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EPPLER E1212 AIRFOIL (e1212-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E1212 AIRFOIL (e1212-il)
Reynolds number: 100,000
Max Cl/Cd: 41.91 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1212-il-100000-n5.txt
Download as CSV file: xf-e1212-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E1212 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.5341   0.10789   0.10205  -0.0305   1.0000   0.0774
 -13.500  -0.5066   0.10606   0.10024  -0.0308   1.0000   0.0821
 -13.250  -0.6178   0.08267   0.07680  -0.0438   1.0000   0.0927
 -13.000  -0.5644   0.08850   0.08270  -0.0398   1.0000   0.0937
 -12.750  -0.7027   0.06364   0.05769  -0.0549   1.0000   0.1007
 -12.500  -0.6275   0.07213   0.06634  -0.0487   1.0000   0.1036
 -12.250  -0.7747   0.04794   0.04186  -0.0653   1.0000   0.1053
 -12.000  -0.8131   0.04115   0.03490  -0.0698   1.0000   0.1069
 -11.750  -0.8390   0.03770   0.03129  -0.0693   1.0000   0.1091
 -11.500  -0.8467   0.03590   0.02943  -0.0673   1.0000   0.1123
 -11.250  -0.8427   0.03487   0.02839  -0.0656   1.0000   0.1163
 -11.000  -0.8438   0.03311   0.02643  -0.0638   1.0000   0.1212
 -10.750  -0.8302   0.03280   0.02621  -0.0622   1.0000   0.1251
 -10.500  -0.8229   0.03170   0.02496  -0.0604   1.0000   0.1303
 -10.250  -0.8098   0.03119   0.02446  -0.0587   1.0000   0.1345
 -10.000  -0.7965   0.03074   0.02399  -0.0570   1.0000   0.1392
  -9.750  -0.7881   0.02972   0.02280  -0.0551   1.0000   0.1442
  -9.500  -0.7581   0.02972   0.02290  -0.0558   0.9929   0.1488
  -9.250  -0.7243   0.02854   0.02139  -0.0585   0.9719   0.1561
  -9.000  -0.6846   0.02856   0.02151  -0.0605   0.9517   0.1606
  -8.750  -0.6476   0.02775   0.02047  -0.0630   0.9296   0.1671
  -8.500  -0.6073   0.02726   0.01989  -0.0655   0.9084   0.1722
  -8.250  -0.5673   0.02690   0.01942  -0.0678   0.8862   0.1774
  -8.000  -0.5343   0.02593   0.01804  -0.0693   0.8624   0.1837
  -7.500  -0.4725   0.02550   0.01746  -0.0699   0.8167   0.1917
  -7.250  -0.4479   0.02489   0.01652  -0.0695   0.7958   0.1971
  -7.000  -0.4220   0.02452   0.01602  -0.0690   0.7769   0.2008
  -6.750  -0.3959   0.02433   0.01576  -0.0684   0.7586   0.2044
  -6.500  -0.3706   0.02400   0.01526  -0.0678   0.7415   0.2088
  -6.250  -0.3459   0.02350   0.01445  -0.0673   0.7257   0.2139
  -6.000  -0.3196   0.02319   0.01407  -0.0668   0.7109   0.2174
  -5.750  -0.2934   0.02296   0.01378  -0.0662   0.6965   0.2210
  -5.500  -0.2675   0.02267   0.01336  -0.0657   0.6825   0.2254
  -5.250  -0.2418   0.02233   0.01275  -0.0651   0.6698   0.2303
  -5.000  -0.2158   0.02200   0.01233  -0.0646   0.6567   0.2340
  -4.750  -0.1894   0.02178   0.01208  -0.0641   0.6445   0.2377
  -4.500  -0.1632   0.02156   0.01174  -0.0636   0.6328   0.2420
  -4.250  -0.1368   0.02130   0.01134  -0.0631   0.6208   0.2467
  -4.000  -0.1104   0.02105   0.01088  -0.0626   0.6105   0.2510
  -3.750  -0.0839   0.02083   0.01069  -0.0622   0.5987   0.2548
  -3.250  -0.0307   0.02047   0.01016  -0.0612   0.5779   0.2640
  -3.000  -0.0038   0.02032   0.00978  -0.0608   0.5688   0.2689
  -2.750   0.0227   0.02011   0.00964  -0.0603   0.5580   0.2729
  -2.500   0.0494   0.01998   0.00944  -0.0598   0.5493   0.2776
  -2.250   0.0762   0.01986   0.00927  -0.0595   0.5393   0.2827
  -2.000   0.1032   0.01976   0.00901  -0.0590   0.5305   0.2882
  -1.750   0.1297   0.01962   0.00891  -0.0586   0.5214   0.2929
  -1.500   0.1564   0.01953   0.00879  -0.0581   0.5126   0.2983
  -1.250   0.1833   0.01946   0.00865  -0.0577   0.5045   0.3043
  -1.000   0.2100   0.01939   0.00856  -0.0573   0.4956   0.3103
  -0.750   0.2366   0.01933   0.00846  -0.0568   0.4885   0.3164
  -0.500   0.2632   0.01930   0.00845  -0.0563   0.4797   0.3236
  -0.250   0.2899   0.01926   0.00837  -0.0559   0.4721   0.3307
   0.000   0.3162   0.01923   0.00836  -0.0554   0.4648   0.3383
   0.250   0.3427   0.01925   0.00837  -0.0549   0.4568   0.3478
   0.500   0.3690   0.01923   0.00835  -0.0544   0.4503   0.3571
   0.750   0.3953   0.01926   0.00842  -0.0540   0.4428   0.3684
   1.000   0.4213   0.01926   0.00848  -0.0534   0.4355   0.3801
   1.500   0.4737   0.01936   0.00865  -0.0525   0.4222   0.4123
   1.750   0.4997   0.01939   0.00875  -0.0520   0.4156   0.4330
   2.000   0.5257   0.01943   0.00880  -0.0514   0.4101   0.4580
   2.250   0.5507   0.01949   0.00906  -0.0508   0.4030   0.4888
   2.500   0.5758   0.01951   0.00922  -0.0501   0.3969   0.5286
   2.750   0.6008   0.01952   0.00932  -0.0493   0.3919   0.5795
   3.000   0.6238   0.01954   0.00965  -0.0482   0.3853   0.6423
   3.250   0.6459   0.01950   0.00988  -0.0466   0.3795   0.7228
   3.500   0.6726   0.01943   0.01003  -0.0456   0.3745   0.8348
   3.750   0.7253   0.01961   0.01034  -0.0503   0.3669   1.0000
   4.000   0.7490   0.01991   0.01056  -0.0495   0.3613   1.0000
   4.250   0.7734   0.02020   0.01071  -0.0489   0.3567   1.0000
   4.500   0.7972   0.02056   0.01102  -0.0482   0.3518   1.0000
   4.750   0.8205   0.02093   0.01138  -0.0474   0.3463   1.0000
   5.000   0.8443   0.02126   0.01164  -0.0468   0.3414   1.0000
   5.250   0.8690   0.02159   0.01183  -0.0462   0.3373   1.0000
   5.500   0.8914   0.02204   0.01232  -0.0453   0.3322   1.0000
   5.750   0.9142   0.02246   0.01274  -0.0446   0.3274   1.0000
   6.000   0.9378   0.02284   0.01307  -0.0439   0.3232   1.0000
   6.250   0.9624   0.02321   0.01332  -0.0433   0.3196   1.0000
   6.500   0.9831   0.02374   0.01394  -0.0424   0.3147   1.0000
   6.750   1.0048   0.02422   0.01445  -0.0415   0.3100   1.0000
   7.000   1.0273   0.02465   0.01485  -0.0407   0.3061   1.0000
   7.250   1.0511   0.02508   0.01518  -0.0401   0.3029   1.0000
   7.500   1.0713   0.02569   0.01586  -0.0391   0.2990   1.0000
   7.750   1.0905   0.02630   0.01654  -0.0381   0.2947   1.0000
   8.000   1.1110   0.02683   0.01708  -0.0371   0.2908   1.0000
   8.250   1.1329   0.02729   0.01751  -0.0363   0.2874   1.0000
   8.500   1.1549   0.02783   0.01799  -0.0356   0.2844   1.0000
   8.750   1.1697   0.02865   0.01896  -0.0341   0.2806   1.0000
   9.000   1.1861   0.02939   0.01978  -0.0328   0.2770   1.0000
   9.250   1.2039   0.03003   0.02045  -0.0316   0.2738   1.0000
   9.500   1.2240   0.03057   0.02096  -0.0307   0.2709   1.0000
   9.750   1.2453   0.03115   0.02149  -0.0300   0.2682   1.0000
  10.000   1.2510   0.03225   0.02278  -0.0277   0.2647   1.0000
  10.250   1.2580   0.03324   0.02388  -0.0254   0.2616   1.0000
  10.500   1.2680   0.03416   0.02486  -0.0236   0.2588   1.0000
  10.750   1.2816   0.03495   0.02568  -0.0221   0.2562   1.0000
  11.000   1.3003   0.03558   0.02627  -0.0213   0.2538   1.0000
  11.250   1.3099   0.03665   0.02739  -0.0197   0.2514   1.0000
  11.500   1.2997   0.03868   0.02963  -0.0171   0.2484   1.0000
  11.750   1.2940   0.04072   0.03183  -0.0154   0.2455   1.0000
  12.000   1.2942   0.04258   0.03379  -0.0142   0.2428   1.0000
  12.250   1.3028   0.04396   0.03521  -0.0135   0.2404   1.0000
  12.500   1.3208   0.04473   0.03596  -0.0129   0.2383   1.0000
  12.750   1.3289   0.04627   0.03754  -0.0123   0.2361   1.0000
  13.000   1.2465   0.05595   0.04768  -0.0130   0.2319   1.0000
  13.250   1.0572   0.08355   0.07575  -0.0236   0.2197   1.0000
  13.500   1.1063   0.07951   0.07166  -0.0211   0.2204   1.0000
  13.750   1.1641   0.07455   0.06664  -0.0181   0.2209   1.0000
  15.250   0.8845   0.14581   0.13854  -0.0505   0.1720   1.0000
  15.500   0.8956   0.14774   0.14050  -0.0511   0.1697   1.0000
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