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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 50,000
Max Cl/Cd: 5.76 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxs21158-il-50000.txt
Download as CSV file: xf-fxs21158-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX S 02/1-158 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3004   0.12896   0.12271  -0.0220   1.0000   0.2686
 -10.750  -0.2974   0.12647   0.12030  -0.0224   1.0000   0.2817
 -10.500  -0.3044   0.12573   0.11965  -0.0229   1.0000   0.2942
 -10.250  -0.2820   0.12068   0.11462  -0.0226   1.0000   0.3074
 -10.000  -0.2662   0.11639   0.11038  -0.0228   1.0000   0.3163
  -9.750  -0.2648   0.11391   0.10796  -0.0232   1.0000   0.3267
  -9.500  -0.2709   0.11271   0.10689  -0.0234   1.0000   0.3386
  -9.250  -0.2487   0.10815   0.10237  -0.0235   1.0000   0.3492
  -9.000  -0.2398   0.10495   0.09928  -0.0237   1.0000   0.3580
  -8.750  -0.2398   0.10287   0.09735  -0.0238   1.0000   0.3692
  -8.500  -0.2462   0.10193   0.09661  -0.0235   1.0000   0.3811
  -8.250  -0.2300   0.09802   0.09289  -0.0236   1.0000   0.3856
  -8.000  -0.2445   0.09897   0.09416  -0.0229   0.9860   0.3894
  -7.750  -0.2918   0.08910   0.08437  -0.0433   0.9612   0.2806
  -7.500  -0.3786   0.06388   0.05902  -0.0795   0.9351   0.1632
  -7.250  -0.3720   0.05501   0.04945  -0.0911   0.9186   0.1483
  -7.000  -0.3512   0.04907   0.04253  -0.0978   0.9037   0.1385
  -6.750  -0.3197   0.04516   0.03811  -0.1014   0.8907   0.1366
  -6.500  -0.2884   0.04214   0.03446  -0.1041   0.8785   0.1377
  -6.250  -0.2528   0.03945   0.03126  -0.1062   0.8682   0.1376
  -6.000  -0.2260   0.03766   0.02906  -0.1064   0.8563   0.1370
  -5.750  -0.1978   0.03618   0.02725  -0.1065   0.8457   0.1375
  -5.500  -0.1634   0.03478   0.02554  -0.1069   0.8370   0.1393
  -5.250  -0.1372   0.03381   0.02453  -0.1059   0.8272   0.1425
  -5.000  -0.1137   0.03315   0.02391  -0.1046   0.8185   0.1477
  -4.750  -0.0875   0.03249   0.02318  -0.1036   0.8112   0.1555
  -4.500  -0.0720   0.03216   0.02294  -0.1022   0.8031   0.1677
  -4.250  -0.0496   0.03114   0.02211  -0.1022   0.7965   0.1955
  -4.000  -0.0398   0.02969   0.02210  -0.1018   0.7892   0.3084
  -3.750  -0.0357   0.03485   0.02765  -0.0895   0.7826   0.5710
  -3.500  -0.0395   0.03756   0.03045  -0.0784   0.7765   0.6214
  -3.250  -0.0402   0.03915   0.03200  -0.0701   0.7706   0.6617
  -3.000  -0.0360   0.04048   0.03329  -0.0592   0.7665   0.7155
  -2.750  -0.0462   0.04141   0.03423  -0.0524   0.7612   0.7403
  -2.500  -0.0484   0.04197   0.03472  -0.0471   0.7568   0.7655
  -2.250  -0.0342   0.04212   0.03466  -0.0441   0.7531   0.7887
  -2.000  -0.0345   0.04252   0.03495  -0.0411   0.7494   0.8010
  -1.750  -0.0513   0.04311   0.03554  -0.0376   0.7462   0.8082
  -1.500  -0.0583   0.04358   0.03595  -0.0347   0.7442   0.8162
  -1.250  -0.0597   0.04407   0.03634  -0.0330   0.7436   0.8239
  -1.000  -0.0556   0.04464   0.03680  -0.0322   0.7437   0.8308
  -0.750  -0.0465   0.04528   0.03729  -0.0327   0.7441   0.8362
  -0.500  -0.0358   0.04589   0.03778  -0.0328   0.7444   0.8408
  -0.250  -0.0237   0.04663   0.03839  -0.0335   0.7455   0.8463
   0.000  -0.0082   0.04747   0.03908  -0.0348   0.7479   0.8519
   0.250   0.0116   0.04841   0.03989  -0.0363   0.7520   0.8575
   0.500  -0.0084   0.04979   0.04130  -0.0352   0.7764   0.8624
   0.750  -0.2131   0.04502   0.03737  -0.0081   1.0000   0.8627
   1.000  -0.1777   0.04666   0.03879  -0.0123   0.9939   0.8703
   1.250  -0.1392   0.04846   0.04037  -0.0173   0.9842   0.8769
   1.500  -0.1031   0.05005   0.04176  -0.0217   0.9723   0.8837
   1.750  -0.0692   0.05155   0.04311  -0.0256   0.9599   0.8913
   2.000  -0.0357   0.05307   0.04451  -0.0294   0.9472   0.8990
   2.250  -0.0020   0.05468   0.04600  -0.0332   0.9345   0.9090
   2.500   0.0331   0.05644   0.04770  -0.0373   0.9231   0.9221
   2.750   0.0791   0.05902   0.05023  -0.0437   0.9120   0.9422
   3.000   0.1103   0.06034   0.05149  -0.0474   0.8975   1.0000
   3.250   0.1388   0.06176   0.05279  -0.0507   0.8842   1.0000
   3.500   0.1675   0.06340   0.05433  -0.0539   0.8713   1.0000
   3.750   0.1963   0.06523   0.05605  -0.0572   0.8590   1.0000
   4.000   0.2272   0.06742   0.05814  -0.0608   0.8491   1.0000
   4.250   0.2649   0.07015   0.06077  -0.0655   0.8395   1.0000
   4.500   0.2867   0.07164   0.06219  -0.0675   0.8272   1.0000
   4.750   0.3105   0.07351   0.06398  -0.0697   0.8156   1.0000
   5.000   0.3383   0.07584   0.06623  -0.0725   0.8054   1.0000
   5.250   0.3760   0.07894   0.06925  -0.0767   0.7954   1.0000
   5.500   0.3945   0.08045   0.07072  -0.0778   0.7824   1.0000
   5.750   0.4127   0.08220   0.07242  -0.0789   0.7702   1.0000
   6.000   0.4323   0.08429   0.07446  -0.0802   0.7600   1.0000
   6.250   0.4667   0.08754   0.07766  -0.0833   0.7521   1.0000
   6.500   0.4763   0.08883   0.07895  -0.0832   0.7404   1.0000
   6.750   0.4913   0.09088   0.08098  -0.0838   0.7309   1.0000
   7.000   0.5246   0.09431   0.08439  -0.0864   0.7229   1.0000
   7.250   0.5323   0.09563   0.08571  -0.0860   0.7109   1.0000
   7.500   0.5437   0.09765   0.08777  -0.0861   0.7012   1.0000
   7.750   0.5757   0.10127   0.09140  -0.0884   0.6939   1.0000
   8.000   0.5830   0.10272   0.09288  -0.0879   0.6813   1.0000
   8.250   0.5939   0.10473   0.09492  -0.0879   0.6693   1.0000
   8.500   0.6083   0.10723   0.09747  -0.0884   0.6595   1.0000
   8.750   0.6375   0.11076   0.10109  -0.0901   0.6506   1.0000
   9.000   0.6395   0.11224   0.10262  -0.0895   0.6392   1.0000
   9.250   0.6498   0.11480   0.10524  -0.0898   0.6307   1.0000
   9.500   0.6752   0.11827   0.10880  -0.0912   0.6221   1.0000
   9.750   0.6779   0.12003   0.11063  -0.0908   0.6106   1.0000
  10.000   0.6874   0.12257   0.11326  -0.0911   0.6000   1.0000
  10.250   0.7144   0.12668   0.11752  -0.0925   0.5914   1.0000
  10.500   0.7256   0.12901   0.11995  -0.0928   0.5788   1.0000
  10.750   0.7289   0.13102   0.12205  -0.0927   0.5666   1.0000
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