Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 715 AIRFOIL (e715-il)
Reynolds number: 200,000
Max Cl/Cd: 74.88 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e715-il-200000-n5.txt
Download as CSV file: xf-e715-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 715 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.6437   0.10696   0.10333  -0.0116   1.0000   0.0097
 -14.000  -0.6760   0.09456   0.09076  -0.0190   1.0000   0.0096
 -13.750  -0.6936   0.08630   0.08240  -0.0243   1.0000   0.0094
 -13.500  -0.7148   0.07794   0.07390  -0.0297   1.0000   0.0093
 -13.250  -0.7319   0.07095   0.06673  -0.0345   1.0000   0.0094
 -13.000  -0.7466   0.06496   0.06060  -0.0383   1.0000   0.0093
 -12.750  -0.7589   0.05959   0.05505  -0.0419   1.0000   0.0094
 -12.500  -0.7694   0.05481   0.05013  -0.0446   1.0000   0.0094
 -12.250  -0.7699   0.05021   0.04519  -0.0494   0.8603   0.0094
 -12.000  -0.7746   0.04669   0.04125  -0.0512   0.8046   0.0097
 -11.750  -0.7785   0.04346   0.03771  -0.0524   0.7760   0.0097
 -11.500  -0.7800   0.04061   0.03465  -0.0535   0.7554   0.0099
 -11.000  -0.7802   0.03598   0.02971  -0.0549   0.7252   0.0105
 -10.750  -0.7794   0.03423   0.02779  -0.0542   0.7136   0.0108
 -10.500  -0.7754   0.03281   0.02619  -0.0529   0.7037   0.0111
 -10.250  -0.7666   0.03126   0.02443  -0.0519   0.6946   0.0116
 -10.000  -0.7552   0.02977   0.02273  -0.0510   0.6865   0.0120
  -9.750  -0.7420   0.02837   0.02111  -0.0501   0.6790   0.0125
  -9.500  -0.7277   0.02702   0.01961  -0.0492   0.6721   0.0129
  -9.250  -0.7118   0.02583   0.01830  -0.0485   0.6656   0.0135
  -9.000  -0.6938   0.02480   0.01713  -0.0479   0.6603   0.0142
  -8.750  -0.6746   0.02377   0.01596  -0.0472   0.6547   0.0152
  -8.500  -0.6550   0.02276   0.01480  -0.0466   0.6497   0.0165
  -8.250  -0.6338   0.02199   0.01392  -0.0462   0.6455   0.0182
  -8.000  -0.6115   0.02120   0.01300  -0.0458   0.6405   0.0207
  -7.750  -0.5891   0.02044   0.01217  -0.0454   0.6358   0.0235
  -7.500  -0.5664   0.01969   0.01131  -0.0449   0.6318   0.0270
  -7.250  -0.5424   0.01909   0.01061  -0.0446   0.6278   0.0318
  -7.000  -0.5185   0.01842   0.00990  -0.0444   0.6238   0.0380
  -6.750  -0.4942   0.01780   0.00923  -0.0441   0.6202   0.0459
  -6.500  -0.4696   0.01723   0.00863  -0.0438   0.6170   0.0563
  -6.250  -0.4445   0.01672   0.00807  -0.0436   0.6142   0.0699
  -6.000  -0.4193   0.01616   0.00757  -0.0435   0.6107   0.0881
  -5.750  -0.3939   0.01565   0.00710  -0.0433   0.6072   0.1120
  -5.500  -0.3684   0.01514   0.00667  -0.0432   0.6039   0.1418
  -5.250  -0.3428   0.01467   0.00627  -0.0431   0.6011   0.1765
  -5.000  -0.3170   0.01425   0.00592  -0.0430   0.5987   0.2141
  -4.750  -0.2908   0.01383   0.00563  -0.0429   0.5958   0.2554
  -4.500  -0.2646   0.01347   0.00541  -0.0428   0.5929   0.3007
  -4.250  -0.2380   0.01323   0.00530  -0.0426   0.5902   0.3456
  -4.000  -0.2107   0.01315   0.00526  -0.0425   0.5875   0.3814
  -3.750  -0.1829   0.01315   0.00522  -0.0423   0.5850   0.4077
  -3.500  -0.1548   0.01321   0.00520  -0.0423   0.5827   0.4271
  -3.250  -0.1263   0.01326   0.00521  -0.0423   0.5801   0.4427
  -3.000  -0.0977   0.01332   0.00518  -0.0423   0.5775   0.4561
  -2.750  -0.0693   0.01338   0.00518  -0.0423   0.5751   0.4673
  -2.500  -0.0409   0.01343   0.00516  -0.0422   0.5726   0.4763
  -2.250  -0.0123   0.01349   0.00508  -0.0423   0.5704   0.4856
  -2.000   0.0159   0.01352   0.00507  -0.0422   0.5684   0.4922
  -1.750   0.0446   0.01358   0.00505  -0.0423   0.5661   0.5004
  -1.500   0.0730   0.01360   0.00508  -0.0424   0.5637   0.5065
  -1.250   0.1016   0.01364   0.00508  -0.0425   0.5613   0.5130
  -1.000   0.1301   0.01366   0.00505  -0.0426   0.5588   0.5187
  -0.750   0.1585   0.01367   0.00504  -0.0426   0.5565   0.5237
  -0.500   0.1870   0.01371   0.00501  -0.0427   0.5545   0.5295
  -0.250   0.2155   0.01376   0.00500  -0.0427   0.5529   0.5345
   0.000   0.2439   0.01379   0.00506  -0.0428   0.5507   0.5392
   0.250   0.2724   0.01383   0.00512  -0.0430   0.5481   0.5441
   0.500   0.3010   0.01388   0.00515  -0.0431   0.5455   0.5485
   0.750   0.3293   0.01389   0.00520  -0.0432   0.5432   0.5523
   1.000   0.3577   0.01394   0.00524  -0.0433   0.5412   0.5564
   1.250   0.3863   0.01399   0.00527  -0.0434   0.5392   0.5608
   1.500   0.4147   0.01405   0.00530  -0.0435   0.5374   0.5647
   1.750   0.4428   0.01410   0.00544  -0.0437   0.5348   0.5685
   2.000   0.4709   0.01418   0.00558  -0.0438   0.5322   0.5729
   2.250   0.4992   0.01426   0.00570  -0.0439   0.5296   0.5775
   2.500   0.5273   0.01431   0.00579  -0.0440   0.5271   0.5813
   2.750   0.5554   0.01436   0.00589  -0.0441   0.5249   0.5858
   3.000   0.5837   0.01443   0.00596  -0.0441   0.5229   0.5909
   3.250   0.6117   0.01452   0.00612  -0.0442   0.5204   0.5957
   3.500   0.6391   0.01461   0.00635  -0.0443   0.5171   0.6006
   3.750   0.6668   0.01469   0.00651  -0.0443   0.5138   0.6066
   4.000   0.6946   0.01473   0.00663  -0.0443   0.5108   0.6128
   4.250   0.7225   0.01475   0.00670  -0.0443   0.5081   0.6198
   4.500   0.7500   0.01482   0.00687  -0.0443   0.5048   0.6273
   4.750   0.7768   0.01489   0.00711  -0.0442   0.5003   0.6366
   5.000   0.8040   0.01490   0.00724  -0.0441   0.4963   0.6483
   5.250   0.8315   0.01485   0.00728  -0.0440   0.4927   0.6635
   5.500   0.8576   0.01487   0.00750  -0.0438   0.4880   0.6852
   5.750   0.8835   0.01480   0.00769  -0.0434   0.4826   0.7236
   6.000   0.9287   0.01430   0.00769  -0.0466   0.4774   1.0000
   6.250   0.9548   0.01445   0.00795  -0.0465   0.4710   1.0000
   6.500   0.9814   0.01452   0.00807  -0.0463   0.4648   1.0000
   6.750   1.0077   0.01461   0.00823  -0.0461   0.4580   1.0000
   7.000   1.0337   0.01469   0.00837  -0.0459   0.4498   1.0000
   7.250   1.0593   0.01481   0.00858  -0.0456   0.4403   1.0000
   7.500   1.0849   0.01490   0.00871  -0.0452   0.4304   1.0000
   7.750   1.1098   0.01502   0.00888  -0.0448   0.4182   1.0000
   8.000   1.1338   0.01520   0.00910  -0.0443   0.4030   1.0000
   8.250   1.1569   0.01545   0.00939  -0.0437   0.3835   1.0000
   8.500   1.1777   0.01582   0.00968  -0.0428   0.3592   1.0000
   8.750   1.1955   0.01640   0.01015  -0.0416   0.3295   1.0000
   9.000   1.2092   0.01723   0.01083  -0.0401   0.2973   1.0000
   9.250   1.2192   0.01827   0.01174  -0.0382   0.2669   1.0000
   9.500   1.2258   0.01943   0.01278  -0.0359   0.2406   1.0000
   9.750   1.2292   0.02065   0.01392  -0.0334   0.2183   1.0000
  10.000   1.2253   0.02204   0.01526  -0.0302   0.2008   1.0000
  10.250   1.2211   0.02384   0.01702  -0.0280   0.1851   1.0000
  10.500   1.2185   0.02591   0.01905  -0.0266   0.1697   1.0000
  10.750   1.2168   0.02811   0.02123  -0.0256   0.1555   1.0000
  11.000   1.2150   0.03045   0.02353  -0.0247   0.1417   1.0000
  11.250   1.2140   0.03278   0.02584  -0.0240   0.1293   1.0000
  11.500   1.2139   0.03508   0.02813  -0.0234   0.1177   1.0000
  11.750   1.2140   0.03739   0.03044  -0.0228   0.1072   1.0000
  12.000   1.2140   0.03975   0.03279  -0.0223   0.0979   1.0000
  12.250   1.2127   0.04227   0.03529  -0.0219   0.0893   1.0000
  12.500   1.2147   0.04452   0.03757  -0.0215   0.0813   1.0000
  12.750   1.2150   0.04697   0.04003  -0.0212   0.0744   1.0000
  13.000   1.2156   0.04943   0.04251  -0.0210   0.0678   1.0000
  13.250   1.2169   0.05192   0.04503  -0.0208   0.0621   1.0000
  13.500   1.2177   0.05457   0.04770  -0.0208   0.0566   1.0000
  13.750   1.2195   0.05718   0.05035  -0.0209   0.0518   1.0000
  14.000   1.2205   0.05995   0.05317  -0.0211   0.0472   1.0000
  14.250   1.2212   0.06281   0.05607  -0.0213   0.0437   1.0000
  14.500   1.2234   0.06557   0.05890  -0.0216   0.0402   1.0000
  14.750   1.2225   0.06877   0.06214  -0.0221   0.0373   1.0000
  15.000   1.2238   0.07176   0.06521  -0.0226   0.0346   1.0000
  15.250   1.2246   0.07487   0.06840  -0.0232   0.0319   1.0000
  15.500   1.2227   0.07843   0.07199  -0.0240   0.0298   1.0000
  15.750   1.2229   0.08177   0.07543  -0.0248   0.0279   1.0000
  16.000   1.2231   0.08516   0.07892  -0.0256   0.0261   1.0000
  16.250   1.2212   0.08893   0.08276  -0.0267   0.0244   1.0000
  16.500   1.2175   0.09305   0.08693  -0.0280   0.0230   1.0000
  16.750   1.2175   0.09667   0.09070  -0.0291   0.0215   1.0000
  17.000   1.2157   0.10062   0.09476  -0.0305   0.0204   1.0000
  17.250   1.2119   0.10498   0.09920  -0.0321   0.0193   1.0000
  17.500   1.2064   0.10970   0.10399  -0.0340   0.0185   1.0000
  17.750   1.2045   0.11387   0.10828  -0.0356   0.0176   1.0000
  18.000   1.2020   0.11820   0.11274  -0.0374   0.0166   1.0000
  18.250   1.1981   0.12284   0.11749  -0.0395   0.0158   1.0000
  18.500   1.1931   0.12777   0.12251  -0.0419   0.0151   1.0000
  18.750   1.1874   0.13289   0.12770  -0.0444   0.0146   1.0000
<< Back to EPPLER 715 AIRFOIL (e715-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 715 AIRFOIL (e715-il)