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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 200,000
Max Cl/Cd: 72.38 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63158-il-200000.txt
Download as CSV file: xf-fx63158-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2258   0.09139   0.08855  -0.0544   0.9932   0.0445
  -9.500  -0.2343   0.08247   0.07965  -0.0626   0.9887   0.0461
  -8.750  -0.3316   0.07877   0.07586  -0.0626   0.9930   0.0430
  -8.500  -0.3301   0.07004   0.06703  -0.0751   0.9837   0.0438
  -8.250  -0.3373   0.06355   0.06040  -0.0836   0.9646   0.0446
  -7.750  -0.3224   0.05175   0.04805  -0.0978   0.9304   0.0482
  -7.250  -0.2661   0.04399   0.03986  -0.1076   0.9077   0.0577
  -7.000  -0.2304   0.04039   0.03598  -0.1134   0.8933   0.0662
  -6.750  -0.1886   0.03711   0.03242  -0.1198   0.8784   0.0776
  -6.500  -0.1501   0.03445   0.02931  -0.1256   0.8581   0.0965
  -6.250  -0.1160   0.03174   0.02642  -0.1289   0.8372   0.1092
  -6.000  -0.0862   0.02982   0.02427  -0.1309   0.8167   0.1244
  -5.750  -0.0330   0.01098   0.00371  -0.1219   0.7775   0.0344
  -5.500  -0.0061   0.00987   0.00208  -0.1213   0.7651   0.0301
  -5.250   0.0184   0.02058   0.01257  -0.1257   0.7723   0.0293
  -5.000   0.0431   0.01957   0.01145  -0.1246   0.7584   0.0289
  -4.750   0.0685   0.01890   0.01060  -0.1237   0.7459   0.0296
  -4.500   0.0929   0.01815   0.00984  -0.1230   0.7346   0.0320
  -4.250   0.1159   0.01758   0.00921  -0.1219   0.7228   0.0331
  -4.000   0.1398   0.01702   0.00859  -0.1211   0.7120   0.0336
  -3.750   0.1651   0.01654   0.00800  -0.1207   0.7014   0.0346
  -3.500   0.1901   0.01582   0.00728  -0.1209   0.6908   0.0364
  -3.250   0.2190   0.01533   0.00661  -0.1216   0.6818   0.0400
  -3.000   0.2502   0.01423   0.00568  -0.1233   0.6721   0.1054
  -2.750   0.2844   0.01292   0.00632  -0.1262   0.6643   0.6094
  -2.500   0.3119   0.01336   0.00664  -0.1257   0.6562   0.6402
  -2.250   0.3340   0.01418   0.00736  -0.1234   0.6499   0.6611
  -2.000   0.3564   0.01471   0.00786  -0.1215   0.6422   0.6752
  -1.750   0.3809   0.01503   0.00807  -0.1203   0.6346   0.6840
  -1.500   0.4068   0.01521   0.00814  -0.1197   0.6270   0.6905
  -1.250   0.4283   0.01548   0.00836  -0.1178   0.6193   0.6959
  -1.000   0.4565   0.01570   0.00842  -0.1179   0.6123   0.7058
  -0.750   0.4751   0.01596   0.00870  -0.1152   0.6055   0.7105
  -0.500   0.5001   0.01613   0.00878  -0.1144   0.6001   0.7159
  -0.250   0.5316   0.01621   0.00875  -0.1155   0.5953   0.7232
   0.000   0.5519   0.01636   0.00894  -0.1135   0.5902   0.7269
   0.250   0.5748   0.01653   0.00908  -0.1122   0.5852   0.7328
   0.500   0.6037   0.01667   0.00912  -0.1126   0.5808   0.7411
   0.750   0.6202   0.01688   0.00938  -0.1095   0.5764   0.7472
   1.000   0.6466   0.01703   0.00953  -0.1093   0.5714   0.7576
   1.250   0.6609   0.01717   0.00971  -0.1056   0.5673   0.7645
   1.500   0.6913   0.01734   0.00978  -0.1064   0.5632   0.7743
   1.750   0.7066   0.01734   0.00985  -0.1033   0.5587   0.7791
   2.000   0.7303   0.01737   0.00991  -0.1025   0.5539   0.7847
   2.250   0.7632   0.01743   0.00991  -0.1041   0.5491   0.7901
   2.500   0.7903   0.01742   0.00985  -0.1042   0.5449   0.7928
   2.750   0.8135   0.01738   0.00987  -0.1035   0.5399   0.7951
   3.000   0.8389   0.01738   0.00991  -0.1032   0.5350   0.7978
   3.250   0.8670   0.01741   0.00991  -0.1036   0.5306   0.8007
   3.500   0.8967   0.01747   0.00997  -0.1044   0.5260   0.8034
   3.750   0.9267   0.01750   0.01006  -0.1055   0.5202   0.8059
   4.000   0.9589   0.01755   0.01012  -0.1070   0.5146   0.8079
   4.250   0.9845   0.01753   0.01011  -0.1068   0.5096   0.8096
   4.500   1.0073   0.01749   0.01017  -0.1060   0.5033   0.8117
   4.750   1.0327   0.01750   0.01022  -0.1058   0.4981   0.8139
   5.000   1.0602   0.01756   0.01029  -0.1060   0.4936   0.8160
   5.250   1.0869   0.01763   0.01046  -0.1063   0.4879   0.8182
   5.500   1.1151   0.01770   0.01059  -0.1068   0.4824   0.8202
   5.750   1.1452   0.01781   0.01067  -0.1077   0.4777   0.8217
   6.000   1.1731   0.01793   0.01093  -0.1083   0.4715   0.8231
   6.250   1.2017   0.01804   0.01111  -0.1090   0.4646   0.8244
   6.500   1.2286   0.01814   0.01126  -0.1093   0.4576   0.8257
   6.750   1.2516   0.01818   0.01144  -0.1088   0.4488   0.8271
   7.000   1.2742   0.01825   0.01160  -0.1081   0.4399   0.8289
   7.250   1.2966   0.01833   0.01175  -0.1074   0.4301   0.8309
   7.500   1.3200   0.01848   0.01198  -0.1070   0.4213   0.8325
   7.750   1.3433   0.01867   0.01221  -0.1066   0.4130   0.8341
   8.000   1.3667   0.01891   0.01256  -0.1063   0.4035   0.8357
   8.250   1.3883   0.01918   0.01289  -0.1057   0.3923   0.8373
   8.500   1.4090   0.01947   0.01329  -0.1049   0.3766   0.8390
   8.750   1.4259   0.01983   0.01366  -0.1035   0.3600   0.8407
   9.000   1.4400   0.02033   0.01413  -0.1017   0.3461   0.8423
   9.250   1.4524   0.02085   0.01471  -0.0996   0.3288   0.8439
   9.500   1.4618   0.02151   0.01540  -0.0971   0.3036   0.8458
   9.750   1.4627   0.02258   0.01635  -0.0935   0.2848   0.8480
  10.000   1.4695   0.02356   0.01738  -0.0910   0.2578   0.8506
  10.250   1.4633   0.02527   0.01894  -0.0872   0.2331   0.8532
  10.500   1.4613   0.02702   0.02066  -0.0845   0.2100   0.8557
  10.750   1.4525   0.02943   0.02293  -0.0817   0.1826   0.8578
  11.000   1.4457   0.03194   0.02542  -0.0795   0.1674   0.8600
  11.250   1.4405   0.03442   0.02789  -0.0777   0.1415   0.8626
  11.500   1.4290   0.03772   0.03111  -0.0761   0.1312   0.8652
  11.750   1.4242   0.04074   0.03420  -0.0752   0.1207   0.8677
  12.000   1.4257   0.04334   0.03687  -0.0748   0.1033   0.8702
  12.250   1.4184   0.04697   0.04043  -0.0746   0.0959   0.8725
  12.500   1.4102   0.05088   0.04434  -0.0745   0.0912   0.8748
  12.750   1.4031   0.05471   0.04824  -0.0745   0.0869   0.8769
  13.000   1.3994   0.05813   0.05180  -0.0745   0.0821   0.8794
  13.250   1.3996   0.06123   0.05504  -0.0746   0.0769   0.8822
  13.500   1.4032   0.06403   0.05797  -0.0748   0.0707   0.8854
  13.750   1.4055   0.06711   0.06112  -0.0753   0.0664   0.8888
  14.000   1.4041   0.07078   0.06481  -0.0760   0.0635   0.8921
  14.250   1.4000   0.07460   0.06868  -0.0765   0.0612   0.8957
  14.500   1.3938   0.07873   0.07280  -0.0770   0.0591   0.8996
  14.750   1.3912   0.08246   0.07659  -0.0775   0.0568   0.9039
  15.000   1.3918   0.08588   0.08010  -0.0781   0.0544   0.9086
  15.250   1.3922   0.08886   0.08307  -0.0781   0.0522   0.9139
  15.500   1.3962   0.09143   0.08572  -0.0781   0.0500   0.9213
  15.750   1.3978   0.09448   0.08898  -0.0786   0.0480   0.9335
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