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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 50,000
Max Cl/Cd: 38.34 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1712-il-50000-n5.txt
Download as CSV file: xf-hs1712-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-712 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3771   0.12035   0.11347  -0.0275   1.0000   0.1140
  -8.250  -0.3826   0.11750   0.11070  -0.0265   1.0000   0.1117
  -7.750  -0.4276   0.10696   0.10029  -0.0285   1.0000   0.0672
  -7.500  -0.4293   0.10390   0.09729  -0.0279   1.0000   0.0665
  -7.250  -0.4323   0.10042   0.09387  -0.0285   1.0000   0.0661
  -7.000  -0.4340   0.09662   0.09011  -0.0299   1.0000   0.0659
  -6.750  -0.4335   0.09251   0.08603  -0.0318   1.0000   0.0657
  -6.500  -0.4302   0.08808   0.08161  -0.0344   1.0000   0.0655
  -6.250  -0.4236   0.08335   0.07684  -0.0376   1.0000   0.0650
  -6.000  -0.4130   0.07809   0.07151  -0.0416   1.0000   0.0642
  -5.750  -0.3971   0.07208   0.06534  -0.0468   1.0000   0.0635
  -5.500  -0.3677   0.06561   0.05858  -0.0543   0.9978   0.0641
  -5.250  -0.3229   0.05726   0.04960  -0.0654   0.9942   0.0666
  -5.000  -0.2797   0.05100   0.04266  -0.0733   0.9909   0.0682
  -4.750  -0.2417   0.04816   0.03947  -0.0777   0.9868   0.0714
  -4.500  -0.1974   0.04412   0.03463  -0.0834   0.9841   0.0759
  -4.250  -0.1603   0.04228   0.03247  -0.0865   0.9802   0.0798
  -4.000  -0.1216   0.04029   0.02998  -0.0898   0.9761   0.0856
  -3.750  -0.0816   0.03887   0.02812  -0.0929   0.9726   0.0924
  -3.500  -0.0467   0.03804   0.02717  -0.0950   0.9674   0.0993
  -3.250  -0.0098   0.03715   0.02602  -0.0973   0.9623   0.1080
  -3.000   0.0297   0.03645   0.02502  -0.0999   0.9586   0.1187
  -2.750   0.0600   0.03599   0.02457  -0.1009   0.9515   0.1284
  -2.500   0.0970   0.03550   0.02399  -0.1030   0.9467   0.1415
  -2.250   0.1318   0.03512   0.02351  -0.1046   0.9408   0.1595
  -2.000   0.1658   0.03486   0.02312  -0.1060   0.9338   0.1847
  -1.750   0.2054   0.03463   0.02291  -0.1087   0.9293   0.2172
  -1.500   0.2331   0.03445   0.02275  -0.1091   0.9201   0.2494
  -1.250   0.2722   0.03411   0.02253  -0.1118   0.9146   0.2956
  -1.000   0.3016   0.03380   0.02239  -0.1125   0.9052   0.3392
  -0.750   0.3408   0.03315   0.02218  -0.1151   0.8990   0.4195
  -0.500   0.3558   0.03185   0.02225  -0.1116   0.8900   0.7519
  -0.250   0.3878   0.03124   0.02147  -0.1118   0.8809   1.0000
   0.250   0.4468   0.03158   0.02131  -0.1128   0.8608   1.0000
   0.500   0.4789   0.03166   0.02120  -0.1136   0.8512   1.0000
   0.750   0.5086   0.03175   0.02112  -0.1140   0.8403   1.0000
   1.000   0.5487   0.03147   0.02068  -0.1159   0.8328   1.0000
   1.250   0.5761   0.03153   0.02064  -0.1158   0.8203   1.0000
   1.500   0.6072   0.03147   0.02048  -0.1162   0.8096   1.0000
   1.750   0.6462   0.03105   0.01996  -0.1177   0.8021   1.0000
   2.000   0.6765   0.03094   0.01980  -0.1178   0.7912   1.0000
   2.250   0.7072   0.03081   0.01962  -0.1180   0.7802   1.0000
   2.500   0.7326   0.03091   0.01970  -0.1174   0.7666   1.0000
   2.750   0.7598   0.03089   0.01966  -0.1170   0.7533   1.0000
   3.000   0.7917   0.03062   0.01938  -0.1172   0.7415   1.0000
   3.250   0.8280   0.03014   0.01888  -0.1180   0.7309   1.0000
   3.500   0.8694   0.02943   0.01816  -0.1195   0.7205   1.0000
   3.750   0.9023   0.02920   0.01793  -0.1199   0.7057   1.0000
   4.000   0.9349   0.02904   0.01776  -0.1202   0.6896   1.0000
   4.250   0.9668   0.02893   0.01764  -0.1204   0.6718   1.0000
   4.500   0.9984   0.02888   0.01760  -0.1206   0.6529   1.0000
   4.750   1.0294   0.02886   0.01757  -0.1207   0.6326   1.0000
   5.000   1.0598   0.02891   0.01757  -0.1207   0.6115   1.0000
   5.250   1.0836   0.02920   0.01787  -0.1196   0.5886   1.0000
   5.500   1.1085   0.02948   0.01812  -0.1188   0.5659   1.0000
   5.750   1.1325   0.02986   0.01846  -0.1178   0.5435   1.0000
   6.000   1.1556   0.03028   0.01882  -0.1168   0.5219   1.0000
   6.250   1.1784   0.03077   0.01928  -0.1158   0.5018   1.0000
   6.500   1.2007   0.03133   0.01979  -0.1147   0.4828   1.0000
   6.750   1.2234   0.03191   0.02033  -0.1138   0.4651   1.0000
   7.000   1.2466   0.03254   0.02091  -0.1130   0.4485   1.0000
   7.250   1.2669   0.03325   0.02161  -0.1117   0.4320   1.0000
   7.500   1.2850   0.03405   0.02242  -0.1101   0.4161   1.0000
   7.750   1.3027   0.03487   0.02328  -0.1086   0.4006   1.0000
   8.000   1.3204   0.03572   0.02414  -0.1070   0.3860   1.0000
   8.250   1.3384   0.03657   0.02497  -0.1055   0.3720   1.0000
   8.500   1.3575   0.03741   0.02575  -0.1042   0.3583   1.0000
   8.750   1.3744   0.03838   0.02676  -0.1026   0.3450   1.0000
   9.000   1.3886   0.03948   0.02797  -0.1007   0.3322   1.0000
   9.250   1.4024   0.04059   0.02917  -0.0988   0.3200   1.0000
   9.500   1.4159   0.04167   0.03032  -0.0968   0.3081   1.0000
   9.750   1.4211   0.04299   0.03187  -0.0937   0.2963   1.0000
  10.000   1.4282   0.04428   0.03330  -0.0910   0.2851   1.0000
  10.250   1.4379   0.04540   0.03443  -0.0887   0.2747   1.0000
  10.500   1.4407   0.04701   0.03629  -0.0857   0.2635   1.0000
  10.750   1.4474   0.04844   0.03783  -0.0833   0.2536   1.0000
  11.000   1.4526   0.05003   0.03957  -0.0808   0.2437   1.0000
  11.250   1.4579   0.05176   0.04145  -0.0785   0.2344   1.0000
  11.500   1.4635   0.05342   0.04321  -0.0763   0.2254   1.0000
  11.750   1.4664   0.05549   0.04548  -0.0741   0.2165   1.0000
  12.000   1.4715   0.05728   0.04733  -0.0720   0.2083   1.0000
  12.250   1.4720   0.05969   0.04994  -0.0700   0.2000   1.0000
  12.500   1.4755   0.06173   0.05206  -0.0681   0.1925   1.0000
  12.750   1.4746   0.06440   0.05490  -0.0663   0.1853   1.0000
  13.000   1.4742   0.06698   0.05762  -0.0646   0.1784   1.0000
  13.250   1.4767   0.06936   0.06007  -0.0632   0.1724   1.0000
  13.500   1.4691   0.07301   0.06400  -0.0618   0.1666   1.0000
  13.750   1.4710   0.07540   0.06643  -0.0607   0.1609   1.0000
  14.000   1.4636   0.07916   0.07039  -0.0598   0.1560   1.0000
  14.250   1.4512   0.08372   0.07520  -0.0593   0.1514   1.0000
  14.500   1.4522   0.08638   0.07791  -0.0588   0.1464   1.0000
  14.750   1.4413   0.09099   0.08270  -0.0589   0.1423   1.0000
  15.000   1.4181   0.09777   0.08979  -0.0602   0.1389   1.0000
  15.250   1.4044   0.10323   0.09542  -0.0614   0.1350   1.0000
  15.500   1.4137   0.10476   0.09691  -0.0610   0.1304   1.0000
  15.750   1.3737   0.11561   0.10812  -0.0656   0.1284   1.0000
  16.000   1.3006   0.13523   0.12805  -0.0764   0.1270   1.0000
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