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EPPLER 1214 AIRFOIL (e1214-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1214 AIRFOIL (e1214-il)
Reynolds number: 50,000
Max Cl/Cd: 18.63 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1214-il-50000-n5.txt
Download as CSV file: xf-e1214-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.5262   0.13276   0.12471  -0.0158   1.0000   0.0880
 -15.000  -0.5145   0.13122   0.12319  -0.0161   1.0000   0.0917
 -14.750  -0.5312   0.12326   0.11526  -0.0198   1.0000   0.0971
 -14.500  -0.5260   0.12048   0.11250  -0.0208   1.0000   0.1024
 -14.250  -0.5262   0.11659   0.10864  -0.0223   1.0000   0.1080
 -14.000  -0.5481   0.10837   0.10045  -0.0262   1.0000   0.1160
 -13.750  -0.5241   0.10979   0.10188  -0.0249   1.0000   0.1214
 -13.250  -0.5462   0.09888   0.09102  -0.0296   1.0000   0.1383
 -13.000  -0.5169   0.10118   0.09330  -0.0276   1.0000   0.1444
 -12.750  -0.5205   0.09735   0.08949  -0.0290   1.0000   0.1528
 -12.500  -0.5425   0.09051   0.08267  -0.0322   1.0000   0.1631
 -12.000  -0.5220   0.08804   0.08020  -0.0319   1.0000   0.1781
 -11.500  -0.5104   0.08403   0.07619  -0.0323   1.0000   0.1940
 -11.250  -0.5403   0.07685   0.06906  -0.0355   1.0000   0.2053
 -10.750  -0.5348   0.07236   0.06459  -0.0359   1.0000   0.2214
 -10.250  -0.5384   0.06685   0.05911  -0.0367   1.0000   0.2381
 -10.000  -0.5765   0.05975   0.05205  -0.0395   1.0000   0.2496
  -9.750  -0.5636   0.05911   0.05144  -0.0384   1.0000   0.2557
  -9.500  -0.6239   0.05235   0.04475  -0.0383   1.0000   0.2647
  -9.250  -0.6740   0.04803   0.04046  -0.0344   1.0000   0.2711
  -9.000  -0.6466   0.04891   0.04141  -0.0328   1.0000   0.2769
  -8.750  -0.6977   0.04529   0.03777  -0.0276   1.0000   0.2834
  -8.500  -0.6625   0.04503   0.03749  -0.0295   0.9766   0.2910
  -8.250  -0.6359   0.04309   0.03530  -0.0328   0.9407   0.3017
  -8.000  -0.5877   0.04264   0.03474  -0.0363   0.9161   0.3096
  -7.750  -0.5559   0.04122   0.03307  -0.0389   0.8892   0.3189
  -7.500  -0.5258   0.03999   0.03160  -0.0406   0.8641   0.3267
  -7.250  -0.4916   0.03957   0.03102  -0.0415   0.8406   0.3333
  -7.000  -0.4886   0.03748   0.02847  -0.0404   0.8186   0.3424
  -6.750  -0.4558   0.03752   0.02846  -0.0401   0.7979   0.3469
  -6.500  -0.4336   0.03708   0.02787  -0.0391   0.7785   0.3528
  -6.250  -0.4239   0.03583   0.02629  -0.0376   0.7608   0.3604
  -6.000  -0.4022   0.03534   0.02567  -0.0365   0.7440   0.3655
  -5.750  -0.3784   0.03503   0.02524  -0.0355   0.7286   0.3707
  -5.500  -0.3604   0.03430   0.02428  -0.0343   0.7144   0.3770
  -5.250  -0.3451   0.03345   0.02317  -0.0331   0.6998   0.3835
  -5.000  -0.3196   0.03320   0.02287  -0.0322   0.6865   0.3879
  -4.750  -0.2973   0.03278   0.02232  -0.0313   0.6736   0.3933
  -4.500  -0.2786   0.03216   0.02148  -0.0303   0.6608   0.3998
  -4.250  -0.2561   0.03166   0.02079  -0.0294   0.6500   0.4053
  -4.000  -0.2323   0.03144   0.02055  -0.0286   0.6372   0.4101
  -3.750  -0.2085   0.03104   0.01996  -0.0278   0.6275   0.4160
  -3.500  -0.1884   0.03060   0.01934  -0.0271   0.6153   0.4227
  -3.250  -0.1620   0.03032   0.01896  -0.0265   0.6063   0.4278
  -3.000  -0.1383   0.03016   0.01882  -0.0259   0.5946   0.4334
  -2.750  -0.1135   0.02983   0.01828  -0.0253   0.5862   0.4402
  -2.500  -0.0909   0.02963   0.01801  -0.0247   0.5752   0.4465
  -2.250  -0.0646   0.02946   0.01779  -0.0241   0.5668   0.4523
  -2.000  -0.0409   0.02937   0.01764  -0.0235   0.5573   0.4593
  -1.750  -0.0167   0.02918   0.01730  -0.0230   0.5486   0.4669
  -1.500   0.0094   0.02910   0.01721  -0.0225   0.5407   0.4730
  -1.250   0.0331   0.02910   0.01719  -0.0219   0.5315   0.4807
  -1.000   0.0592   0.02895   0.01689  -0.0215   0.5247   0.4892
  -0.750   0.0832   0.02906   0.01708  -0.0209   0.5161   0.4966
  -0.500   0.1081   0.02905   0.01698  -0.0205   0.5083   0.5059
  -0.250   0.1359   0.02896   0.01681  -0.0201   0.5026   0.5147
   0.000   0.1578   0.02923   0.01717  -0.0195   0.4938   0.5245
   0.250   0.1831   0.02927   0.01718  -0.0190   0.4871   0.5349
   0.500   0.2094   0.02927   0.01711  -0.0185   0.4816   0.5464
   0.750   0.2300   0.02963   0.01761  -0.0177   0.4734   0.5576
   1.000   0.2547   0.02973   0.01769  -0.0171   0.4673   0.5718
   1.250   0.2820   0.02969   0.01763  -0.0166   0.4628   0.5860
   1.500   0.2996   0.03025   0.01839  -0.0155   0.4549   0.6010
   1.750   0.3226   0.03045   0.01865  -0.0147   0.4489   0.6192
   2.000   0.3489   0.03045   0.01866  -0.0140   0.4443   0.6402
   2.250   0.3668   0.03099   0.01940  -0.0128   0.4380   0.6622
   2.500   0.3859   0.03144   0.02006  -0.0115   0.4318   0.6877
   2.750   0.4108   0.03156   0.02028  -0.0106   0.4271   0.7200
   3.000   0.4409   0.03157   0.02036  -0.0102   0.4231   0.7596
   3.250   0.4586   0.03271   0.02187  -0.0097   0.4155   0.8036
   3.500   0.5008   0.03324   0.02252  -0.0122   0.4097   0.8567
   3.750   0.5607   0.03337   0.02256  -0.0173   0.4051   0.9090
   4.000   0.5989   0.03498   0.02435  -0.0214   0.3973   0.9596
   4.250   0.6421   0.03585   0.02518  -0.0255   0.3914   1.0000
   4.500   0.6567   0.03627   0.02544  -0.0238   0.3881   1.0000
   4.750   0.6790   0.03645   0.02543  -0.0227   0.3854   1.0000
   5.000   0.6572   0.03912   0.02829  -0.0183   0.3788   1.0000
   5.250   0.6575   0.04060   0.02977  -0.0157   0.3738   1.0000
   5.500   0.6736   0.04124   0.03031  -0.0143   0.3703   1.0000
   5.750   0.6990   0.04144   0.03039  -0.0136   0.3677   1.0000
   6.000   0.6313   0.04720   0.03637  -0.0074   0.3595   1.0000
   6.250   0.6077   0.05036   0.03953  -0.0043   0.3538   1.0000
   6.500   0.6273   0.05094   0.04004  -0.0033   0.3509   1.0000
   6.750   0.6617   0.05058   0.03958  -0.0029   0.3490   1.0000
   7.250   0.5616   0.06504   0.05416  -0.0027   0.3317   1.0000
   7.750   0.5146   0.07622   0.06536  -0.0047   0.3174   1.0000
   8.000   0.5307   0.07760   0.06671  -0.0043   0.3150   1.0000
   8.250   0.5525   0.07838   0.06744  -0.0037   0.3132   1.0000
   8.500   0.5071   0.08663   0.07575  -0.0062   0.3048   1.0000
   8.750   0.5140   0.08904   0.07815  -0.0064   0.3010   1.0000
   9.000   0.5289   0.09069   0.07977  -0.0062   0.2984   1.0000
   9.250   0.5478   0.09197   0.08104  -0.0059   0.2965   1.0000
   9.500   0.5255   0.09786   0.08696  -0.0077   0.2912   1.0000
   9.750   0.5223   0.10152   0.09064  -0.0086   0.2869   1.0000
  10.000   0.5317   0.10382   0.09294  -0.0089   0.2836   1.0000
  10.250   0.5461   0.10572   0.09483  -0.0089   0.2813   1.0000
  10.500   0.5651   0.10712   0.09622  -0.0086   0.2794   1.0000
  10.750   0.5455   0.11271   0.10186  -0.0107   0.2744   1.0000
  11.000   0.5450   0.11613   0.10531  -0.0117   0.2704   1.0000
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