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EPPLER E1212MOD AIRFOIL (e1212mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER E1212MOD AIRFOIL (e1212mod-il)
Reynolds number: 100,000
Max Cl/Cd: 39.72 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1212mod-il-100000-n5.txt
Download as CSV file: xf-e1212mod-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E1212MOD 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7953   0.04472   0.03866  -0.0644   1.0000   0.1008
 -11.250  -0.8304   0.03981   0.03354  -0.0656   1.0000   0.1021
 -11.000  -0.8488   0.03712   0.03065  -0.0634   1.0000   0.1044
 -10.750  -0.8386   0.03654   0.03010  -0.0621   1.0000   0.1071
 -10.500  -0.8341   0.03527   0.02871  -0.0605   1.0000   0.1105
 -10.250  -0.8299   0.03377   0.02703  -0.0588   1.0000   0.1141
 -10.000  -0.8150   0.03336   0.02665  -0.0574   1.0000   0.1168
  -9.750  -0.8049   0.03241   0.02557  -0.0558   1.0000   0.1206
  -9.500  -0.7957   0.03139   0.02440  -0.0540   1.0000   0.1242
  -9.250  -0.7704   0.03105   0.02409  -0.0542   0.9879   0.1276
  -9.000  -0.7375   0.02982   0.02252  -0.0567   0.9503   0.1335
  -8.750  -0.6968   0.02954   0.02225  -0.0594   0.9167   0.1379
  -8.500  -0.6603   0.02884   0.02127  -0.0618   0.8847   0.1440
  -8.250  -0.6286   0.02837   0.02064  -0.0627   0.8562   0.1488
  -8.000  -0.6004   0.02818   0.02033  -0.0628   0.8321   0.1533
  -7.750  -0.5790   0.02749   0.01926  -0.0620   0.8110   0.1584
  -7.500  -0.5548   0.02708   0.01876  -0.0614   0.7918   0.1619
  -7.250  -0.5301   0.02681   0.01842  -0.0606   0.7738   0.1654
  -7.000  -0.5072   0.02635   0.01775  -0.0597   0.7570   0.1692
  -6.750  -0.4854   0.02573   0.01680  -0.0588   0.7405   0.1734
  -6.500  -0.4609   0.02531   0.01636  -0.0581   0.7238   0.1767
  -6.250  -0.4360   0.02504   0.01605  -0.0574   0.7075   0.1803
  -6.000  -0.4117   0.02468   0.01552  -0.0566   0.6923   0.1847
  -5.750  -0.3880   0.02420   0.01474  -0.0559   0.6771   0.1891
  -5.500  -0.3626   0.02378   0.01433  -0.0553   0.6616   0.1924
  -5.250  -0.3371   0.02345   0.01395  -0.0546   0.6478   0.1956
  -5.000  -0.3118   0.02307   0.01343  -0.0540   0.6350   0.1990
  -4.750  -0.2862   0.02266   0.01286  -0.0534   0.6224   0.2026
  -4.500  -0.2607   0.02225   0.01217  -0.0528   0.6119   0.2059
  -4.250  -0.2345   0.02188   0.01183  -0.0523   0.6006   0.2086
  -3.750  -0.1821   0.02134   0.01114  -0.0512   0.5814   0.2152
  -3.500  -0.1557   0.02107   0.01071  -0.0506   0.5728   0.2190
  -3.250  -0.1290   0.02080   0.01028  -0.0501   0.5644   0.2225
  -3.000  -0.1027   0.02057   0.01007  -0.0496   0.5556   0.2258
  -2.750  -0.0764   0.02043   0.00984  -0.0490   0.5483   0.2298
  -2.500  -0.0497   0.02027   0.00965  -0.0486   0.5399   0.2347
  -2.000   0.0035   0.02000   0.00924  -0.0475   0.5249   0.2442
  -1.750   0.0301   0.01989   0.00915  -0.0471   0.5167   0.2498
  -1.500   0.0569   0.01981   0.00895  -0.0465   0.5093   0.2570
  -1.250   0.0833   0.01976   0.00890  -0.0460   0.5022   0.2637
  -1.000   0.1100   0.01970   0.00883  -0.0455   0.4941   0.2728
  -0.750   0.1365   0.01964   0.00874  -0.0450   0.4871   0.2814
  -0.500   0.1631   0.01962   0.00866  -0.0445   0.4801   0.2919
  -0.250   0.1893   0.01955   0.00865  -0.0439   0.4720   0.3019
   0.000   0.2160   0.01954   0.00855  -0.0434   0.4652   0.3143
   0.250   0.2420   0.01949   0.00857  -0.0428   0.4585   0.3256
   0.500   0.2683   0.01948   0.00859  -0.0423   0.4507   0.3384
   0.750   0.2945   0.01945   0.00858  -0.0417   0.4441   0.3512
   1.000   0.3208   0.01946   0.00861  -0.0412   0.4377   0.3638
   1.250   0.3470   0.01948   0.00868  -0.0406   0.4300   0.3779
   1.500   0.3730   0.01946   0.00870  -0.0400   0.4236   0.3924
   1.750   0.3991   0.01948   0.00876  -0.0395   0.4171   0.4083
   2.000   0.4252   0.01951   0.00887  -0.0389   0.4098   0.4257
   2.250   0.4516   0.01951   0.00888  -0.0384   0.4039   0.4456
   2.500   0.4778   0.01953   0.00898  -0.0379   0.3981   0.4689
   2.750   0.5033   0.01954   0.00915  -0.0373   0.3918   0.4989
   3.000   0.5279   0.01945   0.00927  -0.0364   0.3865   0.5479
   3.250   0.5508   0.01924   0.00938  -0.0350   0.3822   0.6377
   3.500   0.5804   0.01903   0.00977  -0.0345   0.3758   0.8039
   3.750   0.6571   0.01914   0.00996  -0.0434   0.3678   0.9924
   4.000   0.6850   0.01940   0.01002  -0.0434   0.3636   1.0000
   4.250   0.7070   0.01976   0.01037  -0.0423   0.3583   1.0000
   4.500   0.7295   0.02008   0.01064  -0.0413   0.3536   1.0000
   4.750   0.7524   0.02040   0.01086  -0.0403   0.3497   1.0000
   5.000   0.7759   0.02072   0.01104  -0.0394   0.3464   1.0000
   5.250   0.7987   0.02113   0.01142  -0.0384   0.3428   1.0000
   5.500   0.8209   0.02157   0.01188  -0.0375   0.3388   1.0000
   5.750   0.8436   0.02199   0.01228  -0.0365   0.3352   1.0000
   6.000   0.8667   0.02240   0.01263  -0.0357   0.3320   1.0000
   6.250   0.8904   0.02279   0.01295  -0.0349   0.3292   1.0000
   6.500   0.9149   0.02321   0.01325  -0.0342   0.3267   1.0000
   6.750   0.9353   0.02379   0.01393  -0.0331   0.3232   1.0000
   7.000   0.9563   0.02434   0.01453  -0.0321   0.3198   1.0000
   7.250   0.9780   0.02487   0.01507  -0.0311   0.3168   1.0000
   7.500   1.0004   0.02537   0.01557  -0.0302   0.3142   1.0000
   7.750   1.0236   0.02587   0.01603  -0.0295   0.3120   1.0000
   8.000   1.0475   0.02637   0.01649  -0.0288   0.3100   1.0000
   8.250   1.0701   0.02700   0.01710  -0.0281   0.3080   1.0000
   8.500   1.0870   0.02782   0.01806  -0.0267   0.3056   1.0000
   8.750   1.1041   0.02864   0.01900  -0.0255   0.3032   1.0000
   9.000   1.1215   0.02946   0.01991  -0.0242   0.3008   1.0000
   9.250   1.1395   0.03020   0.02071  -0.0231   0.2984   1.0000
   9.500   1.1592   0.03079   0.02131  -0.0220   0.2958   1.0000
   9.750   1.1823   0.03121   0.02168  -0.0213   0.2933   1.0000
  10.000   1.2087   0.03161   0.02199  -0.0210   0.2909   1.0000
  10.250   1.2112   0.03288   0.02350  -0.0183   0.2879   1.0000
  10.500   1.2150   0.03406   0.02485  -0.0159   0.2847   1.0000
  10.750   1.2213   0.03505   0.02593  -0.0137   0.2817   1.0000
  11.000   1.2331   0.03572   0.02663  -0.0118   0.2788   1.0000
  11.250   1.2553   0.03600   0.02685  -0.0110   0.2760   1.0000
  11.500   1.2790   0.03634   0.02712  -0.0103   0.2733   1.0000
  11.750   1.2525   0.03873   0.02978  -0.0060   0.2704   1.0000
  12.000   1.2264   0.04181   0.03308  -0.0035   0.2671   1.0000
  12.250   1.2065   0.04513   0.03656  -0.0024   0.2640   1.0000
  12.500   1.2095   0.04696   0.03843  -0.0017   0.2613   1.0000
  12.750   1.2383   0.04670   0.03813  -0.0010   0.2591   1.0000
  13.000   1.2739   0.04600   0.03735  -0.0003   0.2570   1.0000
  13.250   1.0133   0.07827   0.07030  -0.0110   0.2416   1.0000
  13.500   1.0494   0.07617   0.06819  -0.0093   0.2410   1.0000
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