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GOE 801 (MVA 301) AIRFOIL (goe801-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 801 (MVA 301) AIRFOIL (goe801-il)
Reynolds number: 500,000
Max Cl/Cd: 110.36 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe801-il-500000.txt
Download as CSV file: xf-goe801-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 801 (MVA 301) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1433   0.08672   0.08442  -0.0605   0.9561   0.0236
  -7.750  -0.1412   0.08383   0.08151  -0.0645   0.9409   0.0242
  -7.500  -0.1334   0.08018   0.07783  -0.0715   0.9279   0.0243
  -7.250  -0.1225   0.07624   0.07386  -0.0746   0.9196   0.0244
  -7.000  -0.1126   0.07360   0.07120  -0.0735   0.9124   0.0246
  -6.750  -0.1002   0.07107   0.06865  -0.0737   0.9057   0.0247
  -6.500  -0.0856   0.06841   0.06597  -0.0754   0.8978   0.0250
  -6.250  -0.0694   0.06565   0.06315  -0.0780   0.8911   0.0254
  -6.000  -0.0503   0.06265   0.06013  -0.0815   0.8831   0.0259
  -5.750  -0.0294   0.05951   0.05691  -0.0853   0.8763   0.0265
  -5.500  -0.0044   0.05598   0.05333  -0.0904   0.8688   0.0276
  -5.250   0.0432   0.04861   0.04567  -0.1042   0.8616   0.0287
  -5.000   0.0598   0.04616   0.04319  -0.1045   0.8547   0.0290
  -4.750   0.0804   0.04403   0.04102  -0.1054   0.8473   0.0293
  -4.500   0.1037   0.04184   0.03874  -0.1068   0.8399   0.0297
  -4.250   0.1296   0.03942   0.03623  -0.1087   0.8310   0.0304
  -4.000   0.1578   0.03677   0.03343  -0.1109   0.8227   0.0314
  -3.750   0.2009   0.03085   0.02697  -0.1159   0.8148   0.0339
  -3.500   0.2237   0.02914   0.02524  -0.1164   0.8068   0.0343
  -3.250   0.2487   0.02773   0.02376  -0.1169   0.7981   0.0349
  -3.000   0.2756   0.02615   0.02206  -0.1176   0.7897   0.0357
  -2.750   0.3043   0.02433   0.02005  -0.1183   0.7809   0.0374
  -2.500   0.3366   0.02144   0.01667  -0.1191   0.7720   0.0406
  -2.000   0.3905   0.01933   0.01439  -0.1196   0.7515   0.0430
  -1.750   0.4214   0.01816   0.01272  -0.1197   0.7413   0.0479
  -1.500   0.4480   0.01698   0.01152  -0.1199   0.7299   0.0492
  -1.250   0.4755   0.01634   0.01081  -0.1200   0.7168   0.0518
  -1.000   0.5044   0.01555   0.00974  -0.1200   0.7035   0.0580
  -0.750   0.5318   0.01489   0.00902  -0.1201   0.6899   0.0608
  -0.500   0.5607   0.01613   0.01004  -0.1195   0.6753   0.0669
  -0.250   0.5873   0.01385   0.00771  -0.1201   0.6615   0.0736
   0.000   0.6148   0.01337   0.00711  -0.1201   0.6465   0.0850
   0.500   0.6743   0.01149   0.00456  -0.1186   0.6184   0.0452
   0.750   0.7019   0.01117   0.00415  -0.1183   0.6045   0.0450
   1.000   0.7295   0.01087   0.00379  -0.1181   0.5913   0.0442
   1.250   0.7570   0.01064   0.00349  -0.1179   0.5788   0.0432
   1.500   0.7843   0.01052   0.00330  -0.1177   0.5666   0.0430
   1.750   0.8115   0.01046   0.00318  -0.1176   0.5544   0.0435
   2.000   0.8390   0.01041   0.00311  -0.1174   0.5423   0.0443
   2.250   0.8664   0.01041   0.00307  -0.1173   0.5312   0.0455
   2.500   0.8935   0.01047   0.00308  -0.1171   0.5203   0.0470
   2.750   0.9205   0.01051   0.00307  -0.1170   0.5081   0.0507
   3.000   0.9475   0.01059   0.00310  -0.1168   0.4949   0.0548
   3.250   0.9721   0.00941   0.00343  -0.1169   0.4822   0.7557
   3.500   0.9962   0.00917   0.00348  -0.1157   0.4700   1.0000
   3.750   1.0224   0.00940   0.00359  -0.1154   0.4581   1.0000
   4.000   1.0490   0.00958   0.00371  -0.1152   0.4457   1.0000
   4.250   1.0753   0.00978   0.00384  -0.1150   0.4338   1.0000
   4.500   1.1013   0.01001   0.00401  -0.1147   0.4229   1.0000
   4.750   1.1272   0.01024   0.00417  -0.1144   0.4125   1.0000
   5.000   1.1533   0.01045   0.00435  -0.1141   0.4021   1.0000
   5.250   1.1787   0.01070   0.00454  -0.1138   0.3916   1.0000
   5.500   1.2039   0.01096   0.00475  -0.1134   0.3810   1.0000
   5.750   1.2295   0.01119   0.00495  -0.1131   0.3711   1.0000
   6.000   1.2543   0.01147   0.00518  -0.1126   0.3617   1.0000
   6.250   1.2796   0.01171   0.00542  -0.1123   0.3529   1.0000
   6.500   1.3042   0.01198   0.00567  -0.1119   0.3445   1.0000
   6.750   1.3287   0.01226   0.00592  -0.1114   0.3354   1.0000
   7.000   1.3533   0.01252   0.00620  -0.1110   0.3276   1.0000
   7.250   1.3770   0.01284   0.00648  -0.1104   0.3185   1.0000
   7.500   1.4011   0.01311   0.00676  -0.1099   0.3085   1.0000
   7.750   1.4240   0.01345   0.00707  -0.1092   0.2961   1.0000
   8.000   1.4462   0.01382   0.00740  -0.1084   0.2818   1.0000
   8.250   1.4680   0.01421   0.00775  -0.1076   0.2669   1.0000
   8.500   1.4890   0.01464   0.00813  -0.1067   0.2504   1.0000
   8.750   1.5081   0.01518   0.00859  -0.1055   0.2294   1.0000
   9.000   1.5247   0.01587   0.00915  -0.1039   0.2050   1.0000
   9.500   1.5518   0.01741   0.01047  -0.0997   0.1689   1.0000
   9.750   1.5657   0.01806   0.01110  -0.0977   0.1585   1.0000
  10.000   1.5796   0.01874   0.01178  -0.0957   0.1494   1.0000
  10.250   1.5918   0.01954   0.01254  -0.0936   0.1404   1.0000
  10.500   1.6062   0.02022   0.01324  -0.0919   0.1320   1.0000
  10.750   1.6190   0.02103   0.01405  -0.0901   0.1239   1.0000
  11.000   1.6306   0.02193   0.01494  -0.0882   0.1152   1.0000
  11.250   1.6431   0.02280   0.01582  -0.0865   0.1066   1.0000
  11.500   1.6530   0.02388   0.01687  -0.0846   0.0960   1.0000
  11.750   1.6609   0.02513   0.01808  -0.0826   0.0842   1.0000
  12.000   1.6661   0.02663   0.01951  -0.0805   0.0723   1.0000
  12.250   1.6706   0.02824   0.02109  -0.0785   0.0636   1.0000
  12.500   1.6750   0.02991   0.02276  -0.0766   0.0566   1.0000
  12.750   1.6778   0.03178   0.02463  -0.0747   0.0501   1.0000
  13.000   1.6807   0.03371   0.02657  -0.0730   0.0422   1.0000
  13.250   1.6739   0.03661   0.02938  -0.0710   0.0244   1.0000
  13.500   1.6669   0.03966   0.03244  -0.0692   0.0203   1.0000
  13.750   1.6648   0.04237   0.03525  -0.0679   0.0189   1.0000
  14.000   1.6618   0.04528   0.03827  -0.0668   0.0180   1.0000
  14.250   1.6586   0.04833   0.04143  -0.0660   0.0172   1.0000
  14.500   1.6570   0.05133   0.04456  -0.0654   0.0167   1.0000
  14.750   1.6540   0.05462   0.04798  -0.0650   0.0163   1.0000
  15.000   1.6493   0.05822   0.05170  -0.0647   0.0159   1.0000
  15.250   1.6428   0.06216   0.05578  -0.0647   0.0156   1.0000
  15.500   1.6349   0.06642   0.06017  -0.0649   0.0153   1.0000
  15.750   1.6253   0.07102   0.06489  -0.0654   0.0150   1.0000
  16.000   1.6136   0.07599   0.06999  -0.0660   0.0148   1.0000
  16.250   1.6007   0.08127   0.07540  -0.0669   0.0146   1.0000
  16.500   1.5862   0.08690   0.08116  -0.0680   0.0145   1.0000
  16.750   1.5708   0.09274   0.08713  -0.0692   0.0143   1.0000
  17.000   1.5547   0.09881   0.09333  -0.0707   0.0142   1.0000
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