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EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 0.0/9.0 (eh0009-il)
Reynolds number: 200,000
Max Cl/Cd: 43.29 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh0009-il-200000-n5.txt
Download as CSV file: xf-eh0009-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8386   0.05455   0.05048  -0.0248   1.0000   0.0068
 -10.500  -0.8558   0.05009   0.04582  -0.0262   1.0000   0.0068
 -10.250  -0.8707   0.04662   0.04214  -0.0255   1.0000   0.0068
 -10.000  -0.8903   0.04287   0.03812  -0.0229   1.0000   0.0070
  -9.750  -0.8953   0.03959   0.03453  -0.0210   1.0000   0.0071
  -9.500  -0.8916   0.03719   0.03192  -0.0196   1.0000   0.0075
  -9.250  -0.8830   0.03511   0.02956  -0.0182   1.0000   0.0078
  -9.000  -0.8667   0.03456   0.02893  -0.0175   1.0000   0.0088
  -8.750  -0.8546   0.03236   0.02642  -0.0161   1.0000   0.0094
  -8.500  -0.8412   0.02998   0.02369  -0.0147   1.0000   0.0100
  -8.250  -0.8257   0.02764   0.02100  -0.0132   1.0000   0.0104
  -8.000  -0.8081   0.02566   0.01873  -0.0119   1.0000   0.0109
  -7.750  -0.7887   0.02408   0.01689  -0.0107   1.0000   0.0115
  -7.500  -0.7723   0.02189   0.01452  -0.0092   1.0000   0.0124
  -7.250  -0.7528   0.02072   0.01327  -0.0082   1.0000   0.0139
  -7.000  -0.7313   0.01990   0.01236  -0.0074   1.0000   0.0160
  -6.750  -0.7108   0.01883   0.01114  -0.0062   1.0000   0.0176
  -6.500  -0.6898   0.01789   0.01001  -0.0050   1.0000   0.0190
  -6.250  -0.6712   0.01664   0.00867  -0.0036   1.0000   0.0220
  -6.000  -0.6494   0.01595   0.00790  -0.0026   1.0000   0.0265
  -5.750  -0.6281   0.01520   0.00711  -0.0016   1.0000   0.0332
  -5.500  -0.6064   0.01453   0.00642  -0.0005   1.0000   0.0434
  -5.250  -0.5852   0.01386   0.00583   0.0005   1.0000   0.0647
  -5.000  -0.5641   0.01323   0.00532   0.0016   1.0000   0.0929
  -4.750  -0.5431   0.01262   0.00486   0.0026   1.0000   0.1320
  -4.500  -0.5217   0.01210   0.00448   0.0036   1.0000   0.1716
  -4.250  -0.5007   0.01158   0.00416   0.0046   1.0000   0.2191
  -4.000  -0.4800   0.01108   0.00388   0.0057   1.0000   0.2732
  -3.750  -0.4588   0.01069   0.00365   0.0067   1.0000   0.3200
  -3.500  -0.4376   0.01035   0.00345   0.0078   1.0000   0.3627
  -3.250  -0.4166   0.01005   0.00325   0.0090   1.0000   0.4051
  -3.000  -0.3821   0.00975   0.00311   0.0073   0.9937   0.4560
  -2.750  -0.3476   0.00948   0.00299   0.0058   0.9861   0.5025
  -2.500  -0.3123   0.00925   0.00290   0.0041   0.9788   0.5468
  -2.250  -0.2775   0.00905   0.00279   0.0026   0.9707   0.5877
  -2.000  -0.2443   0.00887   0.00273   0.0016   0.9610   0.6250
  -1.750  -0.2106   0.00871   0.00268   0.0005   0.9512   0.6612
  -1.500  -0.1768   0.00857   0.00264  -0.0005   0.9408   0.6948
  -1.250  -0.1452   0.00846   0.00259  -0.0010   0.9283   0.7243
  -1.000  -0.1140   0.00837   0.00256  -0.0013   0.9147   0.7517
  -0.750  -0.0838   0.00830   0.00254  -0.0014   0.8997   0.7774
  -0.500  -0.0555   0.00824   0.00253  -0.0011   0.8825   0.8017
  -0.250  -0.0276   0.00821   0.00252  -0.0006   0.8641   0.8239
   0.000   0.0000   0.00820   0.00251   0.0000   0.8450   0.8450
   0.250   0.0275   0.00821   0.00252   0.0006   0.8239   0.8641
   0.500   0.0554   0.00824   0.00253   0.0011   0.8018   0.8825
   0.750   0.0838   0.00830   0.00254   0.0014   0.7775   0.8997
   1.000   0.1140   0.00837   0.00256   0.0014   0.7517   0.9147
   1.250   0.1451   0.00846   0.00259   0.0010   0.7242   0.9283
   1.500   0.1767   0.00857   0.00264   0.0005   0.6946   0.9409
   1.750   0.2106   0.00871   0.00268  -0.0005   0.6614   0.9513
   2.000   0.2443   0.00887   0.00272  -0.0016   0.6251   0.9611
   2.250   0.2775   0.00905   0.00279  -0.0026   0.5878   0.9707
   2.500   0.3123   0.00925   0.00290  -0.0041   0.5472   0.9790
   2.750   0.3476   0.00948   0.00299  -0.0058   0.5025   0.9863
   3.000   0.3822   0.00975   0.00311  -0.0073   0.4558   0.9938
   3.250   0.4163   0.01004   0.00325  -0.0089   0.4056   1.0000
   3.500   0.4374   0.01035   0.00344  -0.0078   0.3631   1.0000
   3.750   0.4585   0.01069   0.00364  -0.0067   0.3198   1.0000
   4.000   0.4797   0.01108   0.00388  -0.0056   0.2735   1.0000
   4.250   0.5005   0.01157   0.00415  -0.0045   0.2199   1.0000
   4.500   0.5215   0.01210   0.00448  -0.0035   0.1718   1.0000
   4.750   0.5428   0.01262   0.00485  -0.0025   0.1319   1.0000
   5.000   0.5638   0.01323   0.00532  -0.0015   0.0929   1.0000
   5.250   0.5850   0.01386   0.00583  -0.0005   0.0647   1.0000
   5.500   0.6063   0.01453   0.00642   0.0005   0.0436   1.0000
   5.750   0.6280   0.01520   0.00711   0.0016   0.0332   1.0000
   6.000   0.6493   0.01594   0.00789   0.0026   0.0265   1.0000
   6.250   0.6711   0.01664   0.00866   0.0036   0.0220   1.0000
   6.500   0.6898   0.01789   0.01000   0.0050   0.0189   1.0000
   6.750   0.7108   0.01883   0.01114   0.0062   0.0176   1.0000
   7.000   0.7314   0.01991   0.01237   0.0074   0.0160   1.0000
   7.250   0.7530   0.02071   0.01326   0.0082   0.0138   1.0000
   7.500   0.7726   0.02189   0.01452   0.0092   0.0124   1.0000
   7.750   0.7890   0.02407   0.01689   0.0107   0.0114   1.0000
   8.000   0.8084   0.02566   0.01873   0.0118   0.0109   1.0000
   8.250   0.8261   0.02766   0.02102   0.0132   0.0104   1.0000
   8.500   0.8415   0.03002   0.02373   0.0146   0.0100   1.0000
   8.750   0.8549   0.03244   0.02651   0.0161   0.0095   1.0000
   9.000   0.8683   0.03428   0.02861   0.0173   0.0087   1.0000
   9.250   0.8805   0.03590   0.03045   0.0184   0.0080   1.0000
   9.500   0.8899   0.03775   0.03255   0.0197   0.0076   1.0000
   9.750   0.8956   0.03965   0.03459   0.0209   0.0071   1.0000
  10.000   0.8858   0.04346   0.03874   0.0229   0.0069   1.0000
  10.500   0.8565   0.05016   0.04591   0.0260   0.0068   1.0000
  11.000   0.8253   0.05973   0.05586   0.0212   0.0069   1.0000
  11.250   0.8123   0.06603   0.06233   0.0161   0.0070   1.0000
  11.500   0.7922   0.07537   0.07183   0.0085   0.0070   1.0000
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