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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 200,000
Max Cl/Cd: 86.72 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377m-il-200000-n5.txt
Download as CSV file: xf-e377m-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 (MODIFIED) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1395   0.09418   0.09068  -0.0300   0.8205   0.0125
  -7.000  -0.1265   0.09216   0.08856  -0.0319   0.7968   0.0126
  -6.750  -0.1126   0.09005   0.08637  -0.0339   0.7757   0.0127
  -6.500  -0.0976   0.08794   0.08417  -0.0362   0.7575   0.0127
  -6.250  -0.0816   0.08568   0.08183  -0.0386   0.7410   0.0127
  -6.000  -0.0639   0.08336   0.07943  -0.0413   0.7271   0.0128
  -5.750  -0.0446   0.08102   0.07699  -0.0443   0.7133   0.0128
  -5.500  -0.0246   0.07852   0.07442  -0.0472   0.7017   0.0128
  -5.250  -0.0026   0.07598   0.07180  -0.0505   0.6908   0.0129
  -5.000   0.0151   0.07236   0.06813  -0.0524   0.6811   0.0130
  -4.750   0.0246   0.06826   0.06401  -0.0518   0.6716   0.0137
  -4.500   0.0447   0.06590   0.06158  -0.0539   0.6629   0.0150
  -4.250   0.0695   0.06352   0.05912  -0.0570   0.6542   0.0173
  -4.000   0.1035   0.06157   0.05708  -0.0620   0.6459   0.0190
  -3.750   0.1401   0.05987   0.05524  -0.0674   0.6381   0.0194
  -3.500   0.1747   0.05771   0.05297  -0.0722   0.6306   0.0196
  -3.250   0.2074   0.05533   0.05047  -0.0761   0.6239   0.0196
  -2.750   0.2519   0.04813   0.04318  -0.0797   0.6111   0.0207
  -2.500   0.2777   0.04606   0.04104  -0.0816   0.6050   0.0233
  -2.250   0.3221   0.04497   0.03979  -0.0866   0.5986   0.0283
  -2.000   0.3643   0.04358   0.03821  -0.0911   0.5929   0.0287
  -1.750   0.3998   0.04157   0.03606  -0.0942   0.5868   0.0288
  -1.500   0.4333   0.03946   0.03381  -0.0967   0.5816   0.0288
  -1.250   0.4597   0.03587   0.03018  -0.0987   0.5766   0.0296
  -1.000   0.4863   0.03381   0.02805  -0.1000   0.5710   0.0309
  -0.750   0.5265   0.03387   0.02789  -0.1024   0.5660   0.0394
  -0.500   0.5622   0.03241   0.02628  -0.1045   0.5605   0.0396
   0.000   0.6229   0.02721   0.02079  -0.1076   0.5516   0.0273
   0.250   0.6551   0.02572   0.01920  -0.1089   0.5463   0.0261
   0.500   0.6883   0.02428   0.01759  -0.1102   0.5414   0.0254
   0.750   0.7215   0.02286   0.01595  -0.1112   0.5374   0.0255
   1.000   0.7549   0.02139   0.01429  -0.1121   0.5325   0.0264
   1.250   0.7872   0.02010   0.01280  -0.1128   0.5276   0.0303
   1.500   0.8183   0.01891   0.01138  -0.1132   0.5236   0.0311
   1.750   0.8493   0.01771   0.00995  -0.1135   0.5192   0.0331
   2.000   0.8811   0.01599   0.00788  -0.1138   0.5145   0.0411
   2.250   0.9077   0.01620   0.00807  -0.1134   0.5100   0.0528
   2.500   0.9337   0.01671   0.00863  -0.1131   0.5054   0.0655
   2.750   0.9615   0.01647   0.00828  -0.1129   0.5005   0.0753
   3.000   0.9875   0.01664   0.00843  -0.1127   0.4960   0.0809
   3.250   1.0154   0.01626   0.00789  -0.1124   0.4917   0.0867
   3.500   1.0419   0.01623   0.00789  -0.1123   0.4867   0.0894
   3.750   1.0691   0.01613   0.00768  -0.1119   0.4821   0.0977
   4.000   1.0953   0.01610   0.00767  -0.1117   0.4776   0.0998
   4.250   1.1217   0.01604   0.00765  -0.1115   0.4722   0.1026
   4.500   1.1482   0.01600   0.00755  -0.1112   0.4673   0.1067
   4.750   1.1745   0.01599   0.00760  -0.1109   0.4618   0.1113
   5.000   1.2005   0.01597   0.00762  -0.1106   0.4554   0.1134
   5.250   1.2264   0.01597   0.00762  -0.1103   0.4494   0.1155
   5.500   1.2523   0.01597   0.00766  -0.1100   0.4420   0.1178
   5.750   1.2781   0.01603   0.00769  -0.1095   0.4355   0.1216
   6.000   1.3037   0.01607   0.00790  -0.1093   0.4276   0.1239
   6.250   1.3290   0.01614   0.00803  -0.1089   0.4203   0.1257
   6.500   1.3541   0.01622   0.00818  -0.1085   0.4118   0.1274
   6.750   1.3793   0.01632   0.00836  -0.1081   0.4028   0.1293
   7.000   1.4043   0.01646   0.00854  -0.1076   0.3932   0.1313
   7.250   1.4290   0.01662   0.00876  -0.1072   0.3822   0.1332
   7.500   1.4532   0.01679   0.00910  -0.1067   0.3698   0.1361
   7.750   1.4769   0.01703   0.00941  -0.1061   0.3557   0.1398
   8.000   1.5000   0.01732   0.00974  -0.1055   0.3394   0.1422
   8.250   1.5226   0.01767   0.01013  -0.1048   0.3202   0.1441
   8.500   1.5437   0.01815   0.01060  -0.1040   0.2958   0.1459
   8.750   1.5608   0.01906   0.01131  -0.1029   0.2502   0.1479
   9.000   1.5729   0.02055   0.01251  -0.1014   0.1959   0.1499
   9.250   1.5846   0.02206   0.01377  -0.0998   0.1546   0.1522
   9.500   1.5941   0.02368   0.01515  -0.0981   0.1179   0.1553
   9.750   1.6015   0.02534   0.01662  -0.0962   0.0852   0.1584
  10.000   1.6088   0.02686   0.01805  -0.0941   0.0651   0.1617
  10.250   1.6142   0.02835   0.01951  -0.0918   0.0498   0.1642
  10.500   1.6096   0.03024   0.02132  -0.0885   0.0338   0.1656
  10.750   1.6041   0.03247   0.02351  -0.0858   0.0208   0.1667
  11.000   1.5988   0.03503   0.02608  -0.0839   0.0126   0.1678
  11.250   1.5950   0.03776   0.02889  -0.0826   0.0091   0.1691
  11.500   1.5929   0.04057   0.03181  -0.0817   0.0077   0.1709
  11.750   1.5904   0.04358   0.03500  -0.0810   0.0069   0.1728
  12.000   1.5871   0.04685   0.03842  -0.0806   0.0064   0.1746
  12.250   1.5840   0.05020   0.04193  -0.0804   0.0060   0.1765
  12.500   1.5813   0.05358   0.04548  -0.0803   0.0057   0.1786
  12.750   1.5777   0.05717   0.04922  -0.0804   0.0051   0.1809
  13.000   1.5734   0.06093   0.05315  -0.0806   0.0048   0.1846
  13.250   1.5684   0.06486   0.05723  -0.0810   0.0046   0.1885
  13.500   1.5619   0.06909   0.06162  -0.0815   0.0043   0.1917
  13.750   1.5530   0.07382   0.06651  -0.0824   0.0041   0.1944
  14.000   1.5458   0.07851   0.07136  -0.0833   0.0040   0.1975
  14.250   1.5371   0.08359   0.07661  -0.0846   0.0039   0.2004
  14.500   1.5272   0.08908   0.08227  -0.0861   0.0038   0.2029
  14.750   1.5169   0.09477   0.08813  -0.0878   0.0037   0.2053
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