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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 200,000
Max Cl/Cd: 97.27 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1708-il-200000.txt
Download as CSV file: xf-hs1708-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-708 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3325   0.11462   0.11118  -0.0322   1.0000   0.0398
  -9.250  -0.3470   0.11411   0.11074  -0.0284   1.0000   0.0403
  -9.000  -0.3598   0.11331   0.11000  -0.0254   1.0000   0.0409
  -8.750  -0.3567   0.11070   0.10742  -0.0282   0.9979   0.0424
  -8.500  -0.3503   0.10799   0.10472  -0.0365   0.9930   0.0433
  -8.250  -0.3413   0.10465   0.10140  -0.0426   0.9875   0.0436
  -8.000  -0.3236   0.10019   0.09693  -0.0497   0.9829   0.0437
  -7.750  -0.3165   0.09432   0.09108  -0.0499   0.9797   0.0444
  -7.500  -0.3006   0.09077   0.08752  -0.0493   0.9775   0.0453
  -7.250  -0.2811   0.08720   0.08395  -0.0521   0.9748   0.0465
  -7.000  -0.2590   0.08337   0.08010  -0.0572   0.9724   0.0481
  -6.750  -0.2498   0.08039   0.07712  -0.0598   0.9658   0.0497
  -6.500  -0.2240   0.07571   0.07240  -0.0691   0.9615   0.0529
  -6.250  -0.1773   0.06860   0.06513  -0.0891   0.9562   0.0549
  -6.000  -0.1657   0.06280   0.05932  -0.0922   0.9511   0.0558
  -5.750  -0.1105   0.03406   0.02953  -0.1193   0.9486   0.0340
  -5.500  -0.0692   0.02624   0.02082  -0.1272   0.9477   0.0364
  -5.250  -0.0304   0.02375   0.01773  -0.1304   0.9466   0.0425
  -5.000   0.0065   0.02273   0.01653  -0.1328   0.9454   0.0509
  -4.750   0.0382   0.02172   0.01522  -0.1342   0.9431   0.0587
  -4.500   0.0573   0.02233   0.01578  -0.1327   0.9379   0.0665
  -4.250   0.0889   0.02186   0.01530  -0.1340   0.9356   0.0742
  -4.000   0.1256   0.02105   0.01405  -0.1358   0.9339   0.0807
  -3.750   0.1617   0.01997   0.01292  -0.1379   0.9328   0.0871
  -3.500   0.1993   0.01938   0.01205  -0.1399   0.9316   0.0941
  -3.250   0.2371   0.01879   0.01147  -0.1422   0.9306   0.1028
  -3.000   0.2536   0.01880   0.01130  -0.1400   0.9242   0.1085
  -2.750   0.2895   0.01834   0.01088  -0.1417   0.9214   0.1184
  -2.500   0.3292   0.01783   0.01035  -0.1441   0.9194   0.1293
  -2.250   0.3677   0.01740   0.00989  -0.1461   0.9176   0.1419
  -2.000   0.4054   0.01709   0.00957  -0.1480   0.9160   0.1564
  -1.750   0.4228   0.01732   0.00977  -0.1461   0.9092   0.1676
  -1.500   0.4562   0.01711   0.00958  -0.1472   0.9061   0.1831
  -1.250   0.4941   0.01670   0.00921  -0.1489   0.9034   0.2004
  -1.000   0.5259   0.01641   0.00895  -0.1495   0.8985   0.2156
  -0.750   0.5552   0.01615   0.00873  -0.1495   0.8922   0.2313
  -0.500   0.5910   0.01566   0.00828  -0.1506   0.8885   0.2487
  -0.250   0.6182   0.01547   0.00815  -0.1502   0.8818   0.2649
   0.000   0.6486   0.01514   0.00789  -0.1503   0.8762   0.2838
   0.250   0.6814   0.01469   0.00758  -0.1509   0.8728   0.3070
   0.500   0.7057   0.01464   0.00770  -0.1503   0.8657   0.3366
   0.750   0.7271   0.01304   0.00762  -0.1484   0.8609   1.0000
   1.000   0.7585   0.01293   0.00736  -0.1485   0.8567   1.0000
   1.250   0.7830   0.01308   0.00746  -0.1477   0.8486   1.0000
   1.500   0.8139   0.01290   0.00721  -0.1477   0.8437   1.0000
   1.750   0.8389   0.01299   0.00730  -0.1469   0.8352   1.0000
   2.000   0.8693   0.01279   0.00705  -0.1467   0.8293   1.0000
   2.250   0.8944   0.01284   0.00711  -0.1459   0.8200   1.0000
   2.500   0.9241   0.01268   0.00693  -0.1456   0.8134   1.0000
   2.750   0.9496   0.01267   0.00695  -0.1448   0.8031   1.0000
   3.000   0.9760   0.01260   0.00689  -0.1440   0.7928   1.0000
   3.250   1.0036   0.01243   0.00672  -0.1434   0.7823   1.0000
   3.500   1.0313   0.01225   0.00655  -0.1427   0.7706   1.0000
   3.750   1.0569   0.01214   0.00648  -0.1418   0.7563   1.0000
   4.000   1.0820   0.01206   0.00643  -0.1408   0.7397   1.0000
   4.250   1.1064   0.01198   0.00641  -0.1396   0.7179   1.0000
   4.500   1.1304   0.01185   0.00625  -0.1382   0.6856   1.0000
   4.750   1.1526   0.01185   0.00607  -0.1364   0.6316   1.0000
   5.000   1.1716   0.01232   0.00610  -0.1341   0.5629   1.0000
   5.250   1.1887   0.01310   0.00650  -0.1319   0.5044   1.0000
   5.500   1.2066   0.01383   0.00698  -0.1300   0.4580   1.0000
   6.000   1.2435   0.01520   0.00803  -0.1267   0.3907   1.0000
   6.250   1.2622   0.01587   0.00858  -0.1251   0.3634   1.0000
   6.500   1.2808   0.01651   0.00915  -0.1235   0.3366   1.0000
   6.750   1.2990   0.01714   0.00972  -0.1218   0.3095   1.0000
   7.000   1.3164   0.01780   0.01033  -0.1201   0.2791   1.0000
   7.250   1.3306   0.01862   0.01098  -0.1178   0.2334   1.0000
   7.500   1.3354   0.02018   0.01201  -0.1142   0.1532   1.0000
   7.750   1.3384   0.02197   0.01336  -0.1104   0.1053   1.0000
   8.000   1.3456   0.02324   0.01455  -0.1070   0.0897   1.0000
   8.250   1.3515   0.02466   0.01590  -0.1035   0.0811   1.0000
   8.500   1.3631   0.02573   0.01707  -0.1010   0.0753   1.0000
   8.750   1.3703   0.02718   0.01852  -0.0980   0.0705   1.0000
   9.000   1.3801   0.02856   0.01998  -0.0954   0.0667   1.0000
   9.250   1.3922   0.02974   0.02125  -0.0932   0.0629   1.0000
   9.500   1.4030   0.03113   0.02267  -0.0910   0.0598   1.0000
   9.750   1.4154   0.03330   0.02478  -0.0890   0.0567   1.0000
  10.000   1.4309   0.03446   0.02611  -0.0872   0.0550   1.0000
  10.250   1.4459   0.03578   0.02759  -0.0856   0.0526   1.0000
  10.500   1.4598   0.03715   0.02907  -0.0838   0.0501   1.0000
  10.750   1.4743   0.03869   0.03064  -0.0823   0.0479   1.0000
  11.000   1.5072   0.04198   0.03402  -0.0832   0.0451   1.0000
  11.250   1.5159   0.04341   0.03569  -0.0807   0.0441   1.0000
  11.500   1.5240   0.04506   0.03758  -0.0784   0.0426   1.0000
  11.750   1.5313   0.04688   0.03961  -0.0761   0.0409   1.0000
  12.000   1.5386   0.04887   0.04179  -0.0740   0.0394   1.0000
  12.250   1.5429   0.05084   0.04393  -0.0718   0.0380   1.0000
  12.500   1.5499   0.05318   0.04633  -0.0701   0.0364   1.0000
  12.750   1.5487   0.05835   0.05181  -0.0680   0.0348   1.0000
  13.000   1.5392   0.06059   0.05433  -0.0649   0.0343   1.0000
  13.250   1.5291   0.06347   0.05750  -0.0623   0.0337   1.0000
  13.500   1.5175   0.06679   0.06110  -0.0601   0.0329   1.0000
  13.750   1.5045   0.07045   0.06503  -0.0583   0.0321   1.0000
  14.000   1.4906   0.07436   0.06919  -0.0570   0.0314   1.0000
  14.250   1.4765   0.07854   0.07359  -0.0562   0.0307   1.0000
  14.500   1.4633   0.08274   0.07798  -0.0559   0.0300   1.0000
  14.750   1.4495   0.08727   0.08268  -0.0560   0.0294   1.0000
  15.000   1.4364   0.09192   0.08749  -0.0567   0.0288   1.0000
  15.250   1.4167   0.09805   0.09384  -0.0584   0.0286   1.0000
  15.500   1.3951   0.10501   0.10102  -0.0611   0.0285   1.0000
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