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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.35 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601001-il-1000000-n5.txt
Download as CSV file: xf-fx601001-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6633   0.05524   0.05341  -0.0564   1.0000   0.0029
 -11.000  -0.7068   0.04477   0.04278  -0.0624   1.0000   0.0029
 -10.750  -0.7186   0.03883   0.03672  -0.0685   0.9978   0.0028
 -10.500  -0.6921   0.02827   0.02565  -0.0914   0.9898   0.0029
 -10.250  -0.6624   0.02457   0.02163  -0.0984   0.9869   0.0030
 -10.000  -0.6335   0.02257   0.01944  -0.1018   0.9833   0.0031
  -9.750  -0.6023   0.02101   0.01772  -0.1047   0.9798   0.0031
  -9.500  -0.5694   0.01967   0.01624  -0.1076   0.9768   0.0032
  -9.250  -0.5404   0.01872   0.01518  -0.1090   0.9706   0.0034
  -9.000  -0.5089   0.01751   0.01381  -0.1111   0.9654   0.0035
  -8.750  -0.4813   0.01646   0.01260  -0.1120   0.9573   0.0036
  -8.500  -0.4532   0.01534   0.01128  -0.1131   0.9511   0.0038
  -8.250  -0.4263   0.01439   0.01018  -0.1136   0.9437   0.0039
  -8.000  -0.3988   0.01353   0.00917  -0.1141   0.9372   0.0041
  -7.750  -0.3717   0.01283   0.00836  -0.1144   0.9295   0.0042
  -7.500  -0.3442   0.01225   0.00765  -0.1146   0.9223   0.0044
  -7.250  -0.3167   0.01173   0.00704  -0.1148   0.9136   0.0045
  -7.000  -0.2892   0.01096   0.00612  -0.1151   0.9044   0.0048
  -6.750  -0.2615   0.01039   0.00544  -0.1154   0.8944   0.0051
  -6.500  -0.2338   0.01000   0.00497  -0.1155   0.8836   0.0054
  -6.250  -0.2058   0.00967   0.00454  -0.1156   0.8732   0.0057
  -6.000  -0.1778   0.00936   0.00414  -0.1157   0.8634   0.0061
  -5.750  -0.1497   0.00911   0.00381  -0.1158   0.8536   0.0067
  -5.500  -0.1215   0.00890   0.00353  -0.1159   0.8438   0.0072
  -5.250  -0.0930   0.00857   0.00309  -0.1161   0.8343   0.0079
  -5.000  -0.0646   0.00831   0.00274  -0.1162   0.8247   0.0091
  -4.750  -0.0361   0.00811   0.00246  -0.1163   0.8148   0.0104
  -4.500  -0.0076   0.00795   0.00223  -0.1164   0.8058   0.0117
  -4.250   0.0209   0.00780   0.00203  -0.1165   0.7970   0.0182
  -4.000   0.0496   0.00756   0.00185  -0.1168   0.7880   0.0367
  -3.750   0.0781   0.00744   0.00171  -0.1169   0.7787   0.0455
  -3.500   0.1064   0.00737   0.00159  -0.1170   0.7684   0.0516
  -3.250   0.1350   0.00725   0.00147  -0.1171   0.7576   0.0606
  -3.000   0.1635   0.00715   0.00135  -0.1172   0.7472   0.0724
  -2.750   0.1922   0.00693   0.00121  -0.1175   0.7357   0.1124
  -2.250   0.2492   0.00655   0.00100  -0.1180   0.7068   0.2110
  -2.000   0.2774   0.00644   0.00093  -0.1181   0.6864   0.2535
  -1.750   0.3054   0.00628   0.00084  -0.1183   0.6635   0.3143
  -1.500   0.3333   0.00616   0.00082  -0.1184   0.6409   0.3833
  -1.250   0.3612   0.00620   0.00086  -0.1184   0.6217   0.4205
  -1.000   0.3891   0.00628   0.00090  -0.1184   0.6049   0.4376
  -0.750   0.4171   0.00638   0.00093  -0.1183   0.5897   0.4509
  -0.500   0.4452   0.00647   0.00097  -0.1183   0.5771   0.4592
  -0.250   0.4732   0.00657   0.00102  -0.1182   0.5633   0.4678
   0.000   0.5011   0.00668   0.00107  -0.1182   0.5496   0.4742
   0.250   0.5292   0.00678   0.00111  -0.1181   0.5368   0.4775
   0.500   0.5573   0.00685   0.00115  -0.1181   0.5253   0.4804
   0.750   0.5854   0.00692   0.00120  -0.1181   0.5164   0.4831
   1.000   0.6135   0.00699   0.00125  -0.1181   0.5077   0.4855
   1.250   0.6417   0.00706   0.00130  -0.1181   0.4990   0.4879
   1.500   0.6696   0.00716   0.00136  -0.1180   0.4888   0.4905
   1.750   0.6974   0.00727   0.00143  -0.1180   0.4750   0.4926
   2.000   0.7250   0.00738   0.00150  -0.1179   0.4559   0.4949
   2.250   0.7523   0.00755   0.00160  -0.1178   0.4326   0.4974
   2.500   0.7791   0.00777   0.00172  -0.1176   0.4050   0.4996
   2.750   0.8057   0.00802   0.00186  -0.1174   0.3769   0.5014
   3.000   0.8324   0.00825   0.00202  -0.1173   0.3520   0.5029
   3.250   0.8588   0.00853   0.00219  -0.1170   0.3258   0.5043
   3.500   0.8853   0.00879   0.00237  -0.1168   0.3032   0.5056
   3.750   0.9121   0.00901   0.00254  -0.1167   0.2857   0.5071
   4.000   0.9385   0.00926   0.00273  -0.1165   0.2638   0.5089
   4.250   0.9640   0.00964   0.00297  -0.1161   0.2311   0.5106
   4.500   0.9881   0.01019   0.00329  -0.1157   0.1837   0.5122
   4.750   1.0134   0.01058   0.00357  -0.1153   0.1580   0.5138
   5.000   1.0391   0.01091   0.00384  -0.1150   0.1390   0.5154
   5.250   1.0628   0.01148   0.00420  -0.1145   0.0991   0.5173
   5.500   1.0860   0.01212   0.00466  -0.1138   0.0637   0.5191
   6.000   1.1324   0.01338   0.00566  -0.1125   0.0145   0.5226
   6.250   1.1577   0.01371   0.00602  -0.1121   0.0099   0.5246
   6.500   1.1827   0.01405   0.00642  -0.1117   0.0085   0.5268
   6.750   1.2070   0.01447   0.00688  -0.1111   0.0071   0.5291
   7.000   1.2313   0.01488   0.00734  -0.1106   0.0063   0.5318
   7.250   1.2559   0.01525   0.00776  -0.1101   0.0058   0.5346
   7.500   1.2801   0.01565   0.00820  -0.1096   0.0052   0.5378
   7.750   1.3036   0.01611   0.00871  -0.1090   0.0046   0.5413
   8.000   1.3259   0.01672   0.00939  -0.1082   0.0041   0.5451
   8.500   1.3714   0.01770   0.01051  -0.1067   0.0038   0.5553
   8.750   1.3934   0.01824   0.01114  -0.1059   0.0035   0.5628
   9.000   1.4148   0.01881   0.01183  -0.1050   0.0033   0.5749
   9.250   1.4358   0.01939   0.01253  -0.1041   0.0032   0.5981
   9.500   1.4565   0.01996   0.01327  -0.1032   0.0030   0.6522
   9.750   1.4763   0.02057   0.01406  -0.1022   0.0028   0.7147
  10.000   1.4941   0.02129   0.01500  -0.1010   0.0027   0.7883
  10.250   1.5032   0.02200   0.01610  -0.0979   0.0025   1.0000
  10.500   1.5204   0.02271   0.01687  -0.0965   0.0024   1.0000
  10.750   1.5352   0.02350   0.01774  -0.0947   0.0023   1.0000
  11.000   1.5460   0.02435   0.01867  -0.0923   0.0023   1.0000
  11.250   1.5547   0.02530   0.01972  -0.0896   0.0022   1.0000
  11.500   1.5620   0.02639   0.02090  -0.0870   0.0021   1.0000
  11.750   1.5687   0.02757   0.02218  -0.0845   0.0021   1.0000
  12.000   1.5744   0.02891   0.02361  -0.0821   0.0020   1.0000
  12.250   1.5798   0.03035   0.02515  -0.0799   0.0020   1.0000
  12.500   1.5843   0.03193   0.02684  -0.0779   0.0019   1.0000
  12.750   1.5881   0.03368   0.02869  -0.0761   0.0019   1.0000
  13.000   1.5902   0.03568   0.03079  -0.0744   0.0018   1.0000
  13.250   1.5929   0.03775   0.03297  -0.0731   0.0018   1.0000
  13.500   1.5932   0.04017   0.03552  -0.0719   0.0017   1.0000
  13.750   1.5931   0.04279   0.03824  -0.0711   0.0017   1.0000
  14.000   1.5920   0.04567   0.04124  -0.0705   0.0017   1.0000
  14.250   1.5896   0.04886   0.04455  -0.0703   0.0017   1.0000
  14.500   1.5862   0.05237   0.04818  -0.0704   0.0016   1.0000
  14.750   1.5810   0.05630   0.05223  -0.0709   0.0016   1.0000
  15.000   1.5735   0.06080   0.05687  -0.0718   0.0016   1.0000
  15.250   1.5661   0.06553   0.06173  -0.0731   0.0016   1.0000
  15.500   1.5557   0.07096   0.06730  -0.0748   0.0016   1.0000
  15.750   1.5437   0.07693   0.07341  -0.0771   0.0015   1.0000
  16.000   1.5306   0.08341   0.08003  -0.0798   0.0015   1.0000
  16.250   1.5154   0.09050   0.08728  -0.0830   0.0015   1.0000
  16.500   1.4990   0.09824   0.09517  -0.0867   0.0015   1.0000
  16.750   1.4826   0.10630   0.10337  -0.0909   0.0015   1.0000
  17.000   1.4656   0.11471   0.11193  -0.0953   0.0015   1.0000
  17.250   1.4482   0.12346   0.12082  -0.1001   0.0015   1.0000
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