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EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 50,000
Max Cl/Cd: 3.07 at α=11.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1214-il-50000.txt
Download as CSV file: xf-e1214-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1214 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3243   0.13115   0.12355  -0.0042   1.0000   0.3614
 -11.500  -0.2898   0.12502   0.11737  -0.0046   1.0000   0.3729
 -11.250  -0.3244   0.12656   0.11899  -0.0046   1.0000   0.3822
 -11.000  -0.2769   0.11959   0.11195  -0.0050   1.0000   0.3970
 -10.750  -0.2803   0.11721   0.10961  -0.0053   1.0000   0.4062
 -10.500  -0.2729   0.11528   0.10768  -0.0051   1.0000   0.4215
 -10.250  -0.2520   0.11093   0.10333  -0.0056   1.0000   0.4312
 -10.000  -0.2807   0.11218   0.10467  -0.0044   1.0000   0.4445
  -9.750  -0.2317   0.10571   0.09815  -0.0057   1.0000   0.4573
  -9.500  -0.2384   0.10409   0.09659  -0.0053   1.0000   0.4689
  -9.250  -0.2299   0.10240   0.09492  -0.0048   1.0000   0.4854
  -9.000  -0.2045   0.09817   0.09072  -0.0056   1.0000   0.4953
  -8.750  -0.2227   0.09822   0.09088  -0.0040   1.0000   0.5098
  -8.500  -0.1843   0.09383   0.08650  -0.0053   1.0000   0.5242
  -8.250  -0.1768   0.09152   0.08428  -0.0052   1.0000   0.5364
  -8.000  -0.2010   0.09265   0.08559  -0.0023   1.0000   0.5522
  -7.750  -0.1550   0.08775   0.08077  -0.0047   1.0000   0.5652
  -7.500  -0.2300   0.09313   0.08657   0.0045   1.0000   0.5737
  -7.250  -0.1681   0.08824   0.08160  -0.0041   0.9801   0.5934
  -7.000  -0.1162   0.08418   0.07742  -0.0126   0.9559   0.6157
  -6.750  -0.0598   0.07999   0.07309  -0.0214   0.9354   0.6378
  -6.500  -0.0063   0.07625   0.06916  -0.0294   0.9125   0.6599
  -6.250   0.0544   0.07185   0.06450  -0.0369   0.8836   0.6796
  -6.000   0.0966   0.06866   0.06108  -0.0409   0.8555   0.6945
  -5.750   0.1149   0.06723   0.05950  -0.0411   0.8312   0.7104
  -5.250  -0.0514   0.06058   0.05280  -0.0418   0.8146   0.5311
  -5.000  -0.0519   0.05855   0.05068  -0.0411   0.7983   0.5287
  -4.750  -0.0630   0.05676   0.04887  -0.0396   0.7833   0.5278
  -4.500  -0.0798   0.05463   0.04669  -0.0380   0.7715   0.5276
  -4.250  -0.1021   0.05230   0.04430  -0.0363   0.7595   0.5282
  -4.000  -0.1335   0.04978   0.04166  -0.0342   0.7493   0.5304
  -3.750  -0.0854   0.04991   0.04174  -0.0336   0.7352   0.5372
  -3.500  -0.0912   0.04889   0.04071  -0.0318   0.7225   0.5410
  -3.250  -0.0919   0.04718   0.03883  -0.0304   0.7138   0.5463
  -3.000  -0.1120   0.04595   0.03749  -0.0283   0.7025   0.5512
  -2.750  -0.0823   0.04536   0.03683  -0.0274   0.6928   0.5573
  -2.500  -0.0813   0.04537   0.03685  -0.0255   0.6807   0.5624
  -2.250  -0.0682   0.04433   0.03563  -0.0247   0.6725   0.5699
  -2.000  -0.0701   0.04433   0.03557  -0.0229   0.6618   0.5756
  -1.750  -0.0460   0.04419   0.03541  -0.0218   0.6526   0.5827
  -1.500  -0.0410   0.04437   0.03552  -0.0203   0.6436   0.5896
  -1.250  -0.0368   0.04443   0.03548  -0.0191   0.6345   0.5967
  -1.000   0.0011   0.04393   0.03492  -0.0187   0.6279   0.6058
  -0.750  -0.0202   0.04561   0.03666  -0.0159   0.6173   0.6112
  -0.500   0.0033   0.04540   0.03635  -0.0154   0.6101   0.6208
  -0.250   0.0104   0.04634   0.03731  -0.0139   0.6031   0.6285
   0.000  -0.0077   0.04815   0.03912  -0.0115   0.5954   0.6351
   0.250   0.0222   0.04810   0.03904  -0.0112   0.5886   0.6464
   0.500   0.0259   0.04933   0.04023  -0.0099   0.5826   0.6567
   0.750  -0.0088   0.05195   0.04286  -0.0067   0.5788   0.6619
   1.000  -0.0187   0.05375   0.04472  -0.0046   0.5753   0.6697
   1.250  -0.0086   0.05485   0.04576  -0.0040   0.5705   0.6829
   1.500   0.0348   0.05495   0.04586  -0.0045   0.5634   0.7020
   1.750   0.0237   0.05728   0.04826  -0.0030   0.5629   0.7128
   2.000   0.0223   0.05929   0.05028  -0.0023   0.5629   0.7282
   2.250   0.0255   0.06118   0.05222  -0.0018   0.5632   0.7468
   2.500   0.0366   0.06303   0.05420  -0.0017   0.5650   0.7699
   2.750  -0.0998   0.06955   0.06088  -0.0021   0.7086   0.7508
   3.000  -0.0771   0.07068   0.06219  -0.0023   0.6956   0.7820
   3.250  -0.0617   0.07183   0.06360  -0.0023   0.6859   0.8227
   3.500   0.0319   0.07666   0.06894  -0.0167   0.6720   0.9269
   3.750   0.0569   0.07785   0.06986  -0.0236   0.6586   1.0000
   4.000   0.0971   0.08119   0.07281  -0.0273   0.6504   1.0000
   4.250   0.0881   0.08124   0.07268  -0.0252   0.6382   1.0000
   4.500   0.1211   0.08429   0.07550  -0.0270   0.6300   1.0000
   4.750   0.1195   0.08540   0.07648  -0.0258   0.6223   1.0000
   5.000   0.1371   0.08721   0.07814  -0.0259   0.6116   1.0000
   5.250   0.1826   0.09239   0.08317  -0.0288   0.6066   1.0000
   5.500   0.1586   0.09078   0.08148  -0.0253   0.5932   1.0000
   5.750   0.1948   0.09468   0.08526  -0.0270   0.5869   1.0000
   6.000   0.1829   0.09493   0.08544  -0.0251   0.5783   1.0000
   6.250   0.2016   0.09712   0.08754  -0.0253   0.5695   1.0000
   6.500   0.2428   0.10220   0.09253  -0.0275   0.5650   1.0000
   6.750   0.2191   0.10089   0.09116  -0.0248   0.5534   1.0000
   7.000   0.2474   0.10413   0.09432  -0.0257   0.5464   1.0000
   7.250   0.2630   0.10738   0.09752  -0.0261   0.5424   1.0000
   7.500   0.2554   0.10729   0.09739  -0.0248   0.5315   1.0000
   7.750   0.2831   0.11076   0.10080  -0.0257   0.5256   1.0000
   8.000   0.2884   0.11304   0.10303  -0.0255   0.5206   1.0000
   8.250   0.2910   0.11390   0.10386  -0.0249   0.5100   1.0000
   8.500   0.3203   0.11780   0.10772  -0.0259   0.5047   1.0000
   8.750   0.3235   0.12000   0.10988  -0.0258   0.5006   1.0000
   9.000   0.3227   0.12063   0.11050  -0.0253   0.4907   1.0000
   9.250   0.3493   0.12429   0.11413  -0.0261   0.4850   1.0000
   9.500   0.3596   0.12736   0.11717  -0.0264   0.4809   1.0000
   9.750   0.3545   0.12751   0.11732  -0.0259   0.4712   1.0000
  10.000   0.3768   0.13084   0.12063  -0.0265   0.4658   1.0000
  10.250   0.4160   0.13758   0.12735  -0.0281   0.4628   1.0000
  10.500   0.3850   0.13462   0.12438  -0.0268   0.4533   1.0000
  10.750   0.4044   0.13760   0.12737  -0.0273   0.4469   1.0000
  11.000   0.4377   0.14339   0.13315  -0.0284   0.4435   1.0000
  11.250   0.4169   0.14210   0.13185  -0.0281   0.4367   1.0000
  11.500   0.4298   0.14440   0.13416  -0.0284   0.4292   1.0000
  11.750   0.4590   0.14934   0.13911  -0.0292   0.4248   1.0000
  12.000   0.4541   0.15049   0.14026  -0.0296   0.4207   1.0000
  12.250   0.4567   0.15155   0.14132  -0.0300   0.4122   1.0000
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