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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 100,000
Max Cl/Cd: 37.37 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxs21158-il-100000.txt
Download as CSV file: xf-fxs21158-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3480   0.12245   0.11804  -0.0358   1.0000   0.1018
 -11.000  -0.3231   0.11860   0.11420  -0.0326   1.0000   0.1113
 -10.750  -0.3431   0.11520   0.11092  -0.0380   1.0000   0.1144
 -10.500  -0.3191   0.11165   0.10738  -0.0350   1.0000   0.1244
 -10.250  -0.3255   0.10763   0.10347  -0.0374   1.0000   0.1295
 -10.000  -0.3296   0.10500   0.10093  -0.0393   1.0000   0.1395
  -9.750  -0.3098   0.10189   0.09785  -0.0372   1.0000   0.1497
  -9.500  -0.3199   0.09811   0.09422  -0.0397   1.0000   0.1560
  -9.250  -0.3226   0.09550   0.09174  -0.0410   1.0000   0.1663
  -9.000  -0.3021   0.09263   0.08895  -0.0393   1.0000   0.1746
  -8.750  -0.2840   0.08871   0.08514  -0.0442   0.9528   0.1901
  -8.500  -0.2407   0.08288   0.07905  -0.0552   0.8929   0.2129
  -8.250  -0.2092   0.07907   0.07492  -0.0602   0.8437   0.2289
  -8.000  -0.1952   0.07644   0.07208  -0.0615   0.8119   0.2436
  -7.750  -0.1860   0.07398   0.06947  -0.0620   0.7896   0.2572
  -7.500  -0.3415   0.04570   0.04025  -0.0963   0.7905   0.1260
  -7.250  -0.3251   0.03998   0.03361  -0.0970   0.7768   0.0998
  -7.000  -0.3050   0.03663   0.02932  -0.0968   0.7637   0.0890
  -6.750  -0.2817   0.03377   0.02621  -0.0967   0.7517   0.0865
  -6.500  -0.2577   0.03153   0.02358  -0.0963   0.7399   0.0840
  -6.250  -0.2325   0.02971   0.02135  -0.0959   0.7295   0.0825
  -6.000  -0.2063   0.02821   0.01945  -0.0954   0.7207   0.0818
  -5.750  -0.1805   0.02708   0.01817  -0.0951   0.7114   0.0841
  -5.500  -0.1542   0.02610   0.01700  -0.0947   0.7038   0.0863
  -5.250  -0.1277   0.02513   0.01590  -0.0941   0.6966   0.0871
  -5.000  -0.1017   0.02430   0.01498  -0.0934   0.6900   0.0881
  -4.750  -0.0763   0.02364   0.01427  -0.0926   0.6830   0.0897
  -4.500  -0.0532   0.02288   0.01361  -0.0915   0.6773   0.0929
  -4.250  -0.0295   0.02240   0.01317  -0.0908   0.6705   0.0980
  -4.000  -0.0045   0.02176   0.01243  -0.0906   0.6655   0.1069
  -3.750   0.0207   0.02080   0.01161  -0.0912   0.6600   0.1361
  -3.500   0.0401   0.02130   0.01358  -0.0890   0.6550   0.5168
  -3.250   0.0623   0.02276   0.01499  -0.0859   0.6509   0.5571
  -3.000   0.0795   0.02422   0.01663  -0.0813   0.6461   0.5898
  -2.750   0.0960   0.02530   0.01779  -0.0767   0.6414   0.6195
  -2.500   0.1170   0.02570   0.01811  -0.0741   0.6375   0.6375
  -2.250   0.1424   0.02573   0.01798  -0.0740   0.6337   0.6473
  -2.000   0.1670   0.02580   0.01799  -0.0738   0.6294   0.6548
  -1.750   0.1923   0.02582   0.01790  -0.0736   0.6257   0.6631
  -1.500   0.2192   0.02584   0.01777  -0.0737   0.6227   0.6716
  -1.250   0.2446   0.02591   0.01776  -0.0738   0.6196   0.6774
  -1.000   0.2696   0.02608   0.01791  -0.0741   0.6157   0.6822
  -0.750   0.2981   0.02618   0.01791  -0.0753   0.6123   0.6867
  -0.500   0.3258   0.02623   0.01785  -0.0759   0.6095   0.6905
  -0.250   0.3532   0.02631   0.01783  -0.0761   0.6071   0.6942
   0.000   0.3779   0.02672   0.01826  -0.0769   0.6032   0.6977
   0.250   0.4045   0.02707   0.01859  -0.0779   0.5993   0.7006
   0.500   0.4329   0.02732   0.01875  -0.0790   0.5962   0.7036
   0.750   0.4597   0.02752   0.01891  -0.0792   0.5939   0.7066
   1.000   0.4876   0.02779   0.01911  -0.0797   0.5919   0.7099
   1.250   0.5077   0.02881   0.02027  -0.0803   0.5883   0.7129
   1.500   0.5309   0.02968   0.02117  -0.0812   0.5852   0.7160
   1.750   0.5557   0.03026   0.02175  -0.0817   0.5822   0.7192
   2.000   0.5829   0.03049   0.02195  -0.0818   0.5795   0.7228
   2.250   0.6075   0.03109   0.02258  -0.0821   0.5763   0.7270
   2.500   0.6205   0.03277   0.02439  -0.0823   0.5711   0.7309
   2.750   0.6425   0.03361   0.02526  -0.0826   0.5680   0.7345
   3.000   0.6676   0.03414   0.02582  -0.0827   0.5657   0.7387
   3.250   0.6955   0.03461   0.02629  -0.0831   0.5639   0.7440
   3.500   0.6814   0.03890   0.03083  -0.0825   0.5594   0.7482
   3.750   0.6491   0.04439   0.03650  -0.0811   0.5557   0.7518
   4.000   0.6190   0.04912   0.04131  -0.0793   0.5534   0.7560
   4.250   0.6726   0.04814   0.04033  -0.0810   0.5509   0.7629
   4.500   0.7304   0.04633   0.03854  -0.0819   0.5493   0.7707
   4.750   0.5875   0.06086   0.05317  -0.0788   0.5623   0.7713
   5.000   0.5998   0.06324   0.05560  -0.0793   0.5629   0.7787
   5.250   0.5239   0.07233   0.06481  -0.0806   0.6078   0.7809
   5.500   0.5180   0.07386   0.06638  -0.0793   0.5985   0.7887
   5.750   0.5470   0.07545   0.06808  -0.0803   0.5943   0.8008
   6.000   0.5498   0.07728   0.07000  -0.0798   0.5873   0.8130
   6.250   0.5745   0.07861   0.07149  -0.0802   0.5806   0.8349
   6.500   0.5832   0.08028   0.07344  -0.0803   0.5728   0.8927
   6.750   0.6101   0.08174   0.07492  -0.0812   0.5658   1.0000
   7.000   0.6150   0.08385   0.07702  -0.0816   0.5566   1.0000
   7.250   0.6519   0.08568   0.07882  -0.0832   0.5507   1.0000
   7.500   0.6508   0.08773   0.08087  -0.0830   0.5402   1.0000
   7.750   0.6933   0.08965   0.08282  -0.0844   0.5355   1.0000
   8.000   0.6843   0.09173   0.08490  -0.0838   0.5244   1.0000
   8.250   0.7419   0.09366   0.08687  -0.0853   0.5201   1.0000
   8.500   0.7300   0.09530   0.08853  -0.0843   0.5075   1.0000
   8.750   0.7276   0.09757   0.09082  -0.0840   0.4965   1.0000
   9.000   0.7421   0.09946   0.09275  -0.0839   0.4859   1.0000
   9.250   0.8230   0.09234   0.08568  -0.0799   0.4413   1.0000
   9.500   0.8566   0.09176   0.08517  -0.0789   0.4306   1.0000
   9.750   0.9300   0.08600   0.07956  -0.0764   0.4191   1.0000
  10.000   1.3416   0.04002   0.03426  -0.0735   0.4197   1.0000
  10.250   1.3725   0.03673   0.03108  -0.0714   0.4037   1.0000
  10.500   1.2920   0.04585   0.04032  -0.0658   0.4040   1.0000
  10.750   0.9874   0.08909   0.08304  -0.0738   0.3806   1.0000
  11.000   1.0473   0.08411   0.07831  -0.0715   0.3775   1.0000
  11.250   1.0412   0.08730   0.08158  -0.0716   0.3657   1.0000
  11.500   1.1779   0.06865   0.06334  -0.0652   0.3622   1.0000
  12.000   1.2161   0.06570   0.06070  -0.0626   0.3309   1.0000
  12.250   1.1978   0.07070   0.06579  -0.0632   0.3145   1.0000
  12.500   1.2496   0.06343   0.05790  -0.0598   0.2131   1.0000
  12.750   1.2269   0.06848   0.06249  -0.0598   0.1723   1.0000
  13.000   1.2067   0.07403   0.06782  -0.0606   0.1383   1.0000
  13.250   1.1863   0.07992   0.07348  -0.0616   0.1066   1.0000
  13.500   1.1684   0.08567   0.07897  -0.0628   0.0898   1.0000
  13.750   1.1531   0.09131   0.08443  -0.0639   0.0665   1.0000
  14.000   1.1392   0.09685   0.08975  -0.0651   0.0547   1.0000
  14.250   1.1304   0.10160   0.09444  -0.0657   0.0436   1.0000
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