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HSNLF(1)-0213 AIRFOIL (hsnlf213-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HSNLF(1)-0213 AIRFOIL (hsnlf213-il)
Reynolds number: 50,000
Max Cl/Cd: 28.31 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hsnlf213-il-50000.txt
Download as CSV file: xf-hsnlf213-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HSNLF(1)-0213 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5449   0.15269   0.14619   0.0029   1.0000   0.2095
 -12.250  -0.5188   0.14654   0.14002   0.0035   1.0000   0.2181
 -12.000  -0.5434   0.14615   0.13975  -0.0006   1.0000   0.2257
 -11.750  -0.5102   0.13965   0.13320   0.0007   1.0000   0.2376
 -11.500  -0.5034   0.13564   0.12923  -0.0004   1.0000   0.2466
 -11.250  -0.5266   0.13475   0.12845  -0.0037   1.0000   0.2570
 -11.000  -0.5051   0.12980   0.12349  -0.0032   1.0000   0.2717
 -10.750  -0.4951   0.12597   0.11968  -0.0036   1.0000   0.2871
 -10.500  -0.4902   0.12261   0.11635  -0.0041   1.0000   0.3031
 -10.250  -0.4898   0.11960   0.11338  -0.0048   1.0000   0.3195
 -10.000  -0.4813   0.11581   0.10963  -0.0050   1.0000   0.3363
  -9.500  -0.4470   0.10758   0.10139  -0.0050   1.0000   0.3714
  -9.250  -0.4339   0.10411   0.09793  -0.0049   1.0000   0.3914
  -8.750  -0.4127   0.09759   0.09145  -0.0045   1.0000   0.4366
  -8.500  -0.4034   0.09434   0.08820  -0.0047   1.0000   0.4549
  -8.000  -0.4754   0.07640   0.07103  -0.0221   1.0000   0.2683
  -7.750  -0.5232   0.07351   0.06827  -0.0193   1.0000   0.2747
  -7.500  -0.5690   0.07083   0.06568  -0.0156   1.0000   0.2743
  -7.250  -0.6187   0.06781   0.06267  -0.0124   1.0000   0.2731
  -7.000  -0.6691   0.05758   0.05187  -0.0148   1.0000   0.1972
  -6.750  -0.7195   0.05796   0.05048  -0.0138   1.0000   0.1500
  -6.500  -0.7077   0.05418   0.04651  -0.0122   1.0000   0.1420
  -6.250  -0.6997   0.05053   0.04206  -0.0100   1.0000   0.1312
  -6.000  -0.6855   0.04714   0.03836  -0.0085   1.0000   0.1271
  -5.750  -0.6697   0.04411   0.03481  -0.0069   1.0000   0.1240
  -5.500  -0.6517   0.04164   0.03194  -0.0056   1.0000   0.1250
  -5.250  -0.6313   0.03938   0.02925  -0.0044   1.0000   0.1266
  -5.000  -0.6079   0.03723   0.02670  -0.0034   1.0000   0.1275
  -4.750  -0.5836   0.03545   0.02451  -0.0024   1.0000   0.1307
  -4.500  -0.5589   0.03371   0.02261  -0.0017   1.0000   0.1371
  -4.250  -0.5329   0.03232   0.02112  -0.0008   1.0000   0.1444
  -4.000  -0.1361   0.03243   0.02370  -0.0364   1.0000   1.0000
  -3.750  -0.1340   0.03221   0.02330  -0.0340   1.0000   1.0000
  -3.500  -0.1310   0.03202   0.02294  -0.0315   1.0000   1.0000
  -3.250  -0.1273   0.03187   0.02261  -0.0291   1.0000   1.0000
  -3.000  -0.1228   0.03174   0.02233  -0.0267   1.0000   1.0000
  -2.750  -0.1178   0.03164   0.02208  -0.0243   1.0000   1.0000
  -2.500  -0.1123   0.03156   0.02184  -0.0219   1.0000   1.0000
  -2.250  -0.1064   0.03151   0.02166  -0.0196   1.0000   1.0000
  -2.000  -0.1001   0.03147   0.02150  -0.0173   1.0000   1.0000
  -1.750  -0.0936   0.03146   0.02136  -0.0149   1.0000   1.0000
  -1.500  -0.0869   0.03146   0.02126  -0.0126   1.0000   1.0000
  -1.250  -0.0800   0.03148   0.02118  -0.0104   1.0000   1.0000
  -1.000  -0.0729   0.03151   0.02111  -0.0081   1.0000   1.0000
  -0.750  -0.0659   0.03156   0.02108  -0.0058   1.0000   1.0000
  -0.500  -0.0587   0.03162   0.02107  -0.0035   1.0000   1.0000
  -0.250  -0.0517   0.03170   0.02108  -0.0013   1.0000   1.0000
   0.000  -0.0446   0.03179   0.02111   0.0010   1.0000   1.0000
   0.250  -0.0377   0.03189   0.02115   0.0033   1.0000   1.0000
   0.500  -0.0309   0.03200   0.02122   0.0055   1.0000   1.0000
   0.750  -0.0242   0.03213   0.02131   0.0078   1.0000   1.0000
   1.000  -0.0177   0.03226   0.02142   0.0100   1.0000   1.0000
   1.250  -0.0115   0.03240   0.02154   0.0123   1.0000   1.0000
   1.500  -0.0054   0.03255   0.02168   0.0145   1.0000   1.0000
   1.750   0.0005   0.03271   0.02184   0.0167   1.0000   1.0000
   2.000   0.0063   0.03289   0.02202   0.0189   1.0000   1.0000
   2.250   0.0121   0.03309   0.02222   0.0210   1.0000   1.0000
   2.500   0.0182   0.03332   0.02247   0.0229   1.0000   1.0000
   2.750   0.0259   0.03364   0.02280   0.0245   1.0000   1.0000
   3.000   0.0357   0.03407   0.02326   0.0256   1.0000   1.0000
   3.250   0.0475   0.03463   0.02385   0.0261   1.0000   1.0000
   3.500   0.0610   0.03533   0.02458   0.0263   1.0000   1.0000
   3.750   0.0756   0.03614   0.02544   0.0261   1.0000   1.0000
   4.000   0.0911   0.03708   0.02643   0.0257   1.0000   1.0000
   4.250   0.1069   0.03813   0.02754   0.0250   1.0000   1.0000
   4.500   0.2703   0.04396   0.03370   0.0000   0.8975   1.0000
   4.750   0.3245   0.04580   0.03573  -0.0051   0.8644   1.0000
   5.000   0.3653   0.04704   0.03714  -0.0076   0.8336   1.0000
   5.250   0.4060   0.04802   0.03831  -0.0096   0.8027   1.0000
   5.500   0.4459   0.04862   0.03915  -0.0109   0.7714   1.0000
   5.750   0.4859   0.04875   0.03950  -0.0116   0.7391   1.0000
   6.000   0.5296   0.04817   0.03922  -0.0118   0.7061   1.0000
   6.250   0.5884   0.04607   0.03749  -0.0120   0.6711   1.0000
   6.500   0.6600   0.04160   0.03353  -0.0113   0.6324   1.0000
   6.750   0.7219   0.03524   0.02769  -0.0072   0.5845   1.0000
   7.000   0.7893   0.02788   0.01899   0.0015   0.3648   1.0000
   7.250   0.7825   0.02965   0.01993   0.0071   0.2967   1.0000
   7.500   0.7943   0.03144   0.02116   0.0098   0.2468   1.0000
   7.750   0.8310   0.03337   0.02271   0.0094   0.2083   1.0000
   8.000   0.8659   0.03527   0.02456   0.0090   0.1861   1.0000
   8.250   0.8959   0.03731   0.02662   0.0090   0.1719   1.0000
   8.500   0.9206   0.03945   0.02884   0.0093   0.1616   1.0000
   8.750   0.9448   0.04178   0.03139   0.0097   0.1549   1.0000
   9.000   0.9695   0.04474   0.03445   0.0098   0.1502   1.0000
   9.250   0.9804   0.04741   0.03766   0.0114   0.1467   1.0000
   9.500   0.9917   0.05021   0.04084   0.0126   0.1428   1.0000
   9.750   1.0055   0.05323   0.04410   0.0134   0.1397   1.0000
  10.000   1.0128   0.05684   0.04807   0.0145   0.1390   1.0000
  10.250   1.0095   0.06080   0.05252   0.0162   0.1395   1.0000
  10.500   0.9950   0.06520   0.05739   0.0180   0.1410   1.0000
  10.750   0.9718   0.06991   0.06243   0.0197   0.1430   1.0000
  11.000   0.9413   0.07476   0.06751   0.0209   0.1451   1.0000
  11.250   0.9123   0.08042   0.07332   0.0205   0.1473   1.0000
  11.500   0.8932   0.08647   0.07946   0.0193   0.1494   1.0000
  11.750   0.7798   0.10519   0.09821   0.0065   0.1618   1.0000
  12.000   0.7181   0.12565   0.11851  -0.0085   0.1995   1.0000
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