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

EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.64 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2012-il-1000000-n5.txt
Download as CSV file: xf-eh2012-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/12                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.8667   0.10727   0.10521  -0.0017   1.0000   0.0054
 -15.500  -1.1059   0.05349   0.05078  -0.0374   1.0000   0.0048
 -15.250  -1.1356   0.04570   0.04277  -0.0424   1.0000   0.0048
 -15.000  -1.1534   0.04106   0.03797  -0.0438   1.0000   0.0048
 -14.750  -1.1660   0.03766   0.03441  -0.0436   1.0000   0.0047
 -14.500  -1.1679   0.03552   0.03217  -0.0427   1.0000   0.0048
 -14.250  -1.1743   0.03323   0.02975  -0.0410   1.0000   0.0049
 -14.000  -1.1749   0.03154   0.02794  -0.0390   1.0000   0.0049
 -13.750  -1.1747   0.02999   0.02627  -0.0367   1.0000   0.0050
 -13.500  -1.1723   0.02868   0.02485  -0.0341   1.0000   0.0050
 -13.250  -1.1672   0.02759   0.02366  -0.0315   1.0000   0.0052
 -13.000  -1.1636   0.02641   0.02237  -0.0284   1.0000   0.0052
 -12.750  -1.1536   0.02535   0.02120  -0.0263   1.0000   0.0052
 -12.500  -1.1395   0.02445   0.02020  -0.0247   1.0000   0.0054
 -12.250  -1.1261   0.02342   0.01905  -0.0229   1.0000   0.0054
 -12.000  -1.1108   0.02248   0.01800  -0.0214   1.0000   0.0055
 -11.750  -1.0934   0.02167   0.01709  -0.0200   1.0000   0.0056
 -11.500  -1.0753   0.02088   0.01621  -0.0188   1.0000   0.0057
 -11.250  -1.0564   0.02014   0.01538  -0.0176   1.0000   0.0057
 -11.000  -1.0366   0.01946   0.01462  -0.0165   1.0000   0.0058
 -10.750  -1.0183   0.01857   0.01363  -0.0152   1.0000   0.0059
 -10.500  -0.9990   0.01775   0.01272  -0.0139   1.0000   0.0060
 -10.250  -0.9786   0.01704   0.01193  -0.0129   1.0000   0.0063
 -10.000  -0.9572   0.01643   0.01126  -0.0119   1.0000   0.0064
  -9.750  -0.9353   0.01588   0.01066  -0.0109   1.0000   0.0066
  -9.500  -0.9131   0.01536   0.01010  -0.0100   1.0000   0.0068
  -9.250  -0.8807   0.01480   0.00948  -0.0113   0.9806   0.0070
  -9.000  -0.8437   0.01425   0.00886  -0.0135   0.9477   0.0073
  -8.750  -0.8188   0.01390   0.00834  -0.0129   0.9023   0.0075
  -8.500  -0.7971   0.01361   0.00788  -0.0116   0.8654   0.0078
  -8.250  -0.7741   0.01332   0.00745  -0.0106   0.8350   0.0080
  -8.000  -0.7503   0.01305   0.00705  -0.0098   0.8082   0.0082
  -7.750  -0.7267   0.01265   0.00653  -0.0090   0.7843   0.0089
  -7.500  -0.7022   0.01236   0.00615  -0.0084   0.7623   0.0095
  -7.250  -0.6773   0.01209   0.00579  -0.0078   0.7422   0.0101
  -7.000  -0.6519   0.01186   0.00546  -0.0073   0.7231   0.0109
  -6.750  -0.6265   0.01160   0.00512  -0.0068   0.7054   0.0117
  -6.500  -0.6011   0.01133   0.00479  -0.0063   0.6889   0.0130
  -6.250  -0.5753   0.01111   0.00450  -0.0059   0.6735   0.0142
  -6.000  -0.5493   0.01089   0.00421  -0.0055   0.6592   0.0158
  -5.750  -0.5234   0.01067   0.00395  -0.0051   0.6451   0.0181
  -5.500  -0.4970   0.01048   0.00371  -0.0048   0.6319   0.0204
  -5.250  -0.4709   0.01027   0.00348  -0.0044   0.6192   0.0238
  -5.000  -0.4444   0.01010   0.00326  -0.0041   0.6074   0.0273
  -4.750  -0.4180   0.00992   0.00306  -0.0038   0.5956   0.0323
  -4.500  -0.3915   0.00974   0.00288  -0.0035   0.5839   0.0379
  -4.250  -0.3646   0.00960   0.00271  -0.0033   0.5734   0.0430
  -4.000  -0.3379   0.00945   0.00254  -0.0030   0.5626   0.0496
  -3.750  -0.3110   0.00933   0.00239  -0.0028   0.5518   0.0555
  -3.500  -0.2840   0.00919   0.00226  -0.0026   0.5414   0.0637
  -3.250  -0.2570   0.00906   0.00213  -0.0024   0.5316   0.0727
  -3.000  -0.2300   0.00896   0.00200  -0.0022   0.5216   0.0817
  -2.750  -0.2028   0.00885   0.00189  -0.0020   0.5120   0.0923
  -2.500  -0.1756   0.00874   0.00179  -0.0018   0.5032   0.1044
  -2.250  -0.1485   0.00863   0.00169  -0.0017   0.4943   0.1189
  -2.000  -0.1213   0.00851   0.00161  -0.0015   0.4858   0.1359
  -1.750  -0.0944   0.00840   0.00153  -0.0013   0.4771   0.1564
  -1.500  -0.0674   0.00826   0.00145  -0.0011   0.4692   0.1839
  -1.250  -0.0406   0.00813   0.00138  -0.0009   0.4612   0.2147
  -1.000  -0.0143   0.00792   0.00131  -0.0007   0.4528   0.2640
  -0.750   0.0116   0.00767   0.00124  -0.0004   0.4455   0.3274
  -0.500   0.0362   0.00730   0.00116   0.0001   0.4376   0.4224
  -0.250   0.0600   0.00690   0.00109   0.0008   0.4303   0.5333
   0.000   0.0844   0.00659   0.00105   0.0014   0.4226   0.6221
   0.250   0.1099   0.00643   0.00104   0.0020   0.4154   0.6821
   0.500   0.1361   0.00634   0.00106   0.0024   0.4077   0.7248
   0.750   0.1625   0.00628   0.00109   0.0028   0.4011   0.7620
   1.000   0.1885   0.00623   0.00114   0.0033   0.3934   0.8001
   1.250   0.2150   0.00622   0.00119   0.0037   0.3864   0.8281
   1.500   0.2416   0.00624   0.00125   0.0041   0.3794   0.8522
   1.750   0.2684   0.00628   0.00131   0.0045   0.3726   0.8701
   2.000   0.2961   0.00634   0.00135   0.0046   0.3650   0.8784
   2.250   0.3240   0.00641   0.00140   0.0047   0.3583   0.8841
   2.500   0.3518   0.00647   0.00146   0.0047   0.3510   0.8902
   2.750   0.3796   0.00656   0.00151   0.0048   0.3441   0.8963
   3.000   0.4073   0.00662   0.00158   0.0049   0.3372   0.9020
   3.250   0.4348   0.00672   0.00166   0.0049   0.3300   0.9082
   3.500   0.4626   0.00679   0.00173   0.0050   0.3234   0.9137
   3.750   0.4899   0.00690   0.00181   0.0051   0.3160   0.9196
   4.000   0.5174   0.00699   0.00190   0.0052   0.3094   0.9255
   4.250   0.5449   0.00710   0.00200   0.0053   0.3027   0.9309
   4.500   0.5724   0.00719   0.00210   0.0054   0.2959   0.9368
   4.750   0.5996   0.00732   0.00221   0.0055   0.2885   0.9423
   5.000   0.6277   0.00743   0.00233   0.0054   0.2819   0.9473
   5.500   0.6832   0.00770   0.00258   0.0053   0.2665   0.9578
   5.750   0.7122   0.00787   0.00273   0.0050   0.2588   0.9622
   6.000   0.7406   0.00801   0.00287   0.0048   0.2514   0.9672
   6.250   0.7695   0.00819   0.00303   0.0044   0.2434   0.9712
   6.500   0.8005   0.00837   0.00321   0.0035   0.2343   0.9740
   6.750   0.8308   0.00856   0.00339   0.0028   0.2256   0.9773
   7.000   0.8592   0.00880   0.00360   0.0025   0.2141   0.9813
   7.250   0.8889   0.00914   0.00385   0.0017   0.1940   0.9840
   7.500   0.9196   0.00954   0.00415   0.0007   0.1733   0.9858
   7.750   0.9491   0.01004   0.00452  -0.0002   0.1474   0.9880
   8.000   0.9773   0.01061   0.00494  -0.0009   0.1204   0.9908
   8.250   1.0048   0.01112   0.00536  -0.0014   0.1003   0.9937
   8.500   1.0336   0.01171   0.00585  -0.0023   0.0797   0.9960
   8.750   1.0614   0.01243   0.00643  -0.0031   0.0572   0.9986
   9.000   1.0839   0.01318   0.00707  -0.0029   0.0370   1.0000
   9.250   1.0978   0.01386   0.00766  -0.0008   0.0235   1.0000
   9.500   1.1142   0.01439   0.00817   0.0009   0.0170   1.0000
  10.000   1.1493   0.01534   0.00914   0.0040   0.0116   1.0000
  10.250   1.1663   0.01586   0.00968   0.0055   0.0098   1.0000
  10.500   1.1845   0.01631   0.01016   0.0068   0.0090   1.0000
  10.750   1.2016   0.01682   0.01070   0.0082   0.0083   1.0000
  11.000   1.2172   0.01740   0.01131   0.0097   0.0075   1.0000
  11.250   1.2322   0.01798   0.01194   0.0113   0.0070   1.0000
  11.500   1.2466   0.01853   0.01254   0.0130   0.0067   1.0000
  11.750   1.2559   0.01913   0.01318   0.0156   0.0064   1.0000
  12.000   1.2639   0.01981   0.01392   0.0181   0.0061   1.0000
  12.250   1.2715   0.02061   0.01478   0.0203   0.0059   1.0000
  12.500   1.2780   0.02159   0.01581   0.0223   0.0056   1.0000
  12.750   1.2842   0.02273   0.01701   0.0238   0.0054   1.0000
  13.000   1.2892   0.02410   0.01845   0.0251   0.0052   1.0000
  13.250   1.2920   0.02582   0.02025   0.0261   0.0049   1.0000
  13.500   1.2980   0.02744   0.02195   0.0266   0.0048   1.0000
  13.750   1.3021   0.02937   0.02396   0.0268   0.0047   1.0000
  14.000   1.3066   0.03137   0.02604   0.0269   0.0045   1.0000
  14.250   1.3082   0.03379   0.02854   0.0267   0.0044   1.0000
  14.500   1.3102   0.03624   0.03107   0.0264   0.0043   1.0000
  14.750   1.3096   0.03907   0.03399   0.0258   0.0041   1.0000
  15.000   1.3050   0.04242   0.03744   0.0251   0.0042   1.0000
  15.250   1.3035   0.04547   0.04056   0.0243   0.0040   1.0000
  15.500   1.2991   0.04890   0.04408   0.0234   0.0038   1.0000
  15.750   1.2931   0.05259   0.04787   0.0224   0.0039   1.0000
  16.000   1.2867   0.05640   0.05174   0.0212   0.0037   1.0000
  16.250   1.2794   0.06046   0.05590   0.0199   0.0037   1.0000
  16.500   1.2674   0.06531   0.06086   0.0181   0.0037   1.0000
  16.750   1.2590   0.06977   0.06540   0.0164   0.0036   1.0000
  17.000   1.2488   0.07461   0.07034   0.0146   0.0035   1.0000
  17.250   1.2411   0.07914   0.07496   0.0128   0.0035   1.0000
  17.500   1.2247   0.08515   0.08108   0.0102   0.0034   1.0000
  17.750   1.2140   0.09040   0.08642   0.0080   0.0034   1.0000
<< Back to EH 2.0/12 (eh2012-il)

Polar data table (+)

Polar graphs


<< Back to EH 2.0/12 (eh2012-il)