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HAM-STD HS1-430 AIRFOIL (hs1430-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-430 AIRFOIL (hs1430-il)
Reynolds number: 100,000
Max Cl/Cd: 28.74 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1430-il-100000.txt
Download as CSV file: xf-hs1430-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-430 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6238   0.09978   0.09302  -0.0588   0.9547   0.2285
 -10.250  -0.7812   0.08627   0.07902  -0.0471   0.9489   0.2275
 -10.000  -0.8705   0.08096   0.07339  -0.0337   0.9396   0.2275
  -9.750  -0.9301   0.07588   0.06783  -0.0239   0.9330   0.2287
  -9.500  -0.9389   0.07240   0.06414  -0.0203   0.9267   0.2306
  -9.250  -0.9003   0.07184   0.06375  -0.0228   0.9211   0.2330
  -9.000  -0.8691   0.07130   0.06330  -0.0242   0.9157   0.2357
  -8.750  -0.8625   0.06991   0.06183  -0.0220   0.9099   0.2381
  -8.500  -0.8595   0.06794   0.05968  -0.0194   0.9047   0.2409
  -8.250  -0.8651   0.06602   0.05751  -0.0153   0.8986   0.2433
  -8.000  -0.8604   0.06390   0.05506  -0.0127   0.8934   0.2461
  -7.750  -0.8623   0.06257   0.05339  -0.0086   0.8866   0.2483
  -7.500  -0.8431   0.06053   0.05134  -0.0085   0.8822   0.2510
  -7.250  -0.8076   0.05961   0.05049  -0.0107   0.8793   0.2543
  -7.000  -0.8013   0.05920   0.05009  -0.0076   0.8716   0.2565
  -6.750  -0.7721   0.05827   0.04909  -0.0086   0.8671   0.2598
  -6.500  -0.7468   0.05730   0.04798  -0.0088   0.8629   0.2633
  -6.250  -0.7416   0.05672   0.04725  -0.0056   0.8550   0.2660
  -6.000  -0.7114   0.05580   0.04605  -0.0065   0.8510   0.2695
  -5.750  -0.6980   0.05470   0.04485  -0.0048   0.8442   0.2721
  -5.500  -0.6733   0.05376   0.04397  -0.0050   0.8378   0.2754
  -5.250  -0.6328   0.05287   0.04310  -0.0076   0.8341   0.2795
  -5.000  -0.6181   0.05265   0.04286  -0.0059   0.8269   0.2827
  -4.750  -0.5957   0.05217   0.04231  -0.0054   0.8199   0.2862
  -4.500  -0.5550   0.05123   0.04122  -0.0077   0.8159   0.2907
  -4.250  -0.5358   0.05102   0.04087  -0.0066   0.8086   0.2938
  -4.000  -0.5157   0.05029   0.04009  -0.0058   0.8007   0.2972
  -3.750  -0.4713   0.04902   0.03890  -0.0089   0.7966   0.3020
  -3.500  -0.4199   0.04777   0.03767  -0.0128   0.7937   0.3075
  -3.250  -0.4249   0.04841   0.03831  -0.0079   0.7806   0.3102
  -3.000  -0.3850   0.04756   0.03738  -0.0099   0.7759   0.3158
  -2.750  -0.3375   0.04649   0.03618  -0.0130   0.7729   0.3211
  -2.500  -0.3312   0.04663   0.03637  -0.0100   0.7612   0.3247
  -2.250  -0.2936   0.04562   0.03548  -0.0115   0.7545   0.3308
  -2.000  -0.2413   0.04408   0.03399  -0.0151   0.7510   0.3387
  -1.750  -0.1857   0.04233   0.03216  -0.0191   0.7485   0.3470
  -1.500  -0.1880   0.04312   0.03296  -0.0145   0.7330   0.3506
  -1.250  -0.1425   0.04166   0.03170  -0.0171   0.7289   0.3594
  -1.000  -0.0954   0.04027   0.03036  -0.0198   0.7261   0.3693
  -0.750  -0.0441   0.03864   0.02873  -0.0232   0.7243   0.3796
  -0.500  -0.0395   0.03926   0.02953  -0.0196   0.7113   0.3863
  -0.250  -0.0041   0.03825   0.02863  -0.0204   0.7049   0.3985
   0.000   0.0461   0.03646   0.02701  -0.0235   0.7019   0.4155
   0.250   0.1024   0.03437   0.02514  -0.0275   0.6996   0.4423
   0.500   0.1617   0.03185   0.02321  -0.0321   0.6974   0.5059
   0.750   0.2276   0.02944   0.02182  -0.0368   0.6949   0.7114
   1.000   0.2014   0.03121   0.02389  -0.0265   0.6759   0.7540
   1.250   0.3094   0.03007   0.02281  -0.0381   0.6708   0.8314
   1.500   0.3232   0.03119   0.02398  -0.0345   0.6544   0.8559
   1.750   0.4406   0.03072   0.02323  -0.0489   0.6407   0.8771
   2.000   0.4692   0.03174   0.02422  -0.0481   0.6176   0.8894
   2.250   0.4867   0.03231   0.02469  -0.0454   0.5929   0.9063
   2.500   0.5317   0.03323   0.02542  -0.0482   0.5534   0.9131
   2.750   0.5528   0.03367   0.02549  -0.0466   0.5162   0.9281
   3.000   0.5984   0.03468   0.02605  -0.0501   0.4744   0.9335
   3.250   0.6411   0.03565   0.02663  -0.0533   0.4477   0.9426
   3.500   0.6890   0.03660   0.02730  -0.0576   0.4295   0.9530
   3.750   0.7555   0.03734   0.02767  -0.0655   0.4158   0.9613
   4.000   0.8037   0.03803   0.02828  -0.0701   0.4061   0.9717
   4.250   0.8638   0.03838   0.02842  -0.0771   0.3978   0.9784
   4.500   0.9218   0.03876   0.02857  -0.0838   0.3913   0.9868
   4.750   0.9718   0.03900   0.02880  -0.0891   0.3856   0.9929
   5.000   1.0276   0.03928   0.02899  -0.0955   0.3804   0.9997
   5.250   1.0457   0.03937   0.02899  -0.0948   0.3773   1.0000
   5.500   1.0653   0.03944   0.02894  -0.0943   0.3744   1.0000
   5.750   1.1028   0.03952   0.02881  -0.0972   0.3711   1.0000
   6.000   1.1068   0.03976   0.02908  -0.0938   0.3691   1.0000
   6.250   1.1118   0.04001   0.02937  -0.0905   0.3671   1.0000
   6.500   1.1181   0.04029   0.02968  -0.0874   0.3651   1.0000
   6.750   1.1255   0.04060   0.03000  -0.0845   0.3631   1.0000
   7.000   1.1340   0.04095   0.03035  -0.0818   0.3612   1.0000
   7.250   1.1446   0.04132   0.03071  -0.0794   0.3592   1.0000
   7.500   1.1574   0.04172   0.03108  -0.0774   0.3572   1.0000
   7.750   1.1741   0.04212   0.03143  -0.0761   0.3550   1.0000
   8.000   1.2004   0.04251   0.03171  -0.0765   0.3525   1.0000
   8.250   1.2395   0.04313   0.03217  -0.0795   0.3495   1.0000
   8.500   1.2306   0.04384   0.03300  -0.0734   0.3481   1.0000
   8.750   1.2241   0.04464   0.03392  -0.0679   0.3465   1.0000
   9.000   1.2177   0.04555   0.03493  -0.0625   0.3447   1.0000
   9.250   1.2117   0.04653   0.03601  -0.0573   0.3428   1.0000
   9.500   1.2072   0.04754   0.03710  -0.0525   0.3406   1.0000
   9.750   1.2071   0.04851   0.03813  -0.0484   0.3384   1.0000
  10.000   1.2158   0.04932   0.03893  -0.0459   0.3358   1.0000
  10.250   1.2405   0.04984   0.03936  -0.0459   0.3331   1.0000
  10.500   1.2991   0.05036   0.03963  -0.0518   0.3297   1.0000
  10.750   1.2622   0.05209   0.04160  -0.0419   0.3282   1.0000
  11.000   1.2237   0.05428   0.04404  -0.0325   0.3264   1.0000
  11.250   1.1811   0.05704   0.04704  -0.0233   0.3242   1.0000
  11.500   1.1349   0.06048   0.05071  -0.0146   0.3218   1.0000
  11.750   1.0895   0.06446   0.05491  -0.0069   0.3191   1.0000
  12.000   1.0708   0.06735   0.05789  -0.0026   0.3162   1.0000
  12.250   1.1317   0.06572   0.05603  -0.0062   0.3133   1.0000
  12.500   1.1762   0.06580   0.05596  -0.0085   0.3105   1.0000
  12.750   0.3331   0.16893   0.16118   0.0047   0.3370   1.0000
  13.000   0.3538   0.17075   0.16297   0.0044   0.3337   1.0000
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