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EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EH 0.0/9.0 (eh0009-il)
Reynolds number: 1,000,000
Max Cl/Cd: 66.65 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh0009-il-1000000.txt
Download as CSV file: xf-eh0009-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 0.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7961   0.08105   0.07938  -0.0025   1.0000   0.0039
 -11.750  -0.8353   0.06628   0.06448  -0.0127   1.0000   0.0037
 -11.500  -0.8551   0.05728   0.05535  -0.0202   1.0000   0.0037
 -11.250  -0.8754   0.05023   0.04814  -0.0258   1.0000   0.0036
 -11.000  -0.8976   0.04479   0.04251  -0.0284   1.0000   0.0037
 -10.750  -0.9222   0.04054   0.03807  -0.0279   1.0000   0.0036
 -10.500  -0.9444   0.03732   0.03464  -0.0244   1.0000   0.0036
 -10.250  -0.9585   0.03375   0.03078  -0.0211   1.0000   0.0035
 -10.000  -0.9633   0.03017   0.02685  -0.0184   1.0000   0.0035
  -9.750  -0.9615   0.02690   0.02323  -0.0160   1.0000   0.0035
  -9.500  -0.9528   0.02429   0.02031  -0.0140   1.0000   0.0035
  -9.250  -0.9404   0.02205   0.01781  -0.0123   1.0000   0.0035
  -9.000  -0.9237   0.02044   0.01599  -0.0109   1.0000   0.0037
  -8.750  -0.9052   0.01911   0.01448  -0.0097   1.0000   0.0037
  -8.500  -0.8853   0.01800   0.01320  -0.0086   1.0000   0.0038
  -8.250  -0.8750   0.01522   0.01009  -0.0061   1.0000   0.0045
  -8.000  -0.8528   0.01457   0.00938  -0.0053   1.0000   0.0049
  -7.750  -0.8296   0.01406   0.00884  -0.0046   1.0000   0.0055
  -7.500  -0.8069   0.01350   0.00821  -0.0038   1.0000   0.0060
  -7.250  -0.7838   0.01300   0.00765  -0.0029   1.0000   0.0065
  -7.000  -0.7599   0.01268   0.00729  -0.0023   1.0000   0.0068
  -6.750  -0.7422   0.01144   0.00589  -0.0005   1.0000   0.0085
  -6.500  -0.7190   0.01110   0.00554   0.0004   1.0000   0.0096
  -6.250  -0.6957   0.01080   0.00520   0.0012   1.0000   0.0108
  -6.000  -0.6719   0.01062   0.00501   0.0019   1.0000   0.0115
  -5.750  -0.6519   0.00986   0.00416   0.0035   1.0000   0.0152
  -5.500  -0.6294   0.00957   0.00386   0.0045   1.0000   0.0185
  -5.250  -0.6081   0.00916   0.00343   0.0058   1.0000   0.0248
  -5.000  -0.5862   0.00880   0.00312   0.0069   0.9999   0.0356
  -4.750  -0.5516   0.00836   0.00279   0.0052   0.9975   0.0623
  -4.500  -0.5164   0.00795   0.00253   0.0033   0.9949   0.0942
  -4.250  -0.4827   0.00751   0.00229   0.0017   0.9918   0.1370
  -4.000  -0.4493   0.00709   0.00207   0.0003   0.9879   0.1865
  -3.750  -0.4142   0.00673   0.00188  -0.0015   0.9846   0.2311
  -3.500  -0.3793   0.00635   0.00170  -0.0033   0.9811   0.2850
  -3.250  -0.3488   0.00609   0.00156  -0.0040   0.9732   0.3232
  -3.000  -0.3175   0.00579   0.00143  -0.0048   0.9654   0.3728
  -2.750  -0.2879   0.00556   0.00132  -0.0052   0.9549   0.4122
  -2.500  -0.2611   0.00536   0.00121  -0.0049   0.9412   0.4505
  -2.250  -0.2353   0.00517   0.00113  -0.0044   0.9261   0.4909
  -2.000  -0.2096   0.00504   0.00105  -0.0038   0.9099   0.5244
  -1.500  -0.1578   0.00482   0.00093  -0.0027   0.8759   0.5880
  -1.250  -0.1319   0.00474   0.00088  -0.0022   0.8576   0.6184
  -1.000  -0.1056   0.00467   0.00084  -0.0017   0.8379   0.6473
  -0.750  -0.0793   0.00462   0.00081  -0.0013   0.8178   0.6748
  -0.500  -0.0529   0.00458   0.00079  -0.0009   0.7970   0.7018
   0.000   0.0000   0.00454   0.00077   0.0000   0.7527   0.7528
   0.500   0.0528   0.00458   0.00079   0.0009   0.7018   0.7969
   0.750   0.0792   0.00462   0.00081   0.0013   0.6745   0.8178
   1.000   0.1055   0.00467   0.00084   0.0018   0.6474   0.8379
   1.250   0.1318   0.00474   0.00088   0.0022   0.6184   0.8576
   1.500   0.1578   0.00482   0.00093   0.0027   0.5878   0.8758
   1.750   0.1836   0.00493   0.00099   0.0033   0.5550   0.8934
   2.000   0.2095   0.00504   0.00105   0.0038   0.5242   0.9100
   2.250   0.2352   0.00517   0.00113   0.0044   0.4907   0.9261
   2.500   0.2610   0.00536   0.00121   0.0049   0.4503   0.9413
   2.750   0.2879   0.00556   0.00132   0.0052   0.4123   0.9550
   3.000   0.3175   0.00579   0.00143   0.0048   0.3737   0.9655
   3.250   0.3489   0.00609   0.00156   0.0039   0.3234   0.9733
   3.500   0.3793   0.00635   0.00170   0.0033   0.2855   0.9813
   3.750   0.4144   0.00673   0.00188   0.0015   0.2311   0.9846
   4.000   0.4495   0.00708   0.00207  -0.0003   0.1873   0.9879
   4.250   0.4829   0.00751   0.00228  -0.0018   0.1379   0.9919
   4.500   0.5167   0.00795   0.00253  -0.0034   0.0946   0.9950
   4.750   0.5519   0.00836   0.00279  -0.0052   0.0622   0.9977
   5.000   0.5865   0.00880   0.00312  -0.0070   0.0355   1.0000
   5.250   0.6077   0.00916   0.00343  -0.0057   0.0248   1.0000
   5.500   0.6290   0.00957   0.00386  -0.0044   0.0185   1.0000
   5.750   0.6514   0.00986   0.00415  -0.0034   0.0152   1.0000
   6.000   0.6714   0.01062   0.00501  -0.0019   0.0115   1.0000
   6.250   0.6952   0.01080   0.00520  -0.0011   0.0108   1.0000
   6.500   0.7185   0.01112   0.00557  -0.0003   0.0097   1.0000
   6.750   0.7418   0.01145   0.00590   0.0005   0.0085   1.0000
   7.000   0.7596   0.01271   0.00733   0.0023   0.0068   1.0000
   7.250   0.7836   0.01303   0.00768   0.0030   0.0065   1.0000
   7.500   0.8070   0.01348   0.00818   0.0037   0.0060   1.0000
   7.750   0.8298   0.01404   0.00881   0.0045   0.0054   1.0000
   8.000   0.8524   0.01466   0.00950   0.0053   0.0050   1.0000
   8.250   0.8751   0.01526   0.01013   0.0061   0.0046   1.0000
   8.500   0.8846   0.01820   0.01342   0.0087   0.0038   1.0000
   8.750   0.9052   0.01918   0.01456   0.0097   0.0037   1.0000
   9.000   0.9245   0.02036   0.01590   0.0108   0.0036   1.0000
   9.250   0.9406   0.02209   0.01785   0.0122   0.0036   1.0000
   9.500   0.9533   0.02429   0.02031   0.0139   0.0035   1.0000
   9.750   0.9617   0.02696   0.02330   0.0159   0.0035   1.0000
  10.000   0.9637   0.03022   0.02691   0.0183   0.0035   1.0000
  10.250   0.9602   0.03362   0.03063   0.0209   0.0035   1.0000
  10.500   0.9436   0.03749   0.03482   0.0244   0.0036   1.0000
  10.750   0.9236   0.04051   0.03803   0.0277   0.0036   1.0000
  11.000   0.9012   0.04453   0.04225   0.0283   0.0036   1.0000
  11.250   0.8792   0.04980   0.04769   0.0259   0.0037   1.0000
  11.500   0.8586   0.05683   0.05488   0.0204   0.0037   1.0000
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