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EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EH 2.0/7.0 (eh2070-il)
Reynolds number: 200,000
Max Cl/Cd: 60.04 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eh2070-il-200000.txt
Download as CSV file: xf-eh2070-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/7.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5348   0.09302   0.08980   0.0102   1.0000   0.0293
  -7.750  -0.5344   0.08940   0.08623   0.0075   1.0000   0.0301
  -7.500  -0.5365   0.08572   0.08260   0.0041   1.0000   0.0306
  -7.250  -0.5332   0.08175   0.07862  -0.0009   1.0000   0.0313
  -7.000  -0.5243   0.07801   0.07481  -0.0056   1.0000   0.0319
  -6.750  -0.5131   0.07436   0.07104  -0.0087   1.0000   0.0323
  -6.500  -0.5009   0.07060   0.06716  -0.0105   1.0000   0.0325
  -6.250  -0.4644   0.05156   0.04847  -0.0116   1.0000   0.0338
  -6.000  -0.4559   0.04741   0.04432  -0.0114   1.0000   0.0349
  -5.750  -0.4450   0.04338   0.04025  -0.0119   1.0000   0.0363
  -5.500  -0.4323   0.03930   0.03603  -0.0126   1.0000   0.0383
  -5.250  -0.4170   0.03515   0.03172  -0.0135   1.0000   0.0410
  -5.000  -0.3907   0.03312   0.02910  -0.0138   1.0000   0.0451
  -4.750  -0.3824   0.02640   0.02235  -0.0143   1.0000   0.0468
  -4.500  -0.3661   0.02331   0.01926  -0.0140   1.0000   0.0492
  -4.250  -0.3462   0.02065   0.01641  -0.0137   1.0000   0.0539
  -4.000  -0.3268   0.01759   0.01303  -0.0132   1.0000   0.0614
  -3.750  -0.3070   0.01552   0.01076  -0.0126   1.0000   0.0744
  -3.500  -0.2859   0.01384   0.00875  -0.0117   1.0000   0.0864
  -3.250  -0.2698   0.02278   0.01659  -0.0075   1.0000   0.0431
  -3.000  -0.2437   0.01976   0.01295  -0.0053   1.0000   0.0330
  -2.750  -0.2207   0.01753   0.01052  -0.0041   1.0000   0.0317
  -2.500  -0.1970   0.01580   0.00855  -0.0030   0.9987   0.0317
  -2.250  -0.1525   0.01353   0.00613  -0.0061   0.9802   0.0352
  -2.000  -0.1086   0.01257   0.00513  -0.0091   0.9522   0.0447
  -1.750  -0.0719   0.01117   0.00381  -0.0106   0.9170   0.0753
  -1.500  -0.0494   0.00956   0.00321  -0.0098   0.8780   0.3211
  -1.250   0.0209   0.00822   0.00361  -0.0150   0.8562   0.9787
  -1.000   0.0876   0.00827   0.00323  -0.0227   0.8193   1.0000
  -0.750   0.1079   0.00835   0.00304  -0.0210   0.7849   1.0000
  -0.500   0.1291   0.00843   0.00288  -0.0196   0.7569   1.0000
  -0.250   0.1512   0.00851   0.00272  -0.0184   0.7325   1.0000
   0.000   0.1737   0.00860   0.00260  -0.0173   0.7112   1.0000
   0.250   0.1967   0.00868   0.00252  -0.0164   0.6904   1.0000
   0.500   0.2198   0.00878   0.00246  -0.0155   0.6721   1.0000
   0.750   0.2431   0.00888   0.00243  -0.0146   0.6548   1.0000
   1.000   0.2667   0.00898   0.00242  -0.0138   0.6377   1.0000
   1.250   0.2904   0.00910   0.00243  -0.0130   0.6217   1.0000
   1.500   0.3143   0.00922   0.00245  -0.0122   0.6066   1.0000
   1.750   0.3382   0.00935   0.00250  -0.0114   0.5919   1.0000
   2.000   0.3623   0.00949   0.00257  -0.0107   0.5778   1.0000
   2.250   0.3865   0.00963   0.00267  -0.0100   0.5639   1.0000
   2.500   0.4108   0.00978   0.00277  -0.0093   0.5502   1.0000
   2.750   0.4352   0.00994   0.00289  -0.0087   0.5367   1.0000
   3.000   0.4597   0.01010   0.00303  -0.0080   0.5232   1.0000
   3.250   0.4843   0.01027   0.00318  -0.0074   0.5100   1.0000
   3.500   0.5091   0.01045   0.00341  -0.0068   0.4972   1.0000
   3.750   0.5339   0.01065   0.00362  -0.0062   0.4846   1.0000
   4.000   0.5587   0.01085   0.00385  -0.0056   0.4719   1.0000
   4.250   0.5836   0.01106   0.00410  -0.0051   0.4591   1.0000
   4.500   0.6085   0.01127   0.00435  -0.0045   0.4456   1.0000
   4.750   0.6334   0.01148   0.00467  -0.0039   0.4315   1.0000
   5.000   0.6584   0.01169   0.00497  -0.0034   0.4170   1.0000
   5.250   0.6820   0.01166   0.00493  -0.0025   0.3828   1.0000
   5.500   0.7055   0.01175   0.00496  -0.0017   0.3326   1.0000
   5.750   0.7185   0.01404   0.00583  -0.0006   0.0688   1.0000
   6.000   0.7376   0.01589   0.00758   0.0007   0.0304   1.0000
   6.250   0.7585   0.01707   0.00895   0.0016   0.0235   1.0000
   6.500   0.7748   0.01909   0.01110   0.0031   0.0215   1.0000
   6.750   0.7948   0.02054   0.01266   0.0044   0.0208   1.0000
   7.000   0.8148   0.02234   0.01455   0.0058   0.0205   1.0000
   7.250   0.8357   0.02449   0.01681   0.0070   0.0207   1.0000
   7.500   0.8570   0.02728   0.01978   0.0082   0.0211   1.0000
   7.750   0.8794   0.03005   0.02273   0.0091   0.0221   1.0000
   8.000   0.9043   0.03150   0.02468   0.0109   0.0256   1.0000
   8.250   0.9186   0.03771   0.03140   0.0124   0.0314   1.0000
  12.250   0.6546   0.12969   0.12647  -0.0203   0.0623   1.0000
  12.500   0.6549   0.13354   0.13033  -0.0217   0.0598   1.0000
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