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HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il)
Reynolds number: 100,000
Max Cl/Cd: 43.63 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1620-il-100000.txt
Download as CSV file: xf-hs1620-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-620 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.7123   0.08801   0.08264  -0.0367   1.0000   0.1299
  -9.000  -0.7381   0.08229   0.07683  -0.0349   1.0000   0.1294
  -8.750  -0.7724   0.07415   0.06841  -0.0335   1.0000   0.1289
  -8.500  -0.8161   0.06194   0.05532  -0.0322   1.0000   0.1296
  -8.250  -0.8086   0.05991   0.05321  -0.0308   1.0000   0.1315
  -8.000  -0.7870   0.06144   0.05498  -0.0295   0.9997   0.1335
  -7.750  -0.7547   0.05744   0.05054  -0.0340   0.9931   0.1376
  -7.500  -0.7351   0.05161   0.04385  -0.0367   0.9865   0.1425
  -7.250  -0.6914   0.05253   0.04502  -0.0400   0.9811   0.1460
  -7.000  -0.6646   0.05036   0.04250  -0.0415   0.9734   0.1509
  -6.750  -0.6284   0.04852   0.04028  -0.0446   0.9687   0.1562
  -6.500  -0.6007   0.04828   0.04013  -0.0452   0.9604   0.1601
  -6.250  -0.5662   0.04649   0.03770  -0.0477   0.9561   0.1674
  -6.000  -0.5403   0.04615   0.03755  -0.0481   0.9485   0.1712
  -5.750  -0.5034   0.04577   0.03709  -0.0504   0.9432   0.1774
  -5.500  -0.4757   0.04473   0.03574  -0.0513   0.9366   0.1839
  -5.250  -0.4453   0.04462   0.03573  -0.0524   0.9307   0.1892
  -5.000  -0.4039   0.04408   0.03477  -0.0554   0.9270   0.1983
  -4.750  -0.3846   0.04359   0.03444  -0.0546   0.9184   0.2030
  -4.500  -0.3474   0.04336   0.03412  -0.0568   0.9136   0.2115
  -4.250  -0.3170   0.04285   0.03347  -0.0579   0.9079   0.2189
  -4.000  -0.2902   0.04266   0.03332  -0.0583   0.9007   0.2262
  -3.750  -0.2485   0.04225   0.03268  -0.0612   0.8968   0.2363
  -3.500  -0.2283   0.04203   0.03257  -0.0605   0.8890   0.2429
  -3.250  -0.1935   0.04184   0.03223  -0.0621   0.8833   0.2529
  -3.000  -0.1499   0.04125   0.03169  -0.0653   0.8801   0.2630
  -2.750  -0.1352   0.04135   0.03177  -0.0636   0.8707   0.2706
  -2.500  -0.0962   0.04090   0.03126  -0.0659   0.8659   0.2812
  -2.250  -0.0499   0.04047   0.03087  -0.0694   0.8629   0.2938
  -2.000  -0.0391   0.04071   0.03104  -0.0670   0.8521   0.3010
  -1.750   0.0061   0.04002   0.03049  -0.0702   0.8478   0.3141
  -1.500   0.0307   0.03985   0.03028  -0.0698   0.8372   0.3245
  -1.250   0.0817   0.03866   0.02921  -0.0734   0.8310   0.3406
  -1.000   0.1119   0.03810   0.02875  -0.0736   0.8204   0.3540
  -0.750   0.1572   0.03707   0.02781  -0.0762   0.8141   0.3731
  -0.500   0.2077   0.03585   0.02679  -0.0796   0.8110   0.3980
  -0.250   0.2210   0.03617   0.02725  -0.0774   0.7987   0.4187
   0.000   0.2664   0.03481   0.02635  -0.0799   0.7947   0.4769
   0.250   0.3074   0.03276   0.02601  -0.0790   0.7927   0.8720
   0.500   0.4036   0.03214   0.02523  -0.0911   0.7896   1.0000
   0.750   0.4153   0.03230   0.02526  -0.0882   0.7772   1.0000
   1.000   0.4684   0.03087   0.02366  -0.0918   0.7745   1.0000
   1.250   0.5287   0.02923   0.02187  -0.0967   0.7728   1.0000
   1.500   0.5333   0.02965   0.02222  -0.0924   0.7583   1.0000
   1.750   0.5960   0.02797   0.02042  -0.0978   0.7555   1.0000
   2.000   0.6754   0.02607   0.01839  -0.1066   0.7531   1.0000
   2.250   0.6827   0.02625   0.01852  -0.1023   0.7384   1.0000
   2.500   0.7710   0.02441   0.01654  -0.1132   0.7333   1.0000
   2.750   0.7872   0.02439   0.01647  -0.1105   0.7181   1.0000
   3.000   0.8356   0.02366   0.01562  -0.1139   0.7054   1.0000
   3.250   0.8874   0.02293   0.01473  -0.1181   0.6910   1.0000
   3.500   0.9061   0.02290   0.01463  -0.1158   0.6725   1.0000
   3.750   0.9285   0.02281   0.01443  -0.1142   0.6529   1.0000
   4.000   0.9512   0.02275   0.01424  -0.1127   0.6318   1.0000
   4.250   0.9733   0.02273   0.01407  -0.1111   0.6093   1.0000
   4.500   0.9947   0.02280   0.01393  -0.1094   0.5858   1.0000
   4.750   1.0044   0.02310   0.01412  -0.1055   0.5611   1.0000
   5.000   1.0186   0.02343   0.01428  -0.1026   0.5377   1.0000
   5.250   1.0352   0.02382   0.01447  -0.1003   0.5165   1.0000
   5.500   1.0541   0.02427   0.01473  -0.0985   0.4975   1.0000
   5.750   1.0760   0.02477   0.01503  -0.0974   0.4807   1.0000
   6.000   1.1027   0.02529   0.01532  -0.0973   0.4657   1.0000
   6.250   1.1168   0.02592   0.01592  -0.0948   0.4522   1.0000
   6.500   1.1432   0.02654   0.01638  -0.0948   0.4403   1.0000
   6.750   1.1656   0.02714   0.01689  -0.0940   0.4291   1.0000
   7.000   1.1893   0.02783   0.01750  -0.0935   0.4191   1.0000
   7.250   1.2133   0.02846   0.01805  -0.0931   0.4097   1.0000
   7.500   1.2401   0.02920   0.01871  -0.0933   0.4011   1.0000
   7.750   1.2581   0.02989   0.01940  -0.0917   0.3928   1.0000
   8.000   1.2982   0.03066   0.01996  -0.0946   0.3848   1.0000
   8.250   1.3052   0.03143   0.02089  -0.0909   0.3780   1.0000
   8.500   1.3295   0.03215   0.02155  -0.0906   0.3708   1.0000
   8.750   1.3641   0.03304   0.02233  -0.0925   0.3640   1.0000
   9.000   1.3697   0.03390   0.02334  -0.0886   0.3581   1.0000
   9.250   1.3920   0.03468   0.02410  -0.0880   0.3517   1.0000
   9.500   1.4344   0.03566   0.02491  -0.0914   0.3452   1.0000
   9.750   1.4321   0.03661   0.02609  -0.0862   0.3404   1.0000
  10.000   1.4436   0.03754   0.02710  -0.0837   0.3349   1.0000
  10.250   1.4836   0.03834   0.02775  -0.0865   0.3288   1.0000
  10.500   1.4975   0.03954   0.02904  -0.0846   0.3239   1.0000
  10.750   1.4934   0.04071   0.03042  -0.0794   0.3195   1.0000
  11.000   1.5045   0.04174   0.03151  -0.0770   0.3145   1.0000
  11.250   1.5539   0.04254   0.03210  -0.0815   0.3085   1.0000
  11.500   1.5495   0.04398   0.03375  -0.0765   0.3047   1.0000
  11.750   1.5397   0.04546   0.03546  -0.0708   0.3006   1.0000
  12.000   1.5428   0.04675   0.03687  -0.0675   0.2962   1.0000
  12.250   1.5767   0.04746   0.03747  -0.0690   0.2912   1.0000
  12.500   1.5911   0.04901   0.03907  -0.0677   0.2870   1.0000
  12.750   1.5671   0.05112   0.04148  -0.0605   0.2837   1.0000
  13.000   1.5560   0.05310   0.04366  -0.0557   0.2799   1.0000
  13.250   1.5630   0.05448   0.04510  -0.0535   0.2758   1.0000
  13.500   1.6301   0.05452   0.04484  -0.0596   0.2704   1.0000
  13.750   1.5832   0.05772   0.04844  -0.0504   0.2682   1.0000
  14.000   1.5378   0.06169   0.05278  -0.0427   0.2654   1.0000
  14.250   1.4993   0.06598   0.05734  -0.0369   0.2623   1.0000
  14.500   1.4921   0.06860   0.06007  -0.0345   0.2586   1.0000
  14.750   1.5960   0.06491   0.05596  -0.0416   0.2533   1.0000
  15.000   1.5161   0.07185   0.06336  -0.0328   0.2515   1.0000
  15.250   0.8097   0.18723   0.18009  -0.0636   0.2748   1.0000
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