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

EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EH 1.0/9.0 (eh1090-il)
Reynolds number: 100,000
Max Cl/Cd: 43.01 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1090-il-100000-n5.txt
Download as CSV file: xf-eh1090-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6209   0.08435   0.07965  -0.0070   1.0000   0.0211
  -9.250  -0.6271   0.07789   0.07322  -0.0117   1.0000   0.0208
  -9.000  -0.6388   0.07112   0.06644  -0.0170   1.0000   0.0206
  -8.750  -0.6548   0.06582   0.06107  -0.0192   1.0000   0.0204
  -8.500  -0.6668   0.06122   0.05635  -0.0197   1.0000   0.0203
  -8.250  -0.6744   0.05651   0.05144  -0.0199   1.0000   0.0201
  -8.000  -0.6788   0.05171   0.04635  -0.0196   1.0000   0.0201
  -7.750  -0.6783   0.04720   0.04148  -0.0187   1.0000   0.0200
  -7.500  -0.6741   0.04284   0.03668  -0.0175   1.0000   0.0201
  -7.250  -0.6656   0.03889   0.03224  -0.0161   1.0000   0.0202
  -7.000  -0.6533   0.03534   0.02816  -0.0147   1.0000   0.0205
  -6.750  -0.6373   0.03234   0.02464  -0.0132   1.0000   0.0209
  -6.500  -0.6205   0.02953   0.02142  -0.0120   1.0000   0.0225
  -6.250  -0.6007   0.02794   0.01966  -0.0112   1.0000   0.0244
  -6.000  -0.5793   0.02613   0.01758  -0.0102   1.0000   0.0263
  -5.750  -0.5568   0.02419   0.01537  -0.0090   1.0000   0.0276
  -5.500  -0.5342   0.02253   0.01348  -0.0079   1.0000   0.0294
  -5.250  -0.5119   0.02114   0.01191  -0.0066   1.0000   0.0314
  -5.000  -0.4916   0.01985   0.01063  -0.0055   1.0000   0.0360
  -4.750  -0.4698   0.01895   0.00961  -0.0043   1.0000   0.0431
  -4.500  -0.4498   0.01787   0.00849  -0.0030   1.0000   0.0524
  -4.250  -0.4293   0.01700   0.00769  -0.0017   1.0000   0.0705
  -4.000  -0.4091   0.01619   0.00700  -0.0004   1.0000   0.0973
  -3.750  -0.3891   0.01546   0.00643   0.0008   1.0000   0.1344
  -3.500  -0.3696   0.01474   0.00597   0.0021   1.0000   0.1844
  -3.250  -0.3509   0.01399   0.00557   0.0034   1.0000   0.2576
  -3.000  -0.3340   0.01317   0.00520   0.0050   1.0000   0.3652
  -2.750  -0.3171   0.01227   0.00506   0.0069   0.9980   0.5274
  -2.500  -0.2835   0.01176   0.00517   0.0065   0.9850   0.6996
  -2.250  -0.2452   0.01172   0.00524   0.0054   0.9722   0.7858
  -2.000  -0.2048   0.01179   0.00524   0.0038   0.9586   0.8408
  -1.750  -0.1616   0.01191   0.00528   0.0016   0.9445   0.8819
  -1.500  -0.1152   0.01204   0.00526  -0.0013   0.9295   0.9112
  -1.250  -0.0639   0.01215   0.00521  -0.0053   0.9137   0.9334
  -1.000  -0.0111   0.01222   0.00512  -0.0098   0.8942   0.9509
  -0.750   0.0391   0.01220   0.00494  -0.0139   0.8712   0.9628
  -0.500   0.0818   0.01215   0.00473  -0.0167   0.8445   0.9730
  -0.250   0.1201   0.01211   0.00455  -0.0187   0.8172   0.9827
   0.000   0.1587   0.01204   0.00433  -0.0208   0.7897   0.9905
   0.250   0.1950   0.01198   0.00414  -0.0226   0.7631   0.9984
   0.500   0.2194   0.01198   0.00403  -0.0220   0.7380   1.0000
   0.750   0.2409   0.01201   0.00395  -0.0208   0.7148   1.0000
   1.000   0.2624   0.01206   0.00390  -0.0196   0.6926   1.0000
   1.250   0.2845   0.01213   0.00390  -0.0185   0.6710   1.0000
   1.500   0.3066   0.01222   0.00390  -0.0174   0.6506   1.0000
   1.750   0.3288   0.01233   0.00394  -0.0164   0.6303   1.0000
   2.000   0.3510   0.01245   0.00400  -0.0153   0.6109   1.0000
   2.250   0.3734   0.01259   0.00408  -0.0142   0.5923   1.0000
   2.500   0.3960   0.01273   0.00422  -0.0132   0.5734   1.0000
   2.750   0.4186   0.01290   0.00435  -0.0122   0.5551   1.0000
   3.000   0.4412   0.01309   0.00450  -0.0112   0.5373   1.0000
   3.250   0.4641   0.01327   0.00469  -0.0103   0.5185   1.0000
   3.500   0.4869   0.01348   0.00493  -0.0093   0.5002   1.0000
   3.750   0.5098   0.01371   0.00514  -0.0083   0.4824   1.0000
   4.000   0.5329   0.01394   0.00540  -0.0074   0.4634   1.0000
   4.250   0.5558   0.01419   0.00567  -0.0064   0.4443   1.0000
   4.500   0.5786   0.01446   0.00596  -0.0055   0.4244   1.0000
   4.750   0.6014   0.01474   0.00632  -0.0045   0.4028   1.0000
   5.000   0.6241   0.01504   0.00666  -0.0036   0.3810   1.0000
   5.250   0.6469   0.01537   0.00704  -0.0026   0.3600   1.0000
   5.500   0.6696   0.01572   0.00746  -0.0017   0.3376   1.0000
   5.750   0.6919   0.01611   0.00789  -0.0008   0.3096   1.0000
   6.000   0.7131   0.01658   0.00830   0.0003   0.2694   1.0000
   6.250   0.7326   0.01729   0.00882   0.0013   0.2091   1.0000
   6.500   0.7508   0.01832   0.00953   0.0023   0.1412   1.0000
   6.750   0.7665   0.01988   0.01064   0.0035   0.0728   1.0000
   7.000   0.7825   0.02146   0.01206   0.0050   0.0450   1.0000
   7.250   0.7994   0.02284   0.01349   0.0063   0.0345   1.0000
   7.500   0.8162   0.02417   0.01494   0.0077   0.0295   1.0000
   7.750   0.8302   0.02580   0.01670   0.0093   0.0270   1.0000
   8.000   0.8461   0.02726   0.01836   0.0109   0.0253   1.0000
   8.250   0.8617   0.02887   0.02020   0.0124   0.0239   1.0000
   8.500   0.8777   0.03045   0.02192   0.0137   0.0220   1.0000
   8.750   0.8919   0.03210   0.02365   0.0149   0.0198   1.0000
   9.000   0.9038   0.03474   0.02640   0.0162   0.0184   1.0000
   9.250   0.9183   0.03694   0.02889   0.0176   0.0179   1.0000
   9.500   0.9304   0.03942   0.03168   0.0189   0.0175   1.0000
   9.750   0.9388   0.04219   0.03479   0.0204   0.0171   1.0000
  10.000   0.9423   0.04520   0.03816   0.0219   0.0168   1.0000
  10.250   0.9410   0.04825   0.04153   0.0235   0.0167   1.0000
  10.500   0.9330   0.05126   0.04482   0.0254   0.0166   1.0000
  10.750   0.9209   0.05467   0.04849   0.0262   0.0165   1.0000
  11.000   0.9080   0.05847   0.05252   0.0258   0.0166   1.0000
  11.250   0.8930   0.06300   0.05726   0.0239   0.0166   1.0000
  11.500   0.8759   0.06844   0.06291   0.0207   0.0166   1.0000
  11.750   0.8594   0.07446   0.06909   0.0166   0.0168   1.0000
  12.000   0.8415   0.08145   0.07622   0.0116   0.0169   1.0000
  12.250   0.8214   0.08971   0.08459   0.0057   0.0171   1.0000
<< Back to EH 1.0/9.0 (eh1090-il)

Polar data table (+)

Polar graphs


<< Back to EH 1.0/9.0 (eh1090-il)