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E174 (Dicke 8.92%) (e174-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E174 (Dicke 8.92%) (e174-il)
Reynolds number: 200,000
Max Cl/Cd: 83 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e174-il-200000-n5.txt
Download as CSV file: xf-e174-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3347   0.08691   0.08359  -0.0328   1.0000   0.0235
  -7.750  -0.3331   0.08390   0.08064  -0.0338   1.0000   0.0237
  -7.500  -0.3333   0.08111   0.07792  -0.0343   1.0000   0.0240
  -7.250  -0.3343   0.07802   0.07492  -0.0357   0.9963   0.0240
  -7.000  -0.3122   0.06688   0.06373  -0.0525   0.9596   0.0168
  -6.750  -0.2896   0.06379   0.06058  -0.0564   0.9386   0.0155
  -6.250  -0.2436   0.05043   0.04690  -0.0736   0.8899   0.0157
  -6.000  -0.2244   0.04488   0.04110  -0.0781   0.8700   0.0154
  -5.750  -0.2054   0.03903   0.03490  -0.0814   0.8523   0.0154
  -5.500  -0.1857   0.03385   0.02929  -0.0833   0.8371   0.0149
  -5.250  -0.1645   0.02894   0.02382  -0.0844   0.8237   0.0143
  -5.000  -0.1414   0.02476   0.01898  -0.0848   0.8115   0.0139
  -4.750  -0.1167   0.02167   0.01524  -0.0847   0.7998   0.0136
  -4.500  -0.0909   0.01951   0.01256  -0.0844   0.7889   0.0136
  -4.250  -0.0646   0.01791   0.01056  -0.0840   0.7788   0.0138
  -4.000  -0.0382   0.01667   0.00901  -0.0836   0.7690   0.0142
  -3.750  -0.0116   0.01564   0.00776  -0.0833   0.7595   0.0147
  -3.500   0.0151   0.01483   0.00674  -0.0829   0.7509   0.0156
  -3.250   0.0417   0.01416   0.00594  -0.0827   0.7421   0.0174
  -3.000   0.0686   0.01363   0.00532  -0.0825   0.7341   0.0191
  -2.750   0.0958   0.01315   0.00469  -0.0822   0.7262   0.0207
  -2.500   0.1233   0.01272   0.00413  -0.0821   0.7186   0.0232
  -2.250   0.1507   0.01233   0.00367  -0.0819   0.7114   0.0317
  -2.000   0.1779   0.01186   0.00336  -0.0819   0.7043   0.0780
  -1.750   0.2048   0.01145   0.00319  -0.0819   0.6974   0.1513
  -1.500   0.2314   0.01097   0.00307  -0.0820   0.6909   0.2662
  -1.250   0.2579   0.01059   0.00297  -0.0819   0.6843   0.3735
  -1.000   0.2832   0.01015   0.00293  -0.0815   0.6783   0.5132
  -0.750   0.3057   0.00963   0.00294  -0.0802   0.6719   0.6857
  -0.500   0.3275   0.00918   0.00289  -0.0780   0.6665   0.8739
  -0.250   0.3694   0.00909   0.00274  -0.0807   0.6599   1.0000
   0.000   0.3968   0.00918   0.00269  -0.0806   0.6540   1.0000
   0.250   0.4243   0.00928   0.00266  -0.0805   0.6484   1.0000
   0.500   0.4518   0.00937   0.00266  -0.0804   0.6422   1.0000
   0.750   0.4792   0.00948   0.00265  -0.0803   0.6371   1.0000
   1.000   0.5067   0.00958   0.00269  -0.0803   0.6309   1.0000
   1.250   0.5341   0.00969   0.00273  -0.0802   0.6253   1.0000
   1.500   0.5616   0.00981   0.00278  -0.0801   0.6199   1.0000
   1.750   0.5891   0.00992   0.00287  -0.0800   0.6137   1.0000
   2.000   0.6164   0.01005   0.00294  -0.0799   0.6085   1.0000
   2.250   0.6438   0.01016   0.00305  -0.0799   0.6023   1.0000
   2.500   0.6711   0.01029   0.00316  -0.0798   0.5964   1.0000
   2.750   0.6984   0.01042   0.00329  -0.0796   0.5904   1.0000
   3.000   0.7256   0.01055   0.00343  -0.0795   0.5835   1.0000
   3.250   0.7527   0.01069   0.00355  -0.0794   0.5768   1.0000
   3.500   0.7796   0.01081   0.00369  -0.0792   0.5683   1.0000
   3.750   0.8065   0.01094   0.00386  -0.0790   0.5596   1.0000
   4.000   0.8331   0.01107   0.00399  -0.0788   0.5506   1.0000
   4.250   0.8598   0.01120   0.00417  -0.0786   0.5401   1.0000
   4.500   0.8863   0.01134   0.00437  -0.0783   0.5297   1.0000
   4.750   0.9126   0.01149   0.00455  -0.0780   0.5186   1.0000
   5.000   0.9386   0.01165   0.00474  -0.0777   0.5059   1.0000
   5.250   0.9645   0.01182   0.00496  -0.0773   0.4916   1.0000
   5.500   0.9901   0.01201   0.00522  -0.0770   0.4755   1.0000
   5.750   1.0151   0.01223   0.00546  -0.0765   0.4546   1.0000
   6.000   1.0373   0.01260   0.00568  -0.0755   0.4091   1.0000
   6.250   1.0555   0.01336   0.00607  -0.0742   0.3327   1.0000
   6.500   1.0714   0.01448   0.00678  -0.0727   0.2554   1.0000
   6.750   1.0876   0.01563   0.00759  -0.0714   0.1917   1.0000
   7.000   1.1045   0.01671   0.00841  -0.0702   0.1432   1.0000
   7.250   1.1213   0.01776   0.00925  -0.0690   0.1025   1.0000
   7.500   1.1368   0.01891   0.01019  -0.0676   0.0645   1.0000
   7.750   1.1508   0.02015   0.01125  -0.0660   0.0344   1.0000
   8.000   1.1657   0.02125   0.01232  -0.0644   0.0216   1.0000
   8.250   1.1815   0.02221   0.01333  -0.0630   0.0178   1.0000
   8.500   1.1967   0.02317   0.01439  -0.0614   0.0162   1.0000
   8.750   1.2095   0.02427   0.01558  -0.0596   0.0151   1.0000
   9.000   1.2203   0.02534   0.01678  -0.0575   0.0145   1.0000
   9.250   1.2291   0.02646   0.01804  -0.0552   0.0140   1.0000
   9.500   1.2362   0.02772   0.01945  -0.0529   0.0137   1.0000
   9.750   1.2422   0.02914   0.02100  -0.0507   0.0133   1.0000
  10.000   1.2475   0.03070   0.02269  -0.0488   0.0131   1.0000
  10.250   1.2522   0.03244   0.02455  -0.0471   0.0128   1.0000
  10.500   1.2571   0.03427   0.02649  -0.0456   0.0123   1.0000
  10.750   1.2624   0.03614   0.02847  -0.0443   0.0121   1.0000
  11.000   1.2671   0.03816   0.03058  -0.0432   0.0116   1.0000
  11.250   1.2709   0.04036   0.03287  -0.0422   0.0112   1.0000
  11.500   1.2725   0.04296   0.03556  -0.0411   0.0107   1.0000
  11.750   1.2771   0.04539   0.03812  -0.0401   0.0106   1.0000
  12.000   1.2834   0.04766   0.04055  -0.0393   0.0105   1.0000
  12.250   1.2891   0.05006   0.04312  -0.0385   0.0104   1.0000
  12.500   1.2940   0.05263   0.04587  -0.0379   0.0103   1.0000
  12.750   1.2976   0.05539   0.04883  -0.0374   0.0102   1.0000
  13.000   1.2992   0.05848   0.05214  -0.0370   0.0100   1.0000
  13.250   1.2987   0.06185   0.05573  -0.0369   0.0099   1.0000
  13.500   1.2963   0.06553   0.05963  -0.0371   0.0099   1.0000
  13.750   1.2914   0.06959   0.06394  -0.0375   0.0098   1.0000
  14.000   1.2842   0.07408   0.06866  -0.0383   0.0098   1.0000
  14.250   1.2750   0.07900   0.07382  -0.0396   0.0098   1.0000
  14.500   1.2638   0.08438   0.07944  -0.0414   0.0097   1.0000
  14.750   1.2514   0.09022   0.08551  -0.0437   0.0098   1.0000
  15.000   1.2376   0.09661   0.09213  -0.0466   0.0097   1.0000
  15.250   1.2224   0.10363   0.09937  -0.0501   0.0098   1.0000
  15.500   1.2069   0.11111   0.10705  -0.0542   0.0098   1.0000
  15.750   1.1905   0.11927   0.11541  -0.0590   0.0098   1.0000
  16.000   1.1736   0.12802   0.12435  -0.0644   0.0099   1.0000
  16.250   1.1559   0.13765   0.13415  -0.0706   0.0099   1.0000
  16.500   1.1378   0.14815   0.14480  -0.0774   0.0100   1.0000
  16.750   1.1182   0.15998   0.15676  -0.0851   0.0102   1.0000
  17.000   1.0964   0.17372   0.17059  -0.0935   0.0103   1.0000
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