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

EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 344 AIRFOIL (e344-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.86 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e344-il-1000000-n5.txt
Download as CSV file: xf-e344-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 344 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1858   0.09487   0.09150  -0.0638   0.5861   0.0078
 -10.250  -0.1963   0.08840   0.08504  -0.0656   0.5818   0.0058
 -10.000  -0.1947   0.08534   0.08197  -0.0669   0.5737   0.0059
  -9.750  -0.1800   0.08516   0.08174  -0.0671   0.5615   0.0064
  -9.500  -0.1967   0.07785   0.07446  -0.0703   0.5600   0.0060
  -9.250  -0.1913   0.07571   0.07231  -0.0714   0.5523   0.0062
  -8.750  -0.2196   0.06515   0.06176  -0.0786   0.5409   0.0061
  -8.500  -0.2272   0.06232   0.05891  -0.0788   0.5365   0.0063
  -8.250  -0.2540   0.05810   0.05464  -0.0763   0.5312   0.0061
  -8.000  -0.2537   0.05595   0.05242  -0.0752   0.5253   0.0063
  -7.750  -0.2718   0.05026   0.04659  -0.0728   0.5221   0.0061
  -7.500  -0.2682   0.04764   0.04386  -0.0712   0.5160   0.0063
  -7.000  -0.3386   0.02309   0.01789  -0.0552   0.5169   0.0059
  -6.500  -0.3069   0.01896   0.01309  -0.0512   0.5042   0.0059
  -6.250  -0.2858   0.01778   0.01167  -0.0499   0.4973   0.0059
  -6.000  -0.2638   0.01669   0.01037  -0.0489   0.4912   0.0059
  -5.750  -0.2404   0.01582   0.00933  -0.0480   0.4848   0.0059
  -5.250  -0.1919   0.01448   0.00771  -0.0465   0.4718   0.0059
  -5.000  -0.1675   0.01386   0.00695  -0.0458   0.4648   0.0059
  -4.750  -0.1430   0.01328   0.00627  -0.0450   0.4588   0.0059
  -4.500  -0.1181   0.01281   0.00572  -0.0444   0.4536   0.0059
  -4.250  -0.0935   0.01240   0.00523  -0.0437   0.4479   0.0060
  -4.000  -0.0687   0.01204   0.00479  -0.0430   0.4429   0.0060
  -3.750  -0.0436   0.01172   0.00443  -0.0424   0.4383   0.0061
  -3.500  -0.0187   0.01144   0.00409  -0.0417   0.4330   0.0062
  -3.250   0.0064   0.01122   0.00382  -0.0411   0.4278   0.0063
  -3.000   0.0318   0.01098   0.00355  -0.0406   0.4236   0.0064
  -2.750   0.0574   0.01080   0.00334  -0.0400   0.4187   0.0066
  -2.500   0.0829   0.01065   0.00314  -0.0395   0.4143   0.0067
  -2.250   0.1086   0.01049   0.00295  -0.0390   0.4107   0.0071
  -2.000   0.1347   0.01035   0.00279  -0.0386   0.4073   0.0074
  -1.750   0.1608   0.01024   0.00265  -0.0381   0.4035   0.0078
  -1.500   0.1866   0.01012   0.00250  -0.0377   0.3994   0.0085
  -1.250   0.2127   0.01005   0.00241  -0.0373   0.3955   0.0098
  -1.000   0.2392   0.00996   0.00231  -0.0369   0.3924   0.0113
  -0.750   0.2656   0.00988   0.00224  -0.0366   0.3891   0.0146
  -0.500   0.2918   0.00981   0.00218  -0.0363   0.3859   0.0222
  -0.250   0.3177   0.00973   0.00214  -0.0359   0.3828   0.0382
   0.000   0.3433   0.00962   0.00212  -0.0355   0.3798   0.0691
   0.250   0.3680   0.00938   0.00210  -0.0349   0.3776   0.1438
   0.500   0.3600   0.00712   0.00208  -0.0283   0.3757   0.8377
   0.750   0.3855   0.00729   0.00225  -0.0276   0.3727   0.8740
   1.000   0.4115   0.00744   0.00238  -0.0270   0.3698   0.8833
   1.250   0.4383   0.00758   0.00246  -0.0266   0.3670   0.8910
   1.500   0.4626   0.00776   0.00264  -0.0256   0.3643   0.8987
   1.750   0.4886   0.00791   0.00277  -0.0251   0.3625   0.9057
   2.000   0.5165   0.00797   0.00279  -0.0251   0.3601   0.9072
   2.250   0.5443   0.00801   0.00280  -0.0251   0.3575   0.9079
   2.500   0.5720   0.00807   0.00282  -0.0252   0.3550   0.9084
   2.750   0.5995   0.00813   0.00285  -0.0252   0.3525   0.9090
   3.000   0.6268   0.00822   0.00290  -0.0252   0.3497   0.9096
   3.250   0.6545   0.00828   0.00294  -0.0253   0.3477   0.9101
   3.500   0.6821   0.00833   0.00299  -0.0253   0.3457   0.9109
   3.750   0.7096   0.00840   0.00305  -0.0253   0.3436   0.9116
   4.000   0.7371   0.00847   0.00310  -0.0254   0.3411   0.9122
   4.250   0.7643   0.00856   0.00317  -0.0254   0.3385   0.9128
   4.500   0.7912   0.00866   0.00325  -0.0254   0.3359   0.9134
   4.750   0.8180   0.00876   0.00334  -0.0254   0.3334   0.9140
   5.000   0.8456   0.00883   0.00341  -0.0255   0.3315   0.9147
   5.250   0.8729   0.00890   0.00349  -0.0256   0.3293   0.9153
   5.500   0.8999   0.00899   0.00357  -0.0256   0.3267   0.9159
   5.750   0.9267   0.00909   0.00367  -0.0256   0.3241   0.9166
   6.000   0.9530   0.00921   0.00378  -0.0255   0.3211   0.9173
   6.250   0.9792   0.00933   0.00390  -0.0255   0.3183   0.9180
   6.500   1.0061   0.00942   0.00401  -0.0255   0.3162   0.9189
   6.750   1.0328   0.00952   0.00412  -0.0255   0.3135   0.9196
   7.000   1.0590   0.00963   0.00424  -0.0255   0.3105   0.9203
   7.250   1.0847   0.00977   0.00438  -0.0254   0.3069   0.9209
   7.500   1.1100   0.00992   0.00453  -0.0252   0.3036   0.9215
   7.750   1.1364   0.01003   0.00466  -0.0252   0.3006   0.9221
   8.000   1.1619   0.01015   0.00480  -0.0251   0.2969   0.9227
   8.250   1.1865   0.01030   0.00496  -0.0248   0.2930   0.9235
   8.500   1.2103   0.01047   0.00513  -0.0243   0.2887   0.9243
   8.750   1.2350   0.01059   0.00530  -0.0241   0.2853   0.9251
   9.000   1.2586   0.01077   0.00548  -0.0236   0.2800   0.9260
   9.250   1.2809   0.01098   0.00569  -0.0229   0.2744   0.9269
   9.500   1.3038   0.01117   0.00590  -0.0224   0.2679   0.9279
   9.750   1.3246   0.01143   0.00615  -0.0215   0.2617   0.9290
  10.000   1.3460   0.01164   0.00638  -0.0207   0.2549   0.9301
  10.250   1.3633   0.01192   0.00665  -0.0191   0.2477   0.9317
  10.500   1.3817   0.01218   0.00692  -0.0178   0.2404   0.9333
  10.750   1.3975   0.01254   0.00727  -0.0161   0.2325   0.9350
  11.000   1.4139   0.01288   0.00762  -0.0145   0.2246   0.9364
  11.250   1.4274   0.01332   0.00804  -0.0125   0.2149   0.9382
  11.500   1.4381   0.01382   0.00853  -0.0101   0.2050   0.9405
  11.750   1.4476   0.01438   0.00908  -0.0075   0.1946   0.9431
  12.000   1.4580   0.01493   0.00963  -0.0053   0.1856   0.9459
  12.250   1.4661   0.01559   0.01030  -0.0028   0.1773   0.9491
  12.500   1.4707   0.01641   0.01110  -0.0001   0.1676   0.9529
  12.750   1.4770   0.01719   0.01192   0.0023   0.1594   0.9580
  13.000   1.4800   0.01830   0.01303   0.0047   0.1499   0.9652
  13.250   1.4881   0.01963   0.01438   0.0054   0.1408   0.9747
  13.500   1.5016   0.02120   0.01596   0.0045   0.1310   0.9912
  14.000   1.5029   0.02486   0.01965   0.0069   0.1172   1.0000
  14.250   1.5029   0.02693   0.02175   0.0077   0.1109   1.0000
  14.500   1.4969   0.02961   0.02445   0.0085   0.1042   1.0000
  14.750   1.4908   0.03244   0.02731   0.0091   0.0975   1.0000
  15.000   1.4838   0.03546   0.03037   0.0095   0.0929   1.0000
  15.250   1.4759   0.03863   0.03359   0.0098   0.0876   1.0000
  15.500   1.4642   0.04228   0.03729   0.0099   0.0832   1.0000
  15.750   1.4559   0.04568   0.04075   0.0099   0.0792   1.0000
  16.000   1.4477   0.04919   0.04432   0.0096   0.0764   1.0000
  16.250   1.4350   0.05329   0.04847   0.0093   0.0727   1.0000
  16.500   1.4259   0.05708   0.05232   0.0088   0.0689   1.0000
  16.750   1.4146   0.06122   0.05650   0.0081   0.0655   1.0000
  17.000   1.4029   0.06552   0.06084   0.0073   0.0615   1.0000
  17.250   1.3962   0.06929   0.06467   0.0065   0.0591   1.0000
  17.500   1.3839   0.07383   0.06925   0.0054   0.0554   1.0000
  17.750   1.3766   0.07784   0.07331   0.0044   0.0525   1.0000
  18.000   1.3684   0.08198   0.07750   0.0032   0.0489   1.0000
  18.250   1.3596   0.08633   0.08188   0.0019   0.0465   1.0000
  18.500   1.3551   0.09015   0.08577   0.0006   0.0442   1.0000
  18.750   1.3495   0.09416   0.08982  -0.0007   0.0416   1.0000
  19.000   1.3410   0.09863   0.09433  -0.0023   0.0389   1.0000
<< Back to EPPLER 344 AIRFOIL (e344-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 344 AIRFOIL (e344-il)