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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.84 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e178-il-1000000-n5.txt
Download as CSV file: xf-e178-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E178  (8.69%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5227   0.14120   0.13957   0.0140   1.0000   0.0023
 -12.000  -0.5182   0.13682   0.13519   0.0121   1.0000   0.0023
  -9.500  -0.7636   0.02596   0.02319  -0.0455   0.8887   0.0029
  -9.250  -0.7526   0.02231   0.01899  -0.0447   0.8628   0.0030
  -9.000  -0.7347   0.02012   0.01639  -0.0440   0.8423   0.0031
  -8.750  -0.7136   0.01859   0.01454  -0.0435   0.8244   0.0033
  -8.500  -0.6911   0.01733   0.01299  -0.0431   0.8081   0.0034
  -8.250  -0.6673   0.01632   0.01175  -0.0427   0.7936   0.0035
  -8.000  -0.6426   0.01551   0.01074  -0.0424   0.7803   0.0036
  -7.750  -0.6187   0.01435   0.00933  -0.0421   0.7682   0.0041
  -7.500  -0.5922   0.01402   0.00892  -0.0419   0.7571   0.0046
  -7.250  -0.5651   0.01393   0.00879  -0.0419   0.7465   0.0051
  -6.750  -0.5111   0.01348   0.00820  -0.0417   0.7267   0.0061
  -6.500  -0.4843   0.01315   0.00777  -0.0416   0.7182   0.0066
  -6.250  -0.4574   0.01281   0.00732  -0.0415   0.7096   0.0069
  -6.000  -0.4301   0.01260   0.00704  -0.0414   0.7018   0.0070
  -5.500  -0.3774   0.01141   0.00562  -0.0410   0.6876   0.0084
  -5.250  -0.3499   0.01124   0.00539  -0.0410   0.6807   0.0090
  -5.000  -0.3224   0.01101   0.00512  -0.0410   0.6741   0.0097
  -4.500  -0.2679   0.01032   0.00425  -0.0407   0.6618   0.0110
  -4.250  -0.2405   0.01003   0.00389  -0.0406   0.6557   0.0117
  -4.000  -0.2127   0.00985   0.00364  -0.0406   0.6503   0.0123
  -3.750  -0.1850   0.00967   0.00341  -0.0405   0.6445   0.0126
  -3.500  -0.1573   0.00946   0.00315  -0.0405   0.6392   0.0129
  -3.250  -0.1302   0.00896   0.00253  -0.0403   0.6340   0.0139
  -3.000  -0.1025   0.00870   0.00220  -0.0402   0.6286   0.0146
  -2.750  -0.0746   0.00851   0.00195  -0.0401   0.6238   0.0151
  -2.500  -0.0466   0.00834   0.00172  -0.0401   0.6186   0.0155
  -2.250  -0.0187   0.00821   0.00154  -0.0401   0.6134   0.0161
  -2.000   0.0094   0.00808   0.00138  -0.0401   0.6088   0.0169
  -1.750   0.0375   0.00797   0.00124  -0.0401   0.6038   0.0174
  -1.250   0.0938   0.00781   0.00101  -0.0401   0.5941   0.0204
  -1.000   0.1217   0.00761   0.00092  -0.0401   0.5891   0.0527
  -0.750   0.1493   0.00741   0.00085  -0.0401   0.5844   0.0976
  -0.500   0.1773   0.00726   0.00080  -0.0401   0.5794   0.1357
  -0.250   0.2051   0.00712   0.00076  -0.0402   0.5744   0.1770
   0.000   0.2328   0.00694   0.00073  -0.0402   0.5696   0.2342
   0.250   0.2599   0.00661   0.00072  -0.0403   0.5643   0.3425
   0.500   0.2856   0.00606   0.00074  -0.0402   0.5590   0.5369
   0.750   0.3107   0.00560   0.00077  -0.0397   0.5537   0.6999
   1.000   0.3349   0.00528   0.00080  -0.0389   0.5464   0.8184
   1.250   0.3594   0.00503   0.00085  -0.0378   0.5381   0.9321
   1.500   0.4027   0.00505   0.00087  -0.0411   0.5288   0.9833
   1.750   0.4412   0.00511   0.00088  -0.0435   0.5190   0.9975
   2.000   0.4712   0.00518   0.00091  -0.0440   0.5086   1.0000
   2.250   0.4980   0.00526   0.00096  -0.0438   0.4987   1.0000
   2.500   0.5248   0.00536   0.00101  -0.0435   0.4874   1.0000
   2.750   0.5516   0.00547   0.00106  -0.0433   0.4745   1.0000
   3.000   0.5784   0.00558   0.00113  -0.0432   0.4618   1.0000
   3.250   0.6053   0.00570   0.00122  -0.0430   0.4472   1.0000
   3.500   0.6320   0.00585   0.00132  -0.0428   0.4289   1.0000
   3.750   0.6585   0.00605   0.00143  -0.0426   0.4037   1.0000
   4.000   0.6846   0.00632   0.00158  -0.0424   0.3717   1.0000
   4.250   0.7102   0.00669   0.00177  -0.0422   0.3292   1.0000
   4.500   0.7352   0.00715   0.00205  -0.0419   0.2806   1.0000
   4.750   0.7608   0.00752   0.00228  -0.0417   0.2476   1.0000
   5.000   0.7849   0.00811   0.00262  -0.0414   0.1925   1.0000
   5.250   0.8084   0.00879   0.00301  -0.0410   0.1324   1.0000
   5.500   0.8323   0.00938   0.00338  -0.0406   0.0896   1.0000
   5.750   0.8564   0.00992   0.00375  -0.0403   0.0572   1.0000
   6.000   0.8811   0.01036   0.00412  -0.0399   0.0392   1.0000
   6.250   0.9056   0.01081   0.00449  -0.0396   0.0226   1.0000
   6.500   0.9291   0.01140   0.00498  -0.0391   0.0074   1.0000
   6.750   0.9540   0.01178   0.00537  -0.0387   0.0052   1.0000
   7.000   0.9785   0.01220   0.00582  -0.0383   0.0039   1.0000
   7.250   1.0027   0.01264   0.00633  -0.0379   0.0032   1.0000
   7.500   1.0271   0.01302   0.00675  -0.0375   0.0031   1.0000
   7.750   1.0510   0.01347   0.00724  -0.0370   0.0029   1.0000
   8.000   1.0743   0.01395   0.00781  -0.0365   0.0028   1.0000
   8.250   1.0972   0.01446   0.00838  -0.0359   0.0026   1.0000
   8.500   1.1196   0.01501   0.00899  -0.0353   0.0024   1.0000
   8.750   1.1413   0.01561   0.00966  -0.0346   0.0023   1.0000
   9.000   1.1626   0.01623   0.01034  -0.0339   0.0021   1.0000
   9.250   1.1830   0.01690   0.01107  -0.0330   0.0019   1.0000
   9.500   1.2021   0.01767   0.01190  -0.0320   0.0018   1.0000
   9.750   1.2184   0.01867   0.01301  -0.0307   0.0017   1.0000
  10.000   1.2303   0.02001   0.01451  -0.0288   0.0016   1.0000
  10.250   1.2392   0.02151   0.01617  -0.0266   0.0015   1.0000
  10.500   1.2454   0.02303   0.01784  -0.0241   0.0015   1.0000
  10.750   1.2521   0.02409   0.01900  -0.0215   0.0014   1.0000
  11.000   1.2563   0.02537   0.02039  -0.0190   0.0014   1.0000
  11.250   1.2607   0.02680   0.02194  -0.0168   0.0014   1.0000
  11.500   1.2642   0.02843   0.02369  -0.0151   0.0014   1.0000
  11.750   1.2670   0.03027   0.02566  -0.0136   0.0014   1.0000
  12.000   1.2679   0.03241   0.02795  -0.0123   0.0014   1.0000
  12.250   1.2702   0.03452   0.03019  -0.0113   0.0014   1.0000
  12.500   1.2695   0.03706   0.03287  -0.0106   0.0014   1.0000
  12.750   1.2667   0.03993   0.03590  -0.0101   0.0014   1.0000
  13.000   1.2625   0.04312   0.03926  -0.0099   0.0014   1.0000
  13.250   1.2569   0.04659   0.04288  -0.0100   0.0014   1.0000
  13.500   1.2499   0.05039   0.04684  -0.0105   0.0014   1.0000
  13.750   1.2410   0.05463   0.05124  -0.0115   0.0014   1.0000
  14.000   1.2284   0.05961   0.05639  -0.0129   0.0014   1.0000
  14.250   1.2165   0.06474   0.06168  -0.0147   0.0014   1.0000
  14.500   1.2033   0.07047   0.06758  -0.0172   0.0014   1.0000
  14.750   1.1888   0.07685   0.07412  -0.0202   0.0014   1.0000
  15.000   1.1725   0.08402   0.08143  -0.0240   0.0014   1.0000
  15.250   1.1546   0.09203   0.08959  -0.0284   0.0014   1.0000
  15.500   1.1388   0.10019   0.09789  -0.0330   0.0014   1.0000
  15.750   1.1201   0.10950   0.10734  -0.0384   0.0014   1.0000
  16.000   1.1001   0.11965   0.11761  -0.0443   0.0014   1.0000
  16.250   1.0791   0.13058   0.12867  -0.0505   0.0014   1.0000
  16.500   1.0576   0.14214   0.14034  -0.0569   0.0014   1.0000
  16.750   1.0325   0.15541   0.15372  -0.0641   0.0014   1.0000
  17.000   1.0008   0.17188   0.17029  -0.0726   0.0015   1.0000
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