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EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 50,000
Max Cl/Cd: 18.04 at α=12.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh2012-il-50000.txt
Download as CSV file: xf-eh2012-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4648   0.10744   0.10090   0.0070   1.0000   0.2958
  -9.000  -0.4676   0.10462   0.09816   0.0069   1.0000   0.3121
  -8.750  -0.4756   0.10214   0.09577   0.0068   1.0000   0.3281
  -8.500  -0.4408   0.09674   0.09029   0.0087   1.0000   0.3493
  -8.250  -0.4359   0.09355   0.08716   0.0093   1.0000   0.3684
  -7.750  -0.4172   0.08715   0.08083   0.0122   1.0000   0.4227
  -7.500  -0.4215   0.08497   0.07875   0.0138   1.0000   0.4488
  -7.250  -0.5860   0.06130   0.05455  -0.0214   1.0000   0.1498
  -7.000  -0.5776   0.05698   0.05009  -0.0206   1.0000   0.1465
  -6.750  -0.5727   0.05288   0.04576  -0.0193   1.0000   0.1449
  -6.500  -0.5671   0.04891   0.04149  -0.0176   1.0000   0.1432
  -6.250  -0.5606   0.04516   0.03736  -0.0156   1.0000   0.1414
  -6.000  -0.5524   0.04208   0.03391  -0.0132   1.0000   0.1436
  -5.750  -0.5452   0.03945   0.03073  -0.0104   1.0000   0.1477
  -5.500  -0.5327   0.03684   0.02802  -0.0083   1.0000   0.1527
  -5.250  -0.5213   0.03484   0.02577  -0.0058   1.0000   0.1594
  -5.000  -0.5106   0.03299   0.02370  -0.0034   1.0000   0.1682
  -4.750  -0.4990   0.03137   0.02176  -0.0009   1.0000   0.1767
  -4.500  -0.4872   0.02998   0.02034   0.0012   1.0000   0.1889
  -4.250  -0.4737   0.02863   0.01889   0.0031   1.0000   0.2011
  -4.000  -0.4598   0.02752   0.01771   0.0048   1.0000   0.2172
  -3.750  -0.4438   0.02650   0.01661   0.0063   1.0000   0.2360
  -3.500  -0.4257   0.02553   0.01575   0.0073   1.0000   0.2596
  -3.250  -0.4063   0.02464   0.01500   0.0081   1.0000   0.2915
  -3.000  -0.0258   0.02219   0.01417  -0.0343   1.0000   1.0000
  -2.750  -0.0544   0.02301   0.01503  -0.0288   1.0000   1.0000
  -2.500  -0.0812   0.02374   0.01576  -0.0236   1.0000   1.0000
  -2.250  -0.0366   0.02395   0.01570  -0.0299   0.9843   1.0000
  -2.000   0.0374   0.02385   0.01524  -0.0403   0.9612   1.0000
  -1.750   0.1171   0.02355   0.01465  -0.0511   0.9418   1.0000
  -1.500   0.1792   0.02328   0.01415  -0.0583   0.9199   1.0000
  -1.250   0.2320   0.02304   0.01374  -0.0634   0.8986   1.0000
  -1.000   0.2658   0.02308   0.01363  -0.0650   0.8764   1.0000
  -0.750   0.2929   0.02323   0.01365  -0.0651   0.8556   1.0000
  -0.500   0.3167   0.02341   0.01372  -0.0644   0.8370   1.0000
  -0.250   0.3346   0.02381   0.01403  -0.0630   0.8178   1.0000
   0.000   0.3533   0.02420   0.01433  -0.0617   0.8002   1.0000
   0.250   0.3714   0.02460   0.01466  -0.0602   0.7837   1.0000
   0.500   0.3890   0.02505   0.01505  -0.0587   0.7682   1.0000
   0.750   0.4061   0.02554   0.01548  -0.0570   0.7532   1.0000
   1.000   0.4228   0.02609   0.01599  -0.0554   0.7389   1.0000
   1.250   0.4393   0.02668   0.01653  -0.0537   0.7252   1.0000
   1.500   0.4559   0.02727   0.01709  -0.0520   0.7121   1.0000
   1.750   0.4735   0.02781   0.01759  -0.0502   0.7000   1.0000
   2.000   0.4904   0.02841   0.01817  -0.0484   0.6877   1.0000
   2.250   0.5043   0.02931   0.01908  -0.0469   0.6747   1.0000
   2.500   0.5179   0.03026   0.02003  -0.0452   0.6623   1.0000
   2.750   0.5320   0.03115   0.02095  -0.0434   0.6506   1.0000
   3.000   0.5502   0.03175   0.02152  -0.0415   0.6404   1.0000
   3.250   0.5636   0.03276   0.02256  -0.0398   0.6289   1.0000
   3.500   0.5727   0.03411   0.02395  -0.0380   0.6170   1.0000
   3.750   0.5842   0.03533   0.02519  -0.0361   0.6064   1.0000
   4.000   0.6069   0.03570   0.02557  -0.0344   0.5973   1.0000
   4.250   0.6091   0.03764   0.02758  -0.0324   0.5855   1.0000
   4.500   0.6138   0.03945   0.02943  -0.0305   0.5749   1.0000
   4.750   0.6381   0.03986   0.02984  -0.0289   0.5661   1.0000
   5.000   0.6369   0.04215   0.03219  -0.0270   0.5551   1.0000
   5.250   0.6322   0.04476   0.03483  -0.0250   0.5448   1.0000
   5.500   0.6592   0.04513   0.03526  -0.0235   0.5361   1.0000
   5.750   0.6459   0.04851   0.03867  -0.0217   0.5258   1.0000
   6.000   0.6351   0.05178   0.04194  -0.0201   0.5166   1.0000
   6.250   0.6824   0.05083   0.04111  -0.0190   0.5076   1.0000
   6.500   0.6179   0.05800   0.04814  -0.0173   0.5002   1.0000
   6.750   0.6438   0.05904   0.04927  -0.0165   0.4908   1.0000
   7.000   0.6082   0.06391   0.05405  -0.0152   0.4854   1.0000
   7.250   0.6335   0.06524   0.05548  -0.0145   0.4764   1.0000
   7.500   0.6062   0.06992   0.06010  -0.0143   0.4723   1.0000
   7.750   0.6342   0.07117   0.06149  -0.0136   0.4620   1.0000
   8.000   0.6130   0.07583   0.06612  -0.0140   0.4601   1.0000
   8.250   0.6024   0.07985   0.07015  -0.0145   0.4585   1.0000
   8.500   0.5974   0.08383   0.07416  -0.0153   0.4590   1.0000
   8.750   0.6047   0.08783   0.07824  -0.0164   0.4621   1.0000
  12.250   1.0702   0.05931   0.05232   0.0276   0.1894   1.0000
  12.500   1.0367   0.06606   0.05918   0.0262   0.1885   1.0000
  13.000   1.0618   0.06487   0.05736   0.0311   0.1337   1.0000
  13.250   1.0336   0.07149   0.06423   0.0288   0.1332   1.0000
  13.500   1.0043   0.07916   0.07208   0.0255   0.1338   1.0000
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