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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 500,000
Max Cl/Cd: 120.84 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1708-il-500000-n5.txt
Download as CSV file: xf-hs1708-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2878   0.09210   0.08970  -0.0574   0.9636   0.0080
  -9.250  -0.2815   0.08750   0.08509  -0.0607   0.9510   0.0079
  -8.750  -0.3466   0.02283   0.01875  -0.1306   0.8954   0.0068
  -8.500  -0.3197   0.02021   0.01578  -0.1326   0.8896   0.0069
  -8.250  -0.2924   0.01852   0.01381  -0.1338   0.8844   0.0070
  -8.000  -0.2647   0.01723   0.01228  -0.1346   0.8791   0.0072
  -7.750  -0.2369   0.01616   0.01097  -0.1353   0.8744   0.0074
  -7.500  -0.2087   0.01527   0.00988  -0.1359   0.8704   0.0077
  -7.250  -0.1802   0.01449   0.00893  -0.1364   0.8663   0.0080
  -7.000  -0.1517   0.01384   0.00811  -0.1368   0.8625   0.0082
  -6.750  -0.1231   0.01322   0.00732  -0.1372   0.8591   0.0086
  -6.500  -0.0944   0.01260   0.00656  -0.1376   0.8559   0.0093
  -6.250  -0.0655   0.01211   0.00595  -0.1379   0.8524   0.0100
  -6.000  -0.0367   0.01168   0.00542  -0.1382   0.8489   0.0112
  -5.750  -0.0079   0.01125   0.00492  -0.1385   0.8457   0.0138
  -5.250   0.0498   0.01061   0.00420  -0.1391   0.8403   0.0243
  -5.000   0.0787   0.01037   0.00395  -0.1394   0.8376   0.0297
  -4.750   0.1075   0.01020   0.00373  -0.1396   0.8349   0.0340
  -4.500   0.1364   0.01000   0.00352  -0.1398   0.8323   0.0382
  -4.250   0.1652   0.00988   0.00334  -0.1400   0.8298   0.0429
  -4.000   0.1941   0.00972   0.00317  -0.1402   0.8274   0.0479
  -3.750   0.2231   0.00958   0.00302  -0.1405   0.8249   0.0521
  -3.500   0.2521   0.00947   0.00287  -0.1407   0.8225   0.0560
  -3.250   0.2811   0.00933   0.00275  -0.1409   0.8199   0.0632
  -3.000   0.3099   0.00923   0.00263  -0.1411   0.8171   0.0697
  -2.750   0.3386   0.00913   0.00252  -0.1413   0.8136   0.0769
  -2.500   0.3673   0.00901   0.00241  -0.1414   0.8080   0.0840
  -2.250   0.3958   0.00892   0.00230  -0.1414   0.8022   0.0927
  -2.000   0.4244   0.00884   0.00223  -0.1415   0.7968   0.1020
  -1.750   0.4530   0.00875   0.00217  -0.1417   0.7914   0.1129
  -1.500   0.4815   0.00871   0.00210  -0.1417   0.7867   0.1237
  -1.250   0.5102   0.00866   0.00208  -0.1418   0.7820   0.1341
  -1.000   0.5388   0.00861   0.00205  -0.1419   0.7764   0.1435
  -0.750   0.5672   0.00859   0.00202  -0.1420   0.7711   0.1539
  -0.500   0.5958   0.00855   0.00202  -0.1421   0.7652   0.1640
  -0.250   0.6243   0.00852   0.00201  -0.1422   0.7600   0.1725
   0.000   0.6528   0.00852   0.00201  -0.1423   0.7555   0.1822
   0.250   0.6813   0.00849   0.00203  -0.1424   0.7497   0.1918
   0.500   0.7096   0.00847   0.00204  -0.1424   0.7434   0.2017
   0.750   0.7380   0.00846   0.00206  -0.1425   0.7361   0.2127
   1.000   0.7661   0.00846   0.00208  -0.1425   0.7278   0.2244
   1.250   0.7943   0.00844   0.00212  -0.1425   0.7187   0.2378
   1.500   0.8223   0.00843   0.00215  -0.1425   0.7090   0.2542
   1.750   0.8501   0.00843   0.00220  -0.1425   0.6955   0.2762
   2.000   0.8775   0.00838   0.00226  -0.1424   0.6749   0.3304
   2.500   0.9196   0.00761   0.00248  -0.1396   0.5900   1.0000
   2.750   0.9431   0.00807   0.00268  -0.1387   0.5456   1.0000
   3.000   0.9672   0.00848   0.00291  -0.1380   0.5099   1.0000
   3.250   0.9917   0.00887   0.00314  -0.1374   0.4767   1.0000
   3.500   1.0151   0.00933   0.00341  -0.1367   0.4358   1.0000
   3.750   1.0368   0.00994   0.00374  -0.1357   0.3832   1.0000
   4.000   1.0596   0.01045   0.00405  -0.1348   0.3482   1.0000
   4.250   1.0837   0.01084   0.00433  -0.1342   0.3242   1.0000
   4.500   1.1073   0.01126   0.00462  -0.1335   0.2988   1.0000
   4.750   1.1314   0.01162   0.00489  -0.1329   0.2777   1.0000
   5.000   1.1552   0.01200   0.00519  -0.1323   0.2565   1.0000
   5.250   1.1781   0.01244   0.00550  -0.1315   0.2304   1.0000
   5.500   1.2006   0.01291   0.00585  -0.1306   0.2038   1.0000
   5.750   1.2221   0.01346   0.00625  -0.1296   0.1748   1.0000
   6.000   1.2426   0.01408   0.00672  -0.1284   0.1439   1.0000
   6.250   1.2614   0.01484   0.00728  -0.1270   0.1076   1.0000
   6.500   1.2798   0.01561   0.00787  -0.1255   0.0774   1.0000
   6.750   1.2998   0.01622   0.00840  -0.1243   0.0627   1.0000
   7.000   1.3206   0.01673   0.00891  -0.1231   0.0547   1.0000
   7.250   1.3412   0.01723   0.00941  -0.1219   0.0491   1.0000
   7.500   1.3612   0.01775   0.00993  -0.1206   0.0444   1.0000
   7.750   1.3813   0.01822   0.01043  -0.1194   0.0410   1.0000
   8.000   1.4000   0.01877   0.01099  -0.1179   0.0378   1.0000
   8.250   1.4175   0.01938   0.01164  -0.1162   0.0349   1.0000
   8.500   1.4352   0.01987   0.01220  -0.1145   0.0337   1.0000
   8.750   1.4514   0.02041   0.01280  -0.1125   0.0323   1.0000
   9.000   1.4672   0.02101   0.01345  -0.1106   0.0306   1.0000
   9.250   1.4822   0.02169   0.01416  -0.1086   0.0289   1.0000
   9.500   1.4955   0.02251   0.01501  -0.1064   0.0270   1.0000
   9.750   1.5088   0.02332   0.01591  -0.1043   0.0259   1.0000
  10.000   1.5236   0.02404   0.01671  -0.1024   0.0252   1.0000
  10.250   1.5376   0.02483   0.01759  -0.1005   0.0244   1.0000
  10.500   1.5508   0.02568   0.01852  -0.0986   0.0235   1.0000
  10.750   1.5638   0.02657   0.01948  -0.0967   0.0225   1.0000
  11.000   1.5762   0.02752   0.02048  -0.0949   0.0214   1.0000
  11.250   1.5866   0.02864   0.02165  -0.0928   0.0202   1.0000
  11.500   1.5943   0.03000   0.02310  -0.0906   0.0190   1.0000
  11.750   1.6080   0.03089   0.02408  -0.0891   0.0183   1.0000
  12.000   1.6199   0.03194   0.02522  -0.0875   0.0174   1.0000
  12.250   1.6310   0.03306   0.02642  -0.0859   0.0164   1.0000
  12.500   1.6409   0.03431   0.02773  -0.0843   0.0155   1.0000
  12.750   1.6493   0.03572   0.02921  -0.0826   0.0147   1.0000
  13.000   1.6550   0.03739   0.03096  -0.0807   0.0140   1.0000
  13.250   1.6603   0.03914   0.03280  -0.0790   0.0134   1.0000
  13.500   1.6671   0.04077   0.03457  -0.0774   0.0130   1.0000
  13.750   1.6731   0.04253   0.03644  -0.0759   0.0124   1.0000
  14.000   1.6783   0.04437   0.03839  -0.0745   0.0118   1.0000
  14.250   1.6828   0.04631   0.04042  -0.0731   0.0112   1.0000
  14.500   1.6861   0.04844   0.04263  -0.0719   0.0105   1.0000
  14.750   1.6873   0.05086   0.04513  -0.0706   0.0099   1.0000
  15.000   1.6868   0.05355   0.04794  -0.0695   0.0094   1.0000
  15.250   1.6872   0.05621   0.05073  -0.0686   0.0090   1.0000
  15.500   1.6866   0.05911   0.05375  -0.0679   0.0085   1.0000
  15.750   1.6850   0.06223   0.05700  -0.0673   0.0080   1.0000
  16.000   1.6822   0.06563   0.06052  -0.0671   0.0075   1.0000
  16.250   1.6775   0.06943   0.06442  -0.0670   0.0071   1.0000
  16.500   1.6707   0.07366   0.06878  -0.0673   0.0067   1.0000
  16.750   1.6623   0.07832   0.07358  -0.0680   0.0064   1.0000
  17.000   1.6539   0.08316   0.07859  -0.0689   0.0062   1.0000
  17.250   1.6440   0.08838   0.08395  -0.0702   0.0060   1.0000
  17.500   1.6327   0.09394   0.08967  -0.0718   0.0058   1.0000
  17.750   1.6203   0.09983   0.09571  -0.0737   0.0056   1.0000
  18.000   1.6066   0.10608   0.10211  -0.0760   0.0055   1.0000
  18.250   1.5921   0.11264   0.10882  -0.0787   0.0053   1.0000
  18.500   1.5768   0.11943   0.11576  -0.0816   0.0052   1.0000
  18.750   1.5609   0.12645   0.12292  -0.0849   0.0051   1.0000
  19.000   1.5450   0.13362   0.13023  -0.0884   0.0050   1.0000
  19.250   1.5290   0.14096   0.13770  -0.0923   0.0049   1.0000
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