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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 500,000
Max Cl/Cd: 102.2 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1404-il-500000-n5.txt
Download as CSV file: xf-hs1404-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-404 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4565   0.09530   0.09303  -0.0086   1.0000   0.0036
  -7.750  -0.4511   0.09203   0.08979  -0.0101   1.0000   0.0037
  -7.500  -0.4463   0.08883   0.08662  -0.0117   1.0000   0.0037
  -7.250  -0.4385   0.08530   0.08311  -0.0144   1.0000   0.0037
  -7.000  -0.4283   0.08156   0.07938  -0.0178   1.0000   0.0037
  -6.750  -0.4168   0.07766   0.07551  -0.0215   1.0000   0.0037
  -6.500  -0.4043   0.07359   0.07145  -0.0255   1.0000   0.0037
  -6.250  -0.3908   0.06942   0.06729  -0.0294   1.0000   0.0036
  -5.250  -0.2701   0.04959   0.04718  -0.0565   0.9889   0.0029
  -5.000  -0.2282   0.04279   0.04022  -0.0655   0.9854   0.0028
  -4.750  -0.1842   0.03574   0.03294  -0.0734   0.9827   0.0027
  -4.500  -0.1423   0.02813   0.02498  -0.0794   0.9782   0.0027
  -4.250  -0.1007   0.02013   0.01633  -0.0838   0.9746   0.0028
  -3.750  -0.0304   0.01339   0.00838  -0.0877   0.9667   0.0039
  -3.500   0.0004   0.01248   0.00730  -0.0885   0.9610   0.0047
  -3.250   0.0310   0.01240   0.00718  -0.0893   0.9558   0.0070
  -3.000   0.0613   0.01117   0.00570  -0.0896   0.9487   0.0072
  -2.750   0.0919   0.01000   0.00431  -0.0900   0.9426   0.0070
  -2.500   0.1211   0.00917   0.00329  -0.0901   0.9352   0.0069
  -2.250   0.1503   0.00855   0.00254  -0.0901   0.9285   0.0069
  -2.000   0.1788   0.00815   0.00199  -0.0900   0.9208   0.0070
  -1.750   0.2070   0.00789   0.00158  -0.0899   0.9129   0.0073
  -1.500   0.2345   0.00771   0.00129  -0.0895   0.9028   0.0139
  -1.250   0.2616   0.00718   0.00120  -0.0895   0.8900   0.1462
  -1.000   0.2883   0.00725   0.00101  -0.0890   0.8764   0.1196
  -0.250   0.3698   0.00699   0.00099  -0.0885   0.8405   0.2417
   0.000   0.3974   0.00694   0.00098  -0.0884   0.8314   0.2615
   0.250   0.4251   0.00683   0.00099  -0.0885   0.8234   0.3107
   0.750   0.4734   0.00527   0.00108  -0.0869   0.8054   1.0000
   1.000   0.5009   0.00534   0.00111  -0.0868   0.7948   1.0000
   1.250   0.5284   0.00542   0.00115  -0.0866   0.7822   1.0000
   1.500   0.5556   0.00551   0.00119  -0.0864   0.7647   1.0000
   1.750   0.5815   0.00569   0.00121  -0.0858   0.7204   1.0000
   2.000   0.6046   0.00623   0.00126  -0.0848   0.6017   1.0000
   2.250   0.6265   0.00727   0.00161  -0.0839   0.4387   1.0000
   2.500   0.6508   0.00801   0.00189  -0.0836   0.3322   1.0000
   2.750   0.6767   0.00844   0.00211  -0.0834   0.2784   1.0000
   3.000   0.7018   0.00903   0.00239  -0.0832   0.2014   1.0000
   3.250   0.7252   0.01001   0.00283  -0.0828   0.0841   1.0000
   3.500   0.7510   0.01046   0.00316  -0.0826   0.0535   1.0000
   3.750   0.7772   0.01082   0.00349  -0.0823   0.0395   1.0000
   4.000   0.8033   0.01120   0.00397  -0.0820   0.0300   1.0000
   4.250   0.8291   0.01166   0.00444  -0.0817   0.0222   1.0000
   4.500   0.8552   0.01200   0.00486  -0.0814   0.0185   1.0000
   4.750   0.8808   0.01240   0.00521  -0.0812   0.0113   1.0000
   5.000   0.9061   0.01283   0.00558  -0.0809   0.0046   1.0000
   5.250   0.9309   0.01349   0.00628  -0.0804   0.0022   1.0000
   5.500   0.9545   0.01451   0.00750  -0.0794   0.0015   1.0000
   5.750   0.9776   0.01563   0.00883  -0.0784   0.0014   1.0000
   6.000   0.9994   0.01719   0.01071  -0.0771   0.0012   1.0000
   6.250   1.0205   0.01918   0.01301  -0.0757   0.0012   1.0000
   6.500   1.0410   0.02182   0.01604  -0.0740   0.0012   1.0000
   6.750   1.0597   0.02546   0.02021  -0.0719   0.0012   1.0000
   7.000   1.0740   0.03058   0.02599  -0.0692   0.0012   1.0000
   7.250   1.0817   0.03765   0.03371  -0.0657   0.0013   1.0000
   7.500   1.0859   0.04464   0.04120  -0.0624   0.0013   1.0000
   7.750   1.0871   0.05108   0.04802  -0.0597   0.0014   1.0000
   8.000   1.0850   0.05723   0.05449  -0.0574   0.0014   1.0000
   8.250   1.0794   0.06312   0.06064  -0.0557   0.0014   1.0000
   8.500   1.0701   0.06879   0.06651  -0.0544   0.0015   1.0000
   8.750   1.0559   0.07398   0.07185  -0.0534   0.0015   1.0000
   9.000   1.0381   0.07885   0.07683  -0.0532   0.0015   1.0000
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