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FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 63-158 AIRFOIL (fx63158-il)
Reynolds number: 100,000
Max Cl/Cd: 47.53 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63158-il-100000.txt
Download as CSV file: xf-fx63158-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3037   0.10531   0.10096  -0.0455   1.0000   0.1106
  -9.250  -0.3149   0.10258   0.09834  -0.0459   1.0000   0.1147
  -9.000  -0.3589   0.09959   0.09557  -0.0484   1.0000   0.1165
  -8.750  -0.3286   0.09786   0.09386  -0.0430   1.0000   0.1212
  -8.500  -0.3481   0.09676   0.09293  -0.0402   1.0000   0.1242
  -8.250  -0.3933   0.09148   0.08781  -0.0510   0.9912   0.1276
  -8.000  -0.3626   0.08743   0.08377  -0.0548   0.9843   0.1387
  -7.750  -0.3355   0.08328   0.07961  -0.0585   0.9748   0.1497
  -7.500  -0.3281   0.07759   0.07392  -0.0663   0.9600   0.1621
  -6.000  -0.1919   0.03719   0.03008  -0.1103   0.8861   0.0713
  -5.750  -0.1472   0.03343   0.02564  -0.1129   0.8786   0.0615
  -5.500  -0.0982   0.03008   0.02200  -0.1167   0.8741   0.0602
  -5.250  -0.0666   0.02799   0.01969  -0.1169   0.8618   0.0582
  -5.000  -0.0262   0.02593   0.01729  -0.1178   0.8536   0.0551
  -4.750   0.0095   0.02453   0.01576  -0.1181   0.8438   0.0542
  -4.500   0.0401   0.02339   0.01463  -0.1177   0.8336   0.0545
  -4.250   0.0733   0.02233   0.01363  -0.1181   0.8248   0.0559
  -4.000   0.0975   0.02173   0.01299  -0.1174   0.8139   0.0582
  -3.750   0.1323   0.02097   0.01207  -0.1188   0.8061   0.0628
  -3.500   0.1557   0.02054   0.01160  -0.1183   0.7959   0.0728
  -3.250   0.1788   0.01833   0.01179  -0.1188   0.7890   0.5183
  -3.000   0.1838   0.02187   0.01545  -0.1087   0.7798   0.6728
  -2.750   0.1961   0.02353   0.01699  -0.1015   0.7730   0.6983
  -2.500   0.2110   0.02449   0.01783  -0.0969   0.7659   0.7193
  -2.250   0.2263   0.02513   0.01836  -0.0928   0.7586   0.7367
  -2.000   0.2516   0.02548   0.01851  -0.0905   0.7533   0.7524
  -1.750   0.2601   0.02588   0.01889  -0.0858   0.7454   0.7675
  -1.500   0.2813   0.02604   0.01892  -0.0832   0.7392   0.7840
  -1.250   0.3041   0.02606   0.01880  -0.0816   0.7334   0.7976
  -1.000   0.3149   0.02618   0.01888  -0.0787   0.7257   0.8102
  -0.750   0.3397   0.02616   0.01872  -0.0776   0.7206   0.8238
  -0.500   0.3599   0.02612   0.01862  -0.0756   0.7156   0.8358
  -0.250   0.3675   0.02624   0.01873  -0.0724   0.7087   0.8461
   0.000   0.3924   0.02615   0.01852  -0.0718   0.7035   0.8570
   0.250   0.4130   0.02605   0.01836  -0.0705   0.6978   0.8649
   0.500   0.4220   0.02618   0.01849  -0.0678   0.6907   0.8725
   0.750   0.4513   0.02595   0.01814  -0.0683   0.6855   0.8789
   1.000   0.4647   0.02606   0.01824  -0.0662   0.6790   0.8843
   1.250   0.4800   0.02615   0.01831  -0.0648   0.6724   0.8889
   1.500   0.5162   0.02592   0.01793  -0.0666   0.6671   0.8923
   1.750   0.5193   0.02619   0.01827  -0.0631   0.6593   0.8965
   2.000   0.5507   0.02588   0.01787  -0.0638   0.6523   0.9004
   2.250   0.5728   0.02587   0.01782  -0.0632   0.6452   0.9045
   2.500   0.5911   0.02595   0.01789  -0.0622   0.6374   0.9080
   2.750   0.6347   0.02541   0.01719  -0.0647   0.6313   0.9110
   3.000   0.6372   0.02579   0.01769  -0.0612   0.6229   0.9147
   3.250   0.6741   0.02545   0.01726  -0.0629   0.6167   0.9170
   3.500   0.6927   0.02567   0.01750  -0.0621   0.6096   0.9194
   3.750   0.7175   0.02573   0.01757  -0.0622   0.6025   0.9215
   4.000   0.7583   0.02547   0.01723  -0.0646   0.5977   0.9239
   4.250   0.7638   0.02602   0.01793  -0.0618   0.5904   0.9275
   4.500   0.7879   0.02608   0.01802  -0.0616   0.5847   0.9314
   4.750   0.8250   0.02596   0.01785  -0.0634   0.5808   0.9344
   5.000   0.8342   0.02672   0.01879  -0.0616   0.5737   0.9368
   5.250   0.8609   0.02699   0.01911  -0.0622   0.5681   0.9387
   5.500   0.8991   0.02697   0.01909  -0.0644   0.5642   0.9403
   5.750   0.9107   0.02772   0.01999  -0.0629   0.5573   0.9427
   6.000   0.9367   0.02792   0.02029  -0.0633   0.5512   0.9450
   6.250   0.9781   0.02759   0.01995  -0.0656   0.5469   0.9476
   6.500   0.9859   0.02852   0.02107  -0.0636   0.5391   0.9514
   6.750   1.0177   0.02849   0.02112  -0.0647   0.5328   0.9542
   7.000   1.0613   0.02798   0.02060  -0.0672   0.5274   0.9564
   7.250   1.0687   0.02872   0.02155  -0.0651   0.5177   0.9602
   7.500   1.1190   0.02779   0.02060  -0.0683   0.5118   0.9627
   7.750   1.1238   0.02874   0.02180  -0.0660   0.5023   0.9675
   8.000   1.1669   0.02822   0.02133  -0.0684   0.4964   0.9709
   8.250   1.1820   0.02891   0.02225  -0.0676   0.4879   0.9773
   8.500   1.2209   0.02859   0.02202  -0.0696   0.4808   0.9867
   8.750   1.2448   0.02896   0.02258  -0.0700   0.4726   1.0000
   9.000   1.2748   0.02898   0.02274  -0.0709   0.4640   1.0000
   9.250   1.2963   0.02930   0.02323  -0.0707   0.4543   1.0000
   9.500   1.3346   0.02868   0.02268  -0.0724   0.4443   1.0000
   9.750   1.3419   0.02929   0.02352  -0.0703   0.4324   1.0000
  10.000   1.3624   0.02932   0.02369  -0.0698   0.4201   1.0000
  10.250   1.3868   0.02922   0.02368  -0.0698   0.4069   1.0000
  10.500   1.4040   0.02954   0.02411  -0.0690   0.3924   1.0000
  10.750   1.4089   0.03058   0.02533  -0.0672   0.3764   1.0000
  11.000   1.4158   0.03162   0.02649  -0.0659   0.3591   1.0000
  11.250   1.4227   0.03288   0.02781  -0.0648   0.3402   1.0000
  11.500   1.4189   0.03511   0.03017  -0.0635   0.3183   1.0000
  11.750   1.4159   0.03745   0.03243  -0.0624   0.2938   1.0000
  12.000   1.4081   0.04052   0.03538  -0.0616   0.2681   1.0000
  12.250   1.3942   0.04455   0.03936  -0.0613   0.2409   1.0000
  12.500   1.3810   0.04873   0.04335  -0.0611   0.2166   1.0000
  12.750   1.3669   0.05337   0.04791  -0.0614   0.1919   1.0000
  13.000   1.3557   0.05763   0.05187  -0.0615   0.1748   1.0000
  13.250   1.3499   0.06163   0.05583  -0.0618   0.1560   1.0000
  13.500   1.3465   0.06555   0.05970  -0.0625   0.1423   1.0000
  13.750   1.3483   0.06866   0.06260  -0.0627   0.1311   1.0000
  14.000   1.3569   0.07104   0.06487  -0.0625   0.1193   1.0000
  14.250   1.3641   0.07386   0.06776  -0.0629   0.1104   1.0000
  14.500   1.3709   0.07673   0.07065  -0.0635   0.1036   1.0000
  14.750   1.3799   0.07921   0.07302  -0.0642   0.0977   1.0000
  15.000   1.3912   0.08152   0.07535  -0.0645   0.0916   1.0000
  15.250   1.4090   0.08312   0.07691  -0.0643   0.0857   1.0000
  15.500   1.4334   0.08403   0.07768  -0.0639   0.0797   1.0000
  15.750   1.4306   0.08820   0.08222  -0.0652   0.0771   1.0000
  16.000   1.4369   0.09124   0.08542  -0.0661   0.0738   1.0000
  16.250   1.4435   0.09421   0.08850  -0.0670   0.0708   1.0000
  16.500   1.4424   0.09824   0.09279  -0.0685   0.0684   1.0000
  16.750   1.4505   0.10082   0.09539  -0.0695   0.0657   1.0000
  17.000   1.4562   0.10401   0.09873  -0.0705   0.0635   1.0000
  17.250   1.4553   0.10809   0.10305  -0.0721   0.0616   1.0000
  17.500   1.4816   0.10833   0.10308  -0.0716   0.0578   1.0000
  17.750   1.4665   0.11435   0.10949  -0.0744   0.0568   1.0000
  18.000   1.4542   0.12018   0.11564  -0.0773   0.0554   1.0000
  18.250   1.4724   0.12141   0.11670  -0.0773   0.0507   1.0000
  18.500   1.4503   0.12863   0.12429  -0.0815   0.0500   1.0000
  18.750   1.4287   0.13623   0.13223  -0.0861   0.0494   1.0000
  19.000   1.4070   0.14427   0.14058  -0.0913   0.0490   1.0000
  19.250   1.3843   0.15295   0.14955  -0.0971   0.0488   1.0000
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