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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 500,000
Max Cl/Cd: 103.4 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1712-il-500000.txt
Download as CSV file: xf-hs1712-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3034   0.09624   0.09388  -0.0660   0.9836   0.0293
  -9.000  -0.2870   0.09404   0.09168  -0.0673   0.9829   0.0295
  -8.750  -0.4152   0.02948   0.02542  -0.1200   0.9646   0.0212
  -8.500  -0.3855   0.02518   0.02035  -0.1234   0.9633   0.0220
  -8.250  -0.3537   0.02359   0.01855  -0.1255   0.9622   0.0228
  -8.000  -0.3199   0.02320   0.01813  -0.1272   0.9612   0.0236
  -7.750  -0.2853   0.02221   0.01695  -0.1292   0.9605   0.0246
  -7.500  -0.2498   0.02071   0.01509  -0.1314   0.9598   0.0256
  -7.250  -0.2139   0.01989   0.01423  -0.1336   0.9592   0.0264
  -7.000  -0.1769   0.01939   0.01365  -0.1358   0.9586   0.0275
  -6.750  -0.1579   0.01888   0.01301  -0.1341   0.9523   0.0286
  -6.500  -0.1241   0.01831   0.01235  -0.1355   0.9505   0.0299
  -6.250  -0.0895   0.01792   0.01191  -0.1371   0.9491   0.0313
  -6.000  -0.0539   0.01735   0.01115  -0.1388   0.9481   0.0331
  -5.750  -0.0184   0.01675   0.01058  -0.1407   0.9472   0.0347
  -5.500   0.0185   0.01634   0.01001  -0.1426   0.9465   0.0370
  -5.250   0.0556   0.01553   0.00927  -0.1450   0.9459   0.0397
  -5.000   0.0942   0.01472   0.00847  -0.1475   0.9454   0.0430
  -4.750   0.1339   0.01398   0.00774  -0.1503   0.9450   0.0468
  -4.500   0.1558   0.01372   0.00749  -0.1489   0.9387   0.0502
  -4.250   0.1899   0.01336   0.00716  -0.1503   0.9363   0.0545
  -4.000   0.2266   0.01297   0.00678  -0.1523   0.9350   0.0588
  -3.750   0.2644   0.01256   0.00638  -0.1545   0.9340   0.0633
  -3.500   0.3025   0.01218   0.00600  -0.1567   0.9328   0.0677
  -3.250   0.3418   0.01170   0.00556  -0.1592   0.9314   0.0736
  -3.000   0.3827   0.01116   0.00506  -0.1620   0.9296   0.0837
  -2.750   0.4066   0.01083   0.00482  -0.1609   0.9205   0.1013
  -2.500   0.4441   0.01031   0.00441  -0.1629   0.9156   0.1346
  -2.250   0.4725   0.01005   0.00423  -0.1629   0.9069   0.1602
  -2.000   0.5046   0.00980   0.00402  -0.1637   0.8994   0.1811
  -1.750   0.5340   0.00964   0.00389  -0.1639   0.8898   0.1968
  -1.500   0.5696   0.00940   0.00364  -0.1655   0.8809   0.2126
  -1.250   0.6002   0.00926   0.00347  -0.1660   0.8662   0.2261
  -1.000   0.6330   0.00911   0.00329  -0.1669   0.8489   0.2419
  -0.750   0.6650   0.00902   0.00315  -0.1677   0.8289   0.2610
  -0.500   0.6947   0.00897   0.00310  -0.1681   0.8066   0.2889
  -0.250   0.7246   0.00887   0.00309  -0.1687   0.7874   0.3760
   0.000   0.7518   0.00832   0.00328  -0.1690   0.7539   0.6470
   0.250   0.7712   0.00811   0.00340  -0.1667   0.7281   0.8359
   0.500   0.7803   0.00787   0.00322  -0.1618   0.7108   0.9997
   0.750   0.8073   0.00809   0.00332  -0.1616   0.6941   1.0000
   1.000   0.8344   0.00829   0.00341  -0.1614   0.6788   1.0000
   1.250   0.8611   0.00848   0.00351  -0.1612   0.6631   1.0000
   1.500   0.8873   0.00869   0.00360  -0.1608   0.6467   1.0000
   1.750   0.9132   0.00888   0.00371  -0.1604   0.6295   1.0000
   2.000   0.9387   0.00909   0.00382  -0.1599   0.6114   1.0000
   2.250   0.9637   0.00932   0.00395  -0.1593   0.5901   1.0000
   2.500   0.9876   0.00959   0.00410  -0.1585   0.5672   1.0000
   2.750   1.0112   0.00988   0.00427  -0.1576   0.5401   1.0000
   3.000   1.0319   0.01030   0.00447  -0.1561   0.4994   1.0000
   3.250   1.0517   0.01080   0.00473  -0.1545   0.4565   1.0000
   3.500   1.0721   0.01131   0.00503  -0.1531   0.4179   1.0000
   3.750   1.0933   0.01178   0.00532  -0.1518   0.3856   1.0000
   4.000   1.1154   0.01220   0.00559  -0.1508   0.3651   1.0000
   4.250   1.1381   0.01257   0.00587  -0.1498   0.3534   1.0000
   4.500   1.1605   0.01295   0.00618  -0.1488   0.3444   1.0000
   4.750   1.1847   0.01321   0.00644  -0.1482   0.3368   1.0000
   5.000   1.2074   0.01355   0.00674  -0.1472   0.3283   1.0000
   5.250   1.2314   0.01379   0.00699  -0.1465   0.3200   1.0000
   5.500   1.2540   0.01409   0.00726  -0.1456   0.3102   1.0000
   5.750   1.2768   0.01433   0.00750  -0.1446   0.3001   1.0000
   6.000   1.2977   0.01465   0.00779  -0.1433   0.2897   1.0000
   6.250   1.3190   0.01497   0.00809  -0.1421   0.2791   1.0000
   6.500   1.3399   0.01532   0.00841  -0.1408   0.2695   1.0000
   6.750   1.3597   0.01573   0.00878  -0.1394   0.2587   1.0000
   7.000   1.3805   0.01608   0.00914  -0.1381   0.2483   1.0000
   7.250   1.4000   0.01652   0.00954  -0.1367   0.2381   1.0000
   7.500   1.4197   0.01695   0.00995  -0.1353   0.2271   1.0000
   7.750   1.4388   0.01741   0.01039  -0.1337   0.2161   1.0000
   8.000   1.4569   0.01794   0.01088  -0.1321   0.2043   1.0000
   8.250   1.4744   0.01850   0.01140  -0.1304   0.1909   1.0000
   8.500   1.4915   0.01909   0.01195  -0.1286   0.1773   1.0000
   8.750   1.5075   0.01975   0.01256  -0.1267   0.1631   1.0000
   9.000   1.5226   0.02048   0.01323  -0.1246   0.1482   1.0000
   9.250   1.5363   0.02130   0.01397  -0.1224   0.1330   1.0000
   9.500   1.5500   0.02213   0.01475  -0.1202   0.1199   1.0000
   9.750   1.5638   0.02296   0.01554  -0.1180   0.1092   1.0000
  10.000   1.5773   0.02379   0.01636  -0.1159   0.1017   1.0000
  10.250   1.5904   0.02467   0.01723  -0.1137   0.0961   1.0000
  10.500   1.6050   0.02545   0.01805  -0.1118   0.0920   1.0000
  10.750   1.6178   0.02636   0.01898  -0.1097   0.0887   1.0000
  11.000   1.6316   0.02720   0.01987  -0.1078   0.0858   1.0000
  11.250   1.6444   0.02811   0.02081  -0.1058   0.0828   1.0000
  11.500   1.6557   0.02914   0.02187  -0.1037   0.0803   1.0000
  11.750   1.6667   0.03021   0.02299  -0.1016   0.0784   1.0000
  12.000   1.6765   0.03138   0.02421  -0.0994   0.0767   1.0000
  12.250   1.6841   0.03274   0.02561  -0.0971   0.0751   1.0000
  12.500   1.6885   0.03436   0.02726  -0.0944   0.0733   1.0000
  12.750   1.6991   0.03555   0.02856  -0.0926   0.0718   1.0000
  13.000   1.7080   0.03691   0.03001  -0.0908   0.0698   1.0000
  13.250   1.7122   0.03870   0.03187  -0.0885   0.0679   1.0000
  13.500   1.7183   0.04040   0.03365  -0.0866   0.0661   1.0000
  13.750   1.7327   0.04141   0.03477  -0.0856   0.0634   1.0000
  14.000   1.7417   0.04292   0.03635  -0.0842   0.0609   1.0000
  14.250   1.7524   0.04429   0.03782  -0.0830   0.0585   1.0000
  14.500   1.7593   0.04609   0.03963  -0.0816   0.0560   1.0000
  14.750   1.7643   0.04810   0.04173  -0.0802   0.0536   1.0000
  15.000   1.7654   0.05058   0.04427  -0.0788   0.0512   1.0000
  15.250   1.7688   0.05291   0.04671  -0.0776   0.0488   1.0000
  15.500   1.7746   0.05504   0.04894  -0.0767   0.0453   1.0000
  15.750   1.7847   0.05672   0.05072  -0.0760   0.0399   1.0000
  16.000   1.7873   0.05928   0.05326  -0.0753   0.0370   1.0000
  16.250   1.7842   0.06259   0.05661  -0.0745   0.0351   1.0000
  16.500   1.7767   0.06654   0.06064  -0.0738   0.0338   1.0000
  16.750   1.7658   0.07105   0.06524  -0.0734   0.0327   1.0000
  17.000   1.7542   0.07578   0.07008  -0.0732   0.0319   1.0000
  17.250   1.7445   0.08037   0.07482  -0.0733   0.0310   1.0000
  17.500   1.7324   0.08541   0.08001  -0.0737   0.0303   1.0000
  17.750   1.7173   0.09103   0.08576  -0.0744   0.0297   1.0000
  18.000   1.7003   0.09708   0.09194  -0.0756   0.0292   1.0000
  18.250   1.6809   0.10364   0.09863  -0.0772   0.0287   1.0000
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