.0751   0.5457   1.0000
   4.500   0.8634   0.01158   0.00456  -0.0747   0.5356   1.0000
   4.750   0.8886   0.01173   0.00473  -0.0741   0.5251   1.0000
   5.000   0.9135   0.01188   0.00492  -0.0736   0.5141   1.0000
   5.250   0.9382   0.01204   0.00511  -0.0730   0.5020   1.0000
   5.500   0.9626   0.01220   0.00533  -0.0723   0.4884   1.0000
   5.750   0.9867   0.01239   0.00557  -0.0716   0.4734   1.0000
   6.000   1.0103   0.01261   0.00582  -0.0709   0.4558   1.0000
   6.250   1.0331   0.01286   0.00608  -0.0700   0.4329   1.0000
   6.500   1.0529   0.01325   0.00635  -0.0686   0.3936   1.0000
   6.750   1.0673   0.01399   0.00678  -0.0665   0.3283   1.0000
   7.000   1.0780   0.01510   0.00747  -0.0640   0.2558   1.0000
   7.250   1.0909   0.01612   0.00823  -0.0619   0.2045   1.0000
   7.500   1.1034   0.01717   0.00904  -0.0599   0.1596   1.0000
   7.750   1.1164   0.01816   0.00984  -0.0579   0.1232   1.0000
   8.000   1.1275   0.01923   0.01072  -0.0557   0.0887   1.0000
   8.250   1.1384   0.02027   0.01163  -0.0535   0.0618   1.0000
   8.500   1.1455   0.02146   0.01265  -0.0507   0.0375   1.0000
   8.750   1.1531   0.02249   0.01365  -0.0480   0.0254   1.0000
   9.000   1.1608   0.02355   0.01473  -0.0453   0.0196   1.0000
   9.500   1.1772   0.02577   0.01709  -0.0407   0.0157   1.0000
   9.750   1.1857   0.02693   0.01837  -0.0386   0.0149   1.0000
  10.000   1.1925   0.02827   0.01983  -0.0367   0.0141   1.0000
  10.250   1.1986   0.02972   0.02139  -0.0349   0.0136   1.0000
  10.500   1.2019   0.03150   0.02327  -0.0332   0.0130   1.0000
  10.750   1.2057   0.03331   0.02519  -0.0317   0.0126   1.0000
  11.000   1.2104   0.03514   0.02715  -0.0304   0.0122   1.0000
  11.250   1.2156   0.03699   0.02912  -0.0293   0.0116   1.0000
  11.500   1.2200   0.03899   0.03124  -0.0284   0.0112   1.0000
  11.750   1.2226   0.04124   0.03360  -0.0275   0.0109   1.0000
  12.000   1.2254   0.04352   0.03602  -0.0267   0.0107   1.0000
  12.250   1.2278   0.04593   0.03854  -0.0260   0.0105   1.0000
  12.500   1.2301   0.04840   0.04112  -0.0255   0.0103   1.0000
  12.750   1.2321   0.05096   0.04378  -0.0250   0.0101   1.0000
  13.000   1.2338   0.05362   0.04656  -0.0246   0.0100   1.0000
  13.250   1.2352   0.05638   0.04942  -0.0243   0.0098   1.0000
  13.500   1.2369   0.05917   0.05233  -0.0240   0.0097   1.0000
  13.750   1.2378   0.06216   0.05543  -0.0237   0.0095   1.0000
  14.000   1.2386   0.06529   0.05870  -0.0235   0.0094   1.0000
  14.250   1.2399   0.06838   0.06193  -0.0235   0.0094   1.0000
  14.500   1.2390   0.07189   0.06562  -0.0238   0.0093   1.0000
  14.750   1.2372   0.07560   0.06954  -0.0243   0.0093   1.0000
  15.000   1.2335   0.07968   0.07382  -0.0252   0.0092   1.0000
  15.250   1.2278   0.08418   0.07853  -0.0265   0.0092   1.0000
  15.500   1.2215   0.08893   0.08348  -0.0280   0.0092   1.0000
  15.750   1.2128   0.09423   0.08899  -0.0300   0.0091   1.0000
  16.000   1.2023   0.10002   0.09499  -0.0325   0.0091   1.0000
  16.250   1.1913   0.10614   0.10132  -0.0354   0.0091   1.0000
  16.500   1.1784   0.11291   0.10830  -0.0389   0.0091   1.0000
  16.750   1.1655   0.11996   0.11554  -0.0428   0.0091   1.0000
  17.000   1.1528   0.12723   0.12299  -0.0470   0.0092   1.0000
  17.250   1.1386   0.13525   0.13118  -0.0518   0.0092   1.0000
  17.500   1.1230   0.14403   0.14014  -0.0574   0.0092   1.0000
  17.750   1.1083   0.15304   0.14930  -0.0631   0.0093   1.0000
  18.000   1.0925   0.16285   0.15925  -0.0694   0.0093   1.0000
<< Back to E193 (10.22%) (e193-il)

Polar data table (+)

Polar graphs


<< Back to E193 (10.22%) (e193-il)