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FX S 02/1-158 AIRFOIL (fxs21158-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX S 02/1-158 AIRFOIL (fxs21158-il)
Reynolds number: 200,000
Max Cl/Cd: 76.76 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxs21158-il-200000.txt
Download as CSV file: xf-fxs21158-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3452   0.11767   0.11447  -0.0359   1.0000   0.0425
 -11.250  -0.3484   0.11260   0.10945  -0.0396   1.0000   0.0428
 -11.000  -0.3506   0.10730   0.10421  -0.0428   1.0000   0.0429
 -10.750  -0.3521   0.10161   0.09858  -0.0428   1.0000   0.0439
 -10.500  -0.3337   0.10139   0.09838  -0.0395   1.0000   0.0464
 -10.250  -0.3311   0.09781   0.09486  -0.0407   1.0000   0.0488
 -10.000  -0.2244   0.07446   0.07130  -0.0662   0.8070   0.0684
  -9.750  -0.2439   0.06593   0.06270  -0.0717   0.7867   0.0682
  -9.500  -0.2556   0.05993   0.05657  -0.0747   0.7634   0.0686
  -9.250  -0.2352   0.06127   0.05772  -0.0710   0.7296   0.0819
  -9.000  -0.3754   0.05236   0.04872  -0.0912   0.8123   0.0393
  -8.750  -0.3983   0.04628   0.04210  -0.0929   0.7776   0.0365
  -8.500  -0.4027   0.04227   0.03759  -0.0929   0.7506   0.0373
  -8.250  -0.3984   0.03923   0.03400  -0.0925   0.7291   0.0403
  -8.000  -0.3930   0.03630   0.03037  -0.0923   0.7118   0.0446
  -7.000  -0.3143   0.02993   0.02260  -0.0913   0.6603   0.0555
  -6.750  -0.2903   0.02824   0.02058  -0.0909   0.6510   0.0554
  -6.500  -0.2639   0.02745   0.01954  -0.0905   0.6416   0.0544
  -6.250  -0.2392   0.02507   0.01696  -0.0902   0.6350   0.0537
  -6.000  -0.2135   0.02352   0.01522  -0.0899   0.6274   0.0533
  -5.750  -0.1874   0.02235   0.01383  -0.0895   0.6215   0.0533
  -5.500  -0.1612   0.02134   0.01271  -0.0892   0.6148   0.0535
  -5.250  -0.1351   0.02051   0.01175  -0.0888   0.6090   0.0538
  -5.000  -0.1089   0.01985   0.01098  -0.0884   0.6035   0.0544
  -4.750  -0.0847   0.01875   0.00994  -0.0880   0.5979   0.0562
  -4.500  -0.0592   0.01808   0.00924  -0.0878   0.5935   0.0580
  -4.250  -0.0333   0.01752   0.00864  -0.0877   0.5889   0.0593
  -4.000  -0.0067   0.01699   0.00807  -0.0877   0.5842   0.0613
  -3.750   0.0206   0.01655   0.00751  -0.0879   0.5802   0.0646
  -3.500   0.0481   0.01599   0.00684  -0.0882   0.5767   0.0716
  -3.250   0.0719   0.01387   0.00617  -0.0895   0.5729   0.4094
  -3.000   0.1002   0.01457   0.00677  -0.0890   0.5692   0.4856
  -2.750   0.1280   0.01502   0.00714  -0.0886   0.5660   0.5060
  -2.500   0.1559   0.01540   0.00740  -0.0883   0.5633   0.5199
  -2.250   0.1828   0.01591   0.00794  -0.0877   0.5599   0.5408
  -2.000   0.2092   0.01635   0.00842  -0.0869   0.5567   0.5574
  -1.750   0.2362   0.01662   0.00869  -0.0864   0.5538   0.5681
  -1.500   0.2643   0.01670   0.00867  -0.0864   0.5512   0.5738
  -1.250   0.2927   0.01682   0.00867  -0.0866   0.5490   0.5776
  -1.000   0.3208   0.01686   0.00870  -0.0868   0.5461   0.5817
  -0.750   0.3495   0.01692   0.00868  -0.0872   0.5433   0.5860
  -0.500   0.3773   0.01695   0.00870  -0.0873   0.5406   0.5888
  -0.250   0.4054   0.01704   0.00875  -0.0874   0.5383   0.5925
   0.000   0.4341   0.01716   0.00878  -0.0877   0.5361   0.5972
   0.250   0.4623   0.01731   0.00887  -0.0879   0.5336   0.6020
   0.500   0.4890   0.01740   0.00904  -0.0878   0.5301   0.6066
   0.750   0.5169   0.01750   0.00913  -0.0880   0.5269   0.6111
   1.000   0.5457   0.01758   0.00912  -0.0884   0.5240   0.6146
   1.250   0.5741   0.01764   0.00914  -0.0886   0.5216   0.6168
   1.500   0.6019   0.01778   0.00928  -0.0888   0.5189   0.6190
   1.750   0.6290   0.01788   0.00945  -0.0889   0.5155   0.6214
   2.000   0.6568   0.01798   0.00956  -0.0891   0.5123   0.6244
   2.250   0.6852   0.01808   0.00963  -0.0894   0.5095   0.6277
   2.500   0.7138   0.01821   0.00970  -0.0897   0.5073   0.6305
   2.750   0.7417   0.01841   0.00993  -0.0899   0.5053   0.6330
   3.000   0.7679   0.01861   0.01026  -0.0899   0.5023   0.6359
   3.250   0.7949   0.01879   0.01051  -0.0900   0.4993   0.6392
   3.500   0.8228   0.01896   0.01070  -0.0903   0.4966   0.6432
   3.750   0.8508   0.01905   0.01081  -0.0904   0.4941   0.6467
   4.000   0.8793   0.01921   0.01096  -0.0907   0.4919   0.6504
   4.250   0.9046   0.01947   0.01136  -0.0906   0.4885   0.6544
   4.500   0.9313   0.01958   0.01155  -0.0906   0.4841   0.6589
   4.750   0.9595   0.01942   0.01140  -0.0906   0.4798   0.6631
   5.000   0.9868   0.01942   0.01141  -0.0906   0.4751   0.6686
   5.250   1.0125   0.01939   0.01149  -0.0903   0.4691   0.6745
   5.500   1.0406   0.01926   0.01141  -0.0903   0.4650   0.6802
   5.750   1.0691   0.01941   0.01156  -0.0906   0.4623   0.6873
   6.000   1.0923   0.01961   0.01202  -0.0901   0.4583   0.6941
   6.500   1.1447   0.01980   0.01248  -0.0899   0.4518   0.7127
   6.750   1.1726   0.01982   0.01260  -0.0899   0.4492   0.7253
   7.000   1.1950   0.01977   0.01280  -0.0891   0.4428   0.7419
   7.250   1.2211   0.01882   0.01191  -0.0883   0.4318   0.7675
   7.750   1.2677   0.01774   0.01133  -0.0864   0.4122   1.0000
   8.000   1.2945   0.01768   0.01127  -0.0864   0.4057   1.0000
   8.250   1.3168   0.01766   0.01138  -0.0856   0.3931   1.0000
   8.500   1.3395   0.01770   0.01153  -0.0849   0.3793   1.0000
   8.750   1.3621   0.01783   0.01175  -0.0842   0.3657   1.0000
   9.000   1.3824   0.01801   0.01192  -0.0831   0.3471   1.0000
   9.250   1.3901   0.01876   0.01237  -0.0804   0.2881   1.0000
   9.500   1.3794   0.02068   0.01386  -0.0756   0.2249   1.0000
   9.750   1.3574   0.02292   0.01582  -0.0696   0.1775   1.0000
  10.000   1.3397   0.02523   0.01801  -0.0651   0.1413   1.0000
  10.250   1.3178   0.02843   0.02111  -0.0619   0.1230   1.0000
  10.500   1.2984   0.03224   0.02486  -0.0604   0.0964   1.0000
  10.750   1.2834   0.03616   0.02875  -0.0597   0.0861   1.0000
  11.250   1.2560   0.04436   0.03692  -0.0591   0.0547   1.0000
  11.500   1.2482   0.04798   0.04060  -0.0590   0.0425   1.0000
  11.750   1.2340   0.05234   0.04493  -0.0590   0.0351   1.0000
  12.000   1.2220   0.05654   0.04920  -0.0590   0.0286   1.0000
  12.250   1.2049   0.06150   0.05422  -0.0592   0.0236   1.0000
  12.500   1.2031   0.06486   0.05770  -0.0594   0.0203   1.0000
  12.750   1.1994   0.06854   0.06146  -0.0598   0.0179   1.0000
  13.000   1.1939   0.07251   0.06550  -0.0603   0.0165   1.0000
  13.250   1.1920   0.07614   0.06922  -0.0608   0.0154   1.0000
  13.500   1.1921   0.07956   0.07274  -0.0614   0.0146   1.0000
  13.750   1.1939   0.08279   0.07603  -0.0619   0.0134   1.0000
  14.000   1.1956   0.08604   0.07933  -0.0626   0.0124   1.0000
  14.250   1.1946   0.08973   0.08307  -0.0634   0.0116   1.0000
  14.500   1.1925   0.09357   0.08698  -0.0641   0.0112   1.0000
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