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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 100,000
Max Cl/Cd: 51.43 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63158-il-100000-n5.txt
Download as CSV file: xf-fx63158-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-158 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3008   0.11909   0.11421  -0.0469   1.0000   0.0508
 -10.750  -0.3021   0.11554   0.11073  -0.0479   1.0000   0.0515
 -10.500  -0.3277   0.10960   0.10494  -0.0538   1.0000   0.0536
 -10.250  -0.3186   0.10695   0.10233  -0.0519   1.0000   0.0542
 -10.000  -0.3174   0.10393   0.09938  -0.0516   1.0000   0.0545
  -9.750  -0.3188   0.10081   0.09633  -0.0515   1.0000   0.0549
  -9.500  -0.3386   0.08933   0.08486  -0.0567   1.0000   0.0300
  -9.000  -0.3393   0.07649   0.07203  -0.0670   0.9907   0.0252
  -8.750  -0.3366   0.07075   0.06622  -0.0734   0.9781   0.0245
  -8.500  -0.3434   0.06508   0.06044  -0.0789   0.9589   0.0238
  -8.250  -0.3683   0.05746   0.05239  -0.0850   0.9300   0.0219
  -8.000  -0.3568   0.05355   0.04825  -0.0880   0.9141   0.0213
  -7.750  -0.3419   0.04954   0.04396  -0.0911   0.8995   0.0208
  -7.500  -0.3220   0.04525   0.03927  -0.0946   0.8867   0.0203
  -7.250  -0.2954   0.04112   0.03465  -0.0982   0.8752   0.0198
  -7.000  -0.2689   0.03769   0.03073  -0.1006   0.8602   0.0194
  -6.750  -0.2384   0.03459   0.02709  -0.1029   0.8462   0.0191
  -6.500  -0.2043   0.03205   0.02412  -0.1052   0.8331   0.0194
  -6.250  -0.1686   0.02997   0.02157  -0.1075   0.8201   0.0206
  -6.000  -0.1343   0.02816   0.01926  -0.1090   0.8059   0.0219
  -5.750  -0.1027   0.02667   0.01764  -0.1100   0.7914   0.0227
  -5.500  -0.0720   0.02534   0.01610  -0.1103   0.7775   0.0231
  -5.250  -0.0424   0.02422   0.01482  -0.1104   0.7647   0.0235
  -5.000  -0.0136   0.02325   0.01371  -0.1103   0.7531   0.0240
  -4.750   0.0119   0.02245   0.01284  -0.1098   0.7417   0.0246
  -4.500   0.0387   0.02172   0.01199  -0.1096   0.7320   0.0254
  -4.250   0.0642   0.02108   0.01128  -0.1096   0.7221   0.0265
  -4.000   0.0906   0.02053   0.01060  -0.1098   0.7130   0.0281
  -3.750   0.1175   0.02007   0.00998  -0.1099   0.7041   0.0305
  -3.500   0.1449   0.01964   0.00938  -0.1101   0.6963   0.0356
  -3.250   0.1715   0.01897   0.00867  -0.1104   0.6888   0.0487
  -3.000   0.1891   0.01710   0.00932  -0.1099   0.6831   0.5261
  -2.750   0.2144   0.01784   0.00999  -0.1084   0.6761   0.6078
  -2.500   0.2439   0.01844   0.01035  -0.1083   0.6701   0.6424
  -2.250   0.2711   0.01890   0.01062  -0.1076   0.6650   0.6587
  -2.000   0.2956   0.01934   0.01093  -0.1065   0.6588   0.6739
  -1.750   0.3230   0.01967   0.01110  -0.1062   0.6533   0.6879
  -1.250   0.3723   0.02017   0.01138  -0.1043   0.6425   0.7046
  -1.000   0.3922   0.02043   0.01160  -0.1020   0.6371   0.7106
  -0.750   0.4194   0.02062   0.01164  -0.1018   0.6325   0.7198
  -0.500   0.4416   0.02078   0.01177  -0.1005   0.6271   0.7265
  -0.250   0.4651   0.02091   0.01183  -0.0995   0.6216   0.7325
   0.000   0.4977   0.02094   0.01172  -0.1011   0.6168   0.7390
   0.250   0.5219   0.02100   0.01172  -0.1004   0.6120   0.7424
   0.500   0.5455   0.02106   0.01177  -0.0996   0.6061   0.7456
   0.750   0.5731   0.02108   0.01169  -0.0998   0.6002   0.7490
   1.000   0.6016   0.02111   0.01164  -0.1004   0.5933   0.7530
   1.250   0.6304   0.02110   0.01157  -0.1012   0.5849   0.7568
   1.500   0.6545   0.02110   0.01150  -0.1004   0.5782   0.7594
   1.750   0.6766   0.02111   0.01154  -0.0994   0.5697   0.7623
   2.000   0.7042   0.02108   0.01140  -0.0995   0.5627   0.7650
   2.250   0.7294   0.02111   0.01147  -0.0995   0.5544   0.7675
   2.500   0.7588   0.02111   0.01140  -0.1002   0.5477   0.7699
   2.750   0.7878   0.02120   0.01147  -0.1010   0.5411   0.7727
   3.000   0.8128   0.02128   0.01159  -0.1008   0.5353   0.7753
   3.250   0.8377   0.02135   0.01168  -0.1003   0.5306   0.7780
   3.500   0.8628   0.02146   0.01183  -0.1001   0.5255   0.7807
   3.750   0.8881   0.02160   0.01204  -0.1001   0.5195   0.7830
   4.000   0.9158   0.02171   0.01217  -0.1005   0.5142   0.7848
   4.250   0.9436   0.02184   0.01236  -0.1010   0.5091   0.7867
   4.500   0.9703   0.02202   0.01264  -0.1014   0.5029   0.7886
   4.750   0.9992   0.02217   0.01283  -0.1021   0.4978   0.7904
   5.000   1.0262   0.02232   0.01303  -0.1024   0.4937   0.7921
   5.250   1.0489   0.02254   0.01340  -0.1018   0.4886   0.7940
   5.500   1.0733   0.02273   0.01370  -0.1015   0.4837   0.7960
   5.750   1.0996   0.02287   0.01389  -0.1016   0.4790   0.7979
   6.000   1.1230   0.02311   0.01427  -0.1013   0.4720   0.7997
   6.250   1.1471   0.02330   0.01456  -0.1011   0.4642   0.8016
   6.500   1.1707   0.02353   0.01490  -0.1008   0.4558   0.8035
   6.750   1.1936   0.02379   0.01529  -0.1005   0.4465   0.8054
   7.000   1.2165   0.02408   0.01572  -0.1003   0.4372   0.8073
   7.250   1.2383   0.02429   0.01603  -0.0996   0.4285   0.8091
   7.500   1.2571   0.02459   0.01647  -0.0984   0.4199   0.8110
   7.750   1.2775   0.02484   0.01680  -0.0975   0.4127   0.8133
   8.000   1.2956   0.02525   0.01738  -0.0963   0.4042   0.8157
   8.250   1.3133   0.02562   0.01786  -0.0951   0.3951   0.8182
   8.500   1.3273   0.02618   0.01861  -0.0934   0.3838   0.8206
   8.750   1.3419   0.02674   0.01930  -0.0920   0.3713   0.8229
   9.000   1.3557   0.02733   0.01995  -0.0904   0.3580   0.8255
   9.250   1.3648   0.02797   0.02059  -0.0879   0.3452   0.8280
   9.500   1.3714   0.02889   0.02161  -0.0855   0.3293   0.8307
   9.750   1.3758   0.03006   0.02287  -0.0832   0.3076   0.8336
  10.000   1.3763   0.03150   0.02425  -0.0806   0.2903   0.8363
  10.250   1.3775   0.03316   0.02594  -0.0786   0.2743   0.8389
  10.500   1.3797   0.03502   0.02792  -0.0772   0.2526   0.8416
  10.750   1.3713   0.03759   0.03041  -0.0751   0.2365   0.8442
  11.000   1.3626   0.04044   0.03322  -0.0734   0.2244   0.8468
  11.250   1.3634   0.04283   0.03581  -0.0726   0.2053   0.8498
  11.500   1.3538   0.04630   0.03925  -0.0718   0.1874   0.8530
  11.750   1.3448   0.04995   0.04287  -0.0713   0.1774   0.8562
  12.000   1.3412   0.05324   0.04626  -0.0712   0.1663   0.8595
  12.250   1.3397   0.05624   0.04942  -0.0709   0.1465   0.8627
  12.500   1.3272   0.06057   0.05368  -0.0709   0.1369   0.8657
  12.750   1.3182   0.06470   0.05779  -0.0711   0.1296   0.8688
  13.000   1.3153   0.06827   0.06147  -0.0714   0.1206   0.8722
  13.500   1.3103   0.07553   0.06892  -0.0724   0.0994   0.8795
  13.750   1.3038   0.07973   0.07311  -0.0730   0.0944   0.8834
  14.000   1.2977   0.08399   0.07736  -0.0738   0.0902   0.8877
  14.500   1.2947   0.09114   0.08471  -0.0749   0.0810   0.8991
  14.750   1.2973   0.09416   0.08796  -0.0754   0.0753   0.9079
  15.000   1.2979   0.09729   0.09125  -0.0758   0.0705   0.9216
  15.250   1.2964   0.10060   0.09469  -0.0765   0.0669   0.9639
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