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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 500,000
Max Cl/Cd: 114.15 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e193-il-500000.txt
Download as CSV file: xf-e193-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3526   0.08667   0.08449  -0.0382   1.0000   0.0216
  -8.500  -0.3559   0.08278   0.08065  -0.0400   1.0000   0.0226
  -8.000  -0.3738   0.07554   0.07353  -0.0426   1.0000   0.0233
  -7.750  -0.3727   0.07038   0.06842  -0.0484   0.9965   0.0234
  -7.500  -0.3561   0.05440   0.05225  -0.0701   0.9851   0.0239
  -7.250  -0.3368   0.05080   0.04861  -0.0744   0.9761   0.0245
  -7.000  -0.3124   0.04712   0.04483  -0.0791   0.9651   0.0252
  -6.750  -0.2876   0.04284   0.04040  -0.0838   0.9503   0.0261
  -6.500  -0.2640   0.03788   0.03514  -0.0877   0.9306   0.0280
  -6.250  -0.2396   0.03549   0.03208  -0.0884   0.9047   0.0308
  -6.000  -0.2342   0.02869   0.02492  -0.0887   0.8805   0.0324
  -5.750  -0.2232   0.01954   0.01438  -0.0854   0.8600   0.0181
  -4.750  -0.1282   0.01402   0.00776  -0.0822   0.7980   0.0178
  -4.500  -0.1043   0.01272   0.00627  -0.0814   0.7854   0.0185
  -4.250  -0.0795   0.01192   0.00536  -0.0808   0.7739   0.0191
  -4.000  -0.0541   0.01133   0.00466  -0.0803   0.7633   0.0195
  -3.750  -0.0283   0.01088   0.00410  -0.0798   0.7533   0.0204
  -3.500  -0.0019   0.01049   0.00363  -0.0795   0.7435   0.0217
  -3.250   0.0247   0.01020   0.00323  -0.0791   0.7350   0.0232
  -3.000   0.0513   0.00983   0.00279  -0.0787   0.7263   0.0273
  -2.750   0.0776   0.00937   0.00244  -0.0784   0.7185   0.0615
  -2.500   0.1036   0.00899   0.00226  -0.0782   0.7108   0.1253
  -2.250   0.1302   0.00872   0.00214  -0.0781   0.7035   0.1813
  -2.000   0.1566   0.00846   0.00205  -0.0779   0.6963   0.2454
  -1.750   0.1827   0.00815   0.00198  -0.0778   0.6898   0.3341
  -1.500   0.2082   0.00778   0.00195  -0.0775   0.6830   0.4462
  -1.250   0.2334   0.00749   0.00192  -0.0770   0.6770   0.5482
  -1.000   0.2583   0.00719   0.00192  -0.0764   0.6705   0.6484
  -0.750   0.2797   0.00680   0.00195  -0.0748   0.6649   0.7904
  -0.500   0.3127   0.00654   0.00201  -0.0752   0.6589   0.9383
  -0.250   0.3610   0.00658   0.00197  -0.0794   0.6528   0.9819
   0.000   0.4126   0.00662   0.00190  -0.0846   0.6471   0.9989
   0.250   0.4401   0.00666   0.00189  -0.0846   0.6409   1.0000
   0.500   0.4652   0.00675   0.00189  -0.0841   0.6356   1.0000
   0.750   0.4906   0.00681   0.00191  -0.0836   0.6301   1.0000
   1.000   0.5160   0.00688   0.00193  -0.0831   0.6243   1.0000
   1.250   0.5415   0.00699   0.00196  -0.0826   0.6193   1.0000
   1.500   0.5672   0.00704   0.00201  -0.0821   0.6135   1.0000
   1.750   0.5928   0.00713   0.00205  -0.0816   0.6080   1.0000
   2.000   0.6185   0.00723   0.00212  -0.0812   0.6026   1.0000
   2.250   0.6443   0.00729   0.00218  -0.0808   0.5963   1.0000
   2.500   0.6701   0.00741   0.00224  -0.0803   0.5904   1.0000
   2.750   0.6960   0.00747   0.00232  -0.0799   0.5835   1.0000
   3.000   0.7218   0.00757   0.00238  -0.0795   0.5768   1.0000
   3.250   0.7478   0.00764   0.00248  -0.0791   0.5694   1.0000
   3.500   0.7737   0.00774   0.00255  -0.0787   0.5623   1.0000
   3.750   0.7997   0.00781   0.00264  -0.0784   0.5542   1.0000
   4.250   0.8516   0.00800   0.00285  -0.0776   0.5376   1.0000
   4.500   0.8775   0.00811   0.00296  -0.0772   0.5291   1.0000
   4.750   0.9033   0.00822   0.00308  -0.0768   0.5195   1.0000
   5.000   0.9291   0.00832   0.00322  -0.0765   0.5092   1.0000
   5.250   0.9547   0.00845   0.00336  -0.0760   0.4982   1.0000
   5.500   0.9794   0.00858   0.00348  -0.0754   0.4797   1.0000
   5.750   1.0032   0.00879   0.00363  -0.0747   0.4549   1.0000
   6.000   1.0267   0.00904   0.00383  -0.0740   0.4304   1.0000
   6.250   1.0495   0.00937   0.00407  -0.0732   0.3982   1.0000
   6.500   1.0685   0.00999   0.00443  -0.0718   0.3416   1.0000
   6.750   1.0844   0.01089   0.00498  -0.0700   0.2737   1.0000
   7.000   1.1003   0.01181   0.00561  -0.0683   0.2151   1.0000
   7.250   1.1155   0.01278   0.00627  -0.0666   0.1611   1.0000
   7.500   1.1317   0.01363   0.00691  -0.0649   0.1203   1.0000
   7.750   1.1458   0.01460   0.00763  -0.0630   0.0784   1.0000
   8.000   1.1548   0.01591   0.00861  -0.0603   0.0325   1.0000
   8.250   1.1673   0.01690   0.00953  -0.0580   0.0187   1.0000
   8.500   1.1826   0.01764   0.01031  -0.0561   0.0160   1.0000
   8.750   1.1980   0.01830   0.01103  -0.0542   0.0147   1.0000
   9.000   1.2094   0.01905   0.01184  -0.0517   0.0138   1.0000
   9.250   1.2174   0.01996   0.01282  -0.0487   0.0130   1.0000
   9.500   1.2219   0.02110   0.01406  -0.0455   0.0125   1.0000
   9.750   1.2271   0.02227   0.01533  -0.0426   0.0123   1.0000
  10.000   1.2345   0.02337   0.01652  -0.0403   0.0120   1.0000
  10.250   1.2409   0.02461   0.01786  -0.0380   0.0118   1.0000
  10.500   1.2456   0.02606   0.01940  -0.0358   0.0116   1.0000
  10.750   1.2503   0.02762   0.02105  -0.0339   0.0113   1.0000
  11.000   1.2552   0.02927   0.02279  -0.0322   0.0111   1.0000
  11.250   1.2592   0.03110   0.02472  -0.0306   0.0109   1.0000
  11.500   1.2635   0.03299   0.02670  -0.0291   0.0108   1.0000
  11.750   1.2686   0.03491   0.02873  -0.0278   0.0109   1.0000
  12.000   1.2737   0.03687   0.03079  -0.0266   0.0105   1.0000
  12.250   1.2802   0.03872   0.03272  -0.0257   0.0103   1.0000
  12.500   1.2854   0.04083   0.03492  -0.0247   0.0101   1.0000
  12.750   1.2909   0.04285   0.03701  -0.0240   0.0099   1.0000
  13.000   1.2962   0.04512   0.03940  -0.0230   0.0098   1.0000
  13.250   1.3010   0.04742   0.04180  -0.0223   0.0097   1.0000
  13.500   1.3056   0.04986   0.04438  -0.0215   0.0097   1.0000
  13.750   1.3090   0.05252   0.04717  -0.0209   0.0096   1.0000
  14.000   1.3108   0.05539   0.05021  -0.0204   0.0096   1.0000
  14.250   1.3107   0.05857   0.05356  -0.0202   0.0096   1.0000
  14.500   1.3087   0.06202   0.05717  -0.0201   0.0095   1.0000
  14.750   1.3047   0.06577   0.06109  -0.0203   0.0095   1.0000
  15.000   1.2973   0.07009   0.06563  -0.0209   0.0095   1.0000
  15.250   1.2881   0.07478   0.07053  -0.0220   0.0096   1.0000
  15.500   1.2738   0.08059   0.07663  -0.0234   0.0099   1.0000
  15.750   1.2460   0.08897   0.08537  -0.0265   0.0102   1.0000
  16.000   1.2206   0.09741   0.09410  -0.0303   0.0104   1.0000
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