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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 100,000
Max Cl/Cd: 60.7 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1712-il-100000.txt
Download as CSV file: xf-hs1712-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4120   0.11162   0.10706  -0.0201   1.0000   0.1026
  -7.500  -0.4395   0.11044   0.10600  -0.0202   1.0000   0.1042
  -7.250  -0.4584   0.10684   0.10247  -0.0290   1.0000   0.1054
  -7.000  -0.4488   0.10341   0.09908  -0.0211   1.0000   0.1066
  -6.750  -0.4434   0.10083   0.09653  -0.0177   1.0000   0.1086
  -6.500  -0.4422   0.09829   0.09402  -0.0170   1.0000   0.1118
  -6.250  -0.4403   0.09290   0.08851  -0.0358   1.0000   0.1187
  -6.000  -0.4396   0.08997   0.08572  -0.0279   1.0000   0.1201
  -5.750  -0.4358   0.08795   0.08377  -0.0236   1.0000   0.1225
  -5.500  -0.4116   0.08292   0.07844  -0.0397   1.0000   0.1337
  -5.250  -0.4087   0.07966   0.07532  -0.0354   1.0000   0.1350
  -5.000  -0.4026   0.07733   0.07306  -0.0326   1.0000   0.1371
  -4.750  -0.3660   0.07280   0.06817  -0.0448   0.9994   0.1504
  -4.500  -0.3392   0.06903   0.06451  -0.0451   0.9944   0.1536
  -4.250  -0.2374   0.04722   0.04082  -0.0731   0.9941   0.0940
  -4.000  -0.1872   0.04261   0.03566  -0.0794   0.9895   0.0921
  -3.750  -0.1323   0.03856   0.03062  -0.0858   0.9859   0.0936
  -3.500  -0.0873   0.03731   0.02937  -0.0901   0.9810   0.0990
  -3.250  -0.0395   0.03555   0.02687  -0.0941   0.9753   0.1053
  -3.000   0.0085   0.03478   0.02608  -0.0986   0.9714   0.1148
  -2.750   0.0468   0.03391   0.02505  -0.1011   0.9632   0.1238
  -2.500   0.0950   0.03338   0.02438  -0.1052   0.9590   0.1371
  -2.250   0.1296   0.03301   0.02388  -0.1069   0.9503   0.1503
  -2.000   0.1743   0.03255   0.02347  -0.1104   0.9460   0.1698
  -1.750   0.2097   0.03221   0.02323  -0.1122   0.9382   0.1984
  -1.500   0.2526   0.03179   0.02283  -0.1154   0.9323   0.2420
  -1.250   0.3008   0.03126   0.02253  -0.1196   0.9290   0.2877
  -1.000   0.3277   0.03101   0.02242  -0.1199   0.9184   0.3227
  -0.750   0.3734   0.03048   0.02222  -0.1236   0.9145   0.3885
  -0.500   0.4007   0.02940   0.02251  -0.1234   0.9072   0.7045
  -0.250   0.4253   0.02851   0.02174  -0.1214   0.8988   1.0000
   0.000   0.4551   0.02855   0.02156  -0.1218   0.8877   1.0000
   0.250   0.5031   0.02811   0.02090  -0.1253   0.8822   1.0000
   0.500   0.5313   0.02810   0.02078  -0.1254   0.8706   1.0000
   0.750   0.5793   0.02749   0.02002  -0.1287   0.8657   1.0000
   1.000   0.6060   0.02751   0.01997  -0.1285   0.8541   1.0000
   1.250   0.6526   0.02681   0.01918  -0.1315   0.8495   1.0000
   1.500   0.6807   0.02675   0.01907  -0.1314   0.8385   1.0000
   1.750   0.7273   0.02583   0.01809  -0.1342   0.8339   1.0000
   2.000   0.7580   0.02552   0.01776  -0.1342   0.8233   1.0000
   2.250   0.8058   0.02433   0.01654  -0.1370   0.8186   1.0000
   2.500   0.8405   0.02376   0.01597  -0.1376   0.8083   1.0000
   2.750   0.8956   0.02241   0.01460  -0.1419   0.8030   1.0000
   3.000   0.9374   0.02163   0.01383  -0.1438   0.7922   1.0000
   3.250   0.9815   0.02081   0.01300  -0.1461   0.7799   1.0000
   3.500   1.0108   0.02052   0.01272  -0.1457   0.7613   1.0000
   3.750   1.0476   0.01993   0.01211  -0.1466   0.7425   1.0000
   4.000   1.0955   0.01921   0.01127  -0.1496   0.7223   1.0000
   4.250   1.1310   0.01912   0.01104  -0.1504   0.6955   1.0000
   4.500   1.1622   0.01922   0.01100  -0.1504   0.6660   1.0000
   4.750   1.1828   0.01952   0.01122  -0.1485   0.6338   1.0000
   5.000   1.2046   0.01985   0.01140  -0.1469   0.6018   1.0000
   5.250   1.2267   0.02021   0.01158  -0.1454   0.5718   1.0000
   5.500   1.2465   0.02069   0.01194  -0.1436   0.5427   1.0000
   5.750   1.2660   0.02120   0.01234  -0.1418   0.5167   1.0000
   6.000   1.2865   0.02175   0.01276  -0.1403   0.4940   1.0000
   6.250   1.3076   0.02235   0.01325  -0.1390   0.4737   1.0000
   6.500   1.3289   0.02299   0.01379  -0.1377   0.4551   1.0000
   6.750   1.3500   0.02366   0.01439  -0.1365   0.4377   1.0000
   7.000   1.3707   0.02435   0.01501  -0.1352   0.4211   1.0000
   7.250   1.3914   0.02505   0.01567  -0.1340   0.4056   1.0000
   7.500   1.4131   0.02579   0.01633  -0.1330   0.3913   1.0000
   7.750   1.4343   0.02653   0.01701  -0.1320   0.3774   1.0000
   8.000   1.4531   0.02729   0.01781  -0.1304   0.3637   1.0000
   8.250   1.4745   0.02816   0.01866  -0.1295   0.3507   1.0000
   8.500   1.4969   0.02910   0.01957  -0.1288   0.3378   1.0000
   8.750   1.5196   0.03007   0.02049  -0.1282   0.3249   1.0000
   9.000   1.5314   0.03082   0.02141  -0.1253   0.3123   1.0000
   9.250   1.5422   0.03158   0.02231  -0.1223   0.3000   1.0000
   9.500   1.5535   0.03230   0.02307  -0.1195   0.2883   1.0000
   9.750   1.5617   0.03300   0.02379  -0.1160   0.2764   1.0000
  10.000   1.5641   0.03384   0.02478  -0.1116   0.2642   1.0000
  10.250   1.5696   0.03478   0.02576  -0.1079   0.2522   1.0000
  10.500   1.5771   0.03577   0.02666  -0.1047   0.2400   1.0000
  10.750   1.5781   0.03695   0.02802  -0.1005   0.2276   1.0000
  11.000   1.5833   0.03825   0.02937  -0.0972   0.2158   1.0000
  11.250   1.5919   0.03954   0.03057  -0.0946   0.2052   1.0000
  11.500   1.5959   0.04097   0.03214  -0.0913   0.1950   1.0000
  11.750   1.6056   0.04246   0.03365  -0.0891   0.1863   1.0000
  12.000   1.6138   0.04392   0.03518  -0.0867   0.1785   1.0000
  12.250   1.6267   0.04548   0.03676  -0.0850   0.1716   1.0000
  12.500   1.6332   0.04710   0.03856  -0.0826   0.1653   1.0000
  12.750   1.6502   0.04848   0.03980  -0.0816   0.1587   1.0000
  13.000   1.6485   0.05046   0.04212  -0.0783   0.1538   1.0000
  13.250   1.6554   0.05209   0.04381  -0.0763   0.1484   1.0000
  13.500   1.6666   0.05382   0.04556  -0.0748   0.1430   1.0000
  13.750   1.6624   0.05612   0.04816  -0.0718   0.1385   1.0000
  14.000   1.6703   0.05773   0.04975  -0.0701   0.1331   1.0000
  14.250   1.6698   0.06018   0.05237  -0.0678   0.1283   1.0000
  14.500   1.6623   0.06287   0.05530  -0.0652   0.1239   1.0000
  14.750   1.6757   0.06447   0.05674  -0.0643   0.1176   1.0000
  15.000   1.6580   0.06810   0.06077  -0.0614   0.1143   1.0000
  15.250   1.6563   0.07060   0.06334  -0.0598   0.1095   1.0000
  15.500   1.6566   0.07342   0.06622  -0.0585   0.1050   1.0000
  15.750   1.6403   0.07750   0.07061  -0.0568   0.1019   1.0000
  16.000   1.6596   0.07866   0.07154  -0.0563   0.0964   1.0000
  16.250   1.6349   0.08377   0.07705  -0.0550   0.0947   1.0000
  16.500   1.6165   0.08868   0.08228  -0.0546   0.0925   1.0000
  16.750   1.6205   0.09110   0.08469  -0.0542   0.0889   1.0000
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