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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.14 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601001-il-1000000.txt
Download as CSV file: xf-fx601001-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4076   0.10786   0.10618  -0.0298   1.0000   0.0109
 -10.500  -0.4059   0.10381   0.10214  -0.0314   1.0000   0.0114
  -8.750  -0.5295   0.02770   0.02509  -0.0939   0.9881   0.0078
  -8.500  -0.4979   0.02236   0.01918  -0.1006   0.9854   0.0078
  -8.250  -0.4640   0.02006   0.01658  -0.1040   0.9840   0.0081
  -8.000  -0.4296   0.01763   0.01382  -0.1071   0.9829   0.0082
  -7.750  -0.4003   0.01590   0.01184  -0.1085   0.9793   0.0084
  -7.500  -0.3685   0.01464   0.01041  -0.1100   0.9762   0.0086
  -7.250  -0.3357   0.01390   0.00955  -0.1113   0.9734   0.0089
  -7.000  -0.3033   0.01225   0.00770  -0.1131   0.9705   0.0094
  -6.750  -0.2744   0.01123   0.00658  -0.1139   0.9653   0.0100
  -6.500  -0.2455   0.01063   0.00591  -0.1143   0.9596   0.0105
  -6.250  -0.2151   0.01010   0.00531  -0.1150   0.9551   0.0110
  -6.000  -0.1881   0.00964   0.00479  -0.1149   0.9476   0.0116
  -5.750  -0.1595   0.00925   0.00433  -0.1150   0.9415   0.0123
  -5.500  -0.1317   0.00882   0.00381  -0.1151   0.9335   0.0133
  -5.250  -0.1033   0.00834   0.00324  -0.1152   0.9261   0.0152
  -5.000  -0.0754   0.00805   0.00289  -0.1151   0.9168   0.0169
  -4.750  -0.0470   0.00772   0.00253  -0.1152   0.9082   0.0223
  -4.500  -0.0189   0.00743   0.00232  -0.1152   0.8989   0.0434
  -4.250   0.0093   0.00727   0.00215  -0.1153   0.8890   0.0539
  -4.000   0.0375   0.00715   0.00198  -0.1152   0.8791   0.0602
  -3.750   0.0656   0.00702   0.00181  -0.1152   0.8688   0.0676
  -3.500   0.0939   0.00686   0.00164  -0.1152   0.8580   0.0802
  -3.250   0.1227   0.00641   0.00142  -0.1157   0.8480   0.1545
  -3.000   0.1512   0.00599   0.00125  -0.1161   0.8380   0.2466
  -2.750   0.1797   0.00560   0.00110  -0.1164   0.8274   0.3340
  -2.500   0.2081   0.00542   0.00106  -0.1166   0.8169   0.4049
  -2.250   0.2363   0.00543   0.00107  -0.1165   0.8052   0.4325
  -2.000   0.2643   0.00549   0.00108  -0.1163   0.7915   0.4494
  -1.750   0.2923   0.00556   0.00109  -0.1162   0.7762   0.4614
  -1.500   0.3203   0.00565   0.00108  -0.1160   0.7601   0.4696
  -1.250   0.3482   0.00572   0.00110  -0.1158   0.7439   0.4756
  -1.000   0.3762   0.00583   0.00111  -0.1157   0.7283   0.4820
  -0.500   0.4316   0.00604   0.00117  -0.1154   0.6893   0.4945
  -0.250   0.4592   0.00615   0.00119  -0.1152   0.6688   0.5002
   0.000   0.4868   0.00625   0.00122  -0.1150   0.6500   0.5033
   0.250   0.5146   0.00635   0.00125  -0.1149   0.6327   0.5064
   0.500   0.5425   0.00645   0.00128  -0.1148   0.6174   0.5093
   0.750   0.5704   0.00654   0.00132  -0.1148   0.6050   0.5120
   1.000   0.5983   0.00659   0.00135  -0.1147   0.5928   0.5147
   1.500   0.6542   0.00675   0.00146  -0.1146   0.5701   0.5200
   1.750   0.6822   0.00683   0.00152  -0.1146   0.5602   0.5226
   2.000   0.7100   0.00694   0.00159  -0.1145   0.5502   0.5251
   2.250   0.7380   0.00698   0.00164  -0.1144   0.5398   0.5281
   2.500   0.7659   0.00705   0.00171  -0.1144   0.5293   0.5303
   2.750   0.7936   0.00714   0.00180  -0.1143   0.5182   0.5322
   3.000   0.8213   0.00724   0.00189  -0.1142   0.5058   0.5342
   3.250   0.8488   0.00736   0.00198  -0.1141   0.4896   0.5364
   3.500   0.8757   0.00754   0.00210  -0.1139   0.4627   0.5384
   3.750   0.9021   0.00778   0.00222  -0.1137   0.4269   0.5403
   4.000   0.9273   0.00816   0.00242  -0.1133   0.3802   0.5427
   4.250   0.9520   0.00862   0.00268  -0.1129   0.3329   0.5449
   4.500   0.9767   0.00909   0.00296  -0.1124   0.2875   0.5474
   4.750   1.0017   0.00953   0.00323  -0.1120   0.2490   0.5501
   5.000   1.0274   0.00988   0.00347  -0.1117   0.2223   0.5527
   5.250   1.0529   0.01023   0.00373  -0.1114   0.1969   0.5554
   5.500   1.0779   0.01062   0.00404  -0.1110   0.1712   0.5585
   5.750   1.1031   0.01101   0.00435  -0.1106   0.1503   0.5620
   6.000   1.1277   0.01145   0.00468  -0.1102   0.1229   0.5658
   6.250   1.1484   0.01239   0.00530  -0.1093   0.0665   0.5701
   6.500   1.1675   0.01355   0.00616  -0.1080   0.0189   0.5755
   6.750   1.1917   0.01403   0.00669  -0.1074   0.0142   0.5822
   7.000   1.2157   0.01450   0.00722  -0.1068   0.0124   0.5918
   7.250   1.2383   0.01517   0.00802  -0.1060   0.0107   0.6067
   7.500   1.2626   0.01556   0.00855  -0.1054   0.0103   0.6384
   7.750   1.2863   0.01598   0.00919  -0.1049   0.0097   0.7062
   8.000   1.3079   0.01623   0.00986  -0.1039   0.0091   0.8548
   8.250   1.3263   0.01662   0.01043  -0.1021   0.0085   1.0000
   8.500   1.3459   0.01753   0.01140  -0.1009   0.0078   1.0000
   8.750   1.3612   0.01886   0.01286  -0.0991   0.0073   1.0000
   9.000   1.3824   0.01946   0.01352  -0.0981   0.0071   1.0000
   9.250   1.4016   0.02023   0.01435  -0.0969   0.0068   1.0000
   9.500   1.4195   0.02109   0.01528  -0.0955   0.0066   1.0000
   9.750   1.4362   0.02200   0.01628  -0.0939   0.0063   1.0000
  10.000   1.4515   0.02297   0.01733  -0.0922   0.0061   1.0000
  10.250   1.4657   0.02395   0.01838  -0.0903   0.0059   1.0000
  10.500   1.4767   0.02494   0.01944  -0.0880   0.0057   1.0000
  10.750   1.4846   0.02597   0.02055  -0.0852   0.0056   1.0000
  11.000   1.4909   0.02714   0.02178  -0.0824   0.0054   1.0000
  11.250   1.4944   0.02861   0.02334  -0.0795   0.0053   1.0000
  11.500   1.4937   0.03057   0.02541  -0.0765   0.0051   1.0000
  11.750   1.4865   0.03347   0.02847  -0.0732   0.0050   1.0000
  12.000   1.4773   0.03711   0.03231  -0.0703   0.0048   1.0000
  12.250   1.4833   0.03864   0.03395  -0.0689   0.0048   1.0000
  12.500   1.4873   0.04056   0.03600  -0.0676   0.0047   1.0000
  12.750   1.4902   0.04270   0.03826  -0.0666   0.0046   1.0000
  13.000   1.4908   0.04525   0.04094  -0.0657   0.0045   1.0000
  13.250   1.4899   0.04811   0.04393  -0.0651   0.0044   1.0000
  13.500   1.4878   0.05127   0.04723  -0.0648   0.0043   1.0000
  13.750   1.4833   0.05493   0.05104  -0.0648   0.0043   1.0000
  14.000   1.4769   0.05905   0.05531  -0.0653   0.0042   1.0000
  14.250   1.4684   0.06371   0.06013  -0.0662   0.0042   1.0000
  14.500   1.4584   0.06884   0.06542  -0.0676   0.0041   1.0000
  14.750   1.4472   0.07444   0.07118  -0.0696   0.0041   1.0000
  15.000   1.4343   0.08067   0.07758  -0.0721   0.0041   1.0000
  15.250   1.4197   0.08750   0.08458  -0.0751   0.0041   1.0000
  15.500   1.4047   0.09480   0.09205  -0.0788   0.0041   1.0000
  15.750   1.3879   0.10287   0.10029  -0.0831   0.0041   1.0000
  16.000   1.3693   0.11176   0.10935  -0.0881   0.0041   1.0000
  16.250   1.3523   0.12069   0.11845  -0.0934   0.0041   1.0000
  16.500   1.3311   0.13109   0.12902  -0.0998   0.0041   1.0000
  16.750   1.3114   0.14149   0.13958  -0.1065   0.0041   1.0000
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