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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 200,000
Max Cl/Cd: 92.76 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1708-il-200000-n5.txt
Download as CSV file: xf-hs1708-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3267   0.11824   0.11454  -0.0395   1.0000   0.0194
 -10.250  -0.3234   0.11595   0.11228  -0.0386   1.0000   0.0186
 -10.000  -0.3248   0.11356   0.10995  -0.0377   1.0000   0.0178
  -9.500  -0.3173   0.10261   0.09903  -0.0452   0.9933   0.0149
  -9.250  -0.3048   0.09867   0.09509  -0.0486   0.9887   0.0148
  -9.000  -0.2915   0.09448   0.09089  -0.0526   0.9849   0.0147
  -8.750  -0.2810   0.09033   0.08673  -0.0562   0.9778   0.0146
  -8.500  -0.2688   0.08581   0.08222  -0.0608   0.9723   0.0145
  -8.250  -0.2608   0.08157   0.07799  -0.0644   0.9627   0.0145
  -8.000  -0.2500   0.07674   0.07315  -0.0695   0.9549   0.0145
  -7.750  -0.2369   0.07105   0.06745  -0.0764   0.9470   0.0145
  -7.250  -0.1870   0.02405   0.01862  -0.1339   0.9269   0.0148
  -7.000  -0.1576   0.02192   0.01615  -0.1359   0.9224   0.0159
  -6.750  -0.1273   0.02061   0.01460  -0.1373   0.9190   0.0175
  -6.500  -0.0959   0.01898   0.01255  -0.1388   0.9164   0.0195
  -6.250  -0.0670   0.01788   0.01126  -0.1396   0.9124   0.0218
  -6.000  -0.0378   0.01698   0.01012  -0.1402   0.9085   0.0257
  -5.750  -0.0082   0.01642   0.00946  -0.1409   0.9052   0.0304
  -5.500   0.0219   0.01583   0.00869  -0.1415   0.9024   0.0353
  -5.250   0.0506   0.01561   0.00836  -0.1418   0.8987   0.0407
  -5.000   0.0789   0.01540   0.00808  -0.1420   0.8949   0.0470
  -4.750   0.1078   0.01522   0.00778  -0.1423   0.8917   0.0530
  -4.500   0.1371   0.01480   0.00726  -0.1427   0.8890   0.0580
  -4.000   0.1947   0.01417   0.00639  -0.1431   0.8826   0.0671
  -3.750   0.2231   0.01386   0.00608  -0.1434   0.8792   0.0728
  -3.500   0.2520   0.01363   0.00577  -0.1436   0.8764   0.0788
  -3.250   0.2811   0.01338   0.00549  -0.1439   0.8739   0.0854
  -3.000   0.3102   0.01322   0.00526  -0.1441   0.8714   0.0933
  -2.750   0.3380   0.01307   0.00514  -0.1442   0.8677   0.1008
  -2.500   0.3664   0.01296   0.00502  -0.1443   0.8645   0.1107
  -2.250   0.3951   0.01287   0.00490  -0.1444   0.8615   0.1217
  -2.000   0.4241   0.01275   0.00479  -0.1446   0.8585   0.1322
  -1.750   0.4516   0.01269   0.00475  -0.1445   0.8534   0.1437
  -1.500   0.4793   0.01262   0.00467  -0.1443   0.8476   0.1560
  -1.250   0.5081   0.01252   0.00452  -0.1442   0.8428   0.1676
  -1.000   0.5349   0.01248   0.00451  -0.1440   0.8360   0.1792
  -0.750   0.5632   0.01238   0.00441  -0.1438   0.8302   0.1908
  -0.500   0.5906   0.01233   0.00438  -0.1437   0.8240   0.2020
  -0.250   0.6184   0.01226   0.00433  -0.1435   0.8176   0.2141
   0.000   0.6461   0.01219   0.00428  -0.1433   0.8111   0.2271
   0.250   0.6735   0.01213   0.00426  -0.1431   0.8040   0.2405
   0.500   0.7017   0.01205   0.00423  -0.1431   0.7988   0.2560
   0.750   0.7289   0.01200   0.00429  -0.1429   0.7923   0.2751
   1.000   0.7570   0.01189   0.00428  -0.1429   0.7866   0.3044
   1.250   0.7831   0.01129   0.00444  -0.1428   0.7799   0.5659
   1.750   0.8306   0.01059   0.00440  -0.1403   0.7647   1.0000
   2.000   0.8583   0.01063   0.00439  -0.1400   0.7564   1.0000
   2.250   0.8849   0.01070   0.00447  -0.1396   0.7457   1.0000
   2.500   0.9118   0.01077   0.00453  -0.1393   0.7350   1.0000
   2.750   0.9386   0.01083   0.00460  -0.1389   0.7229   1.0000
   3.000   0.9650   0.01089   0.00466  -0.1384   0.7074   1.0000
   3.250   0.9909   0.01096   0.00470  -0.1378   0.6866   1.0000
   3.500   1.0164   0.01104   0.00474  -0.1371   0.6571   1.0000
   3.750   1.0408   0.01122   0.00473  -0.1361   0.6159   1.0000
   4.000   1.0632   0.01158   0.00483  -0.1347   0.5704   1.0000
   4.250   1.0846   0.01209   0.00512  -0.1334   0.5290   1.0000
   4.500   1.1043   0.01272   0.00549  -0.1318   0.4823   1.0000
   4.750   1.1227   0.01344   0.00593  -0.1300   0.4315   1.0000
   5.000   1.1407   0.01417   0.00642  -0.1283   0.3870   1.0000
   5.250   1.1595   0.01485   0.00690  -0.1268   0.3522   1.0000
   5.500   1.1794   0.01546   0.00738  -0.1255   0.3245   1.0000
   5.750   1.1998   0.01602   0.00786  -0.1242   0.3017   1.0000
   6.000   1.2208   0.01653   0.00834  -0.1231   0.2794   1.0000
   6.250   1.2409   0.01708   0.00883  -0.1218   0.2555   1.0000
   6.500   1.2595   0.01773   0.00936  -0.1203   0.2243   1.0000
   6.750   1.2760   0.01854   0.00998  -0.1186   0.1868   1.0000
   7.000   1.2907   0.01950   0.01072  -0.1166   0.1463   1.0000
   7.250   1.3039   0.02057   0.01158  -0.1144   0.1076   1.0000
   7.500   1.3174   0.02160   0.01247  -0.1122   0.0834   1.0000
   7.750   1.3310   0.02253   0.01335  -0.1099   0.0706   1.0000
   8.000   1.3445   0.02335   0.01420  -0.1076   0.0629   1.0000
   8.250   1.3561   0.02435   0.01519  -0.1051   0.0569   1.0000
   8.500   1.3705   0.02515   0.01612  -0.1031   0.0533   1.0000
   8.750   1.3834   0.02607   0.01713  -0.1009   0.0500   1.0000
   9.000   1.3941   0.02718   0.01828  -0.0985   0.0470   1.0000
   9.250   1.4040   0.02836   0.01954  -0.0961   0.0445   1.0000
   9.500   1.4165   0.02936   0.02066  -0.0941   0.0423   1.0000
   9.750   1.4277   0.03048   0.02189  -0.0920   0.0402   1.0000
  10.000   1.4376   0.03172   0.02323  -0.0899   0.0385   1.0000
  10.250   1.4456   0.03315   0.02475  -0.0877   0.0370   1.0000
  10.500   1.4502   0.03492   0.02659  -0.0852   0.0355   1.0000
  10.750   1.4580   0.03647   0.02826  -0.0831   0.0344   1.0000
  11.000   1.4676   0.03787   0.02981  -0.0812   0.0332   1.0000
  11.250   1.4763   0.03937   0.03145  -0.0794   0.0318   1.0000
  11.500   1.4839   0.04099   0.03319  -0.0776   0.0305   1.0000
  11.750   1.4904   0.04274   0.03506  -0.0758   0.0295   1.0000
  12.000   1.4961   0.04459   0.03702  -0.0741   0.0285   1.0000
  12.250   1.5002   0.04662   0.03915  -0.0724   0.0276   1.0000
  12.500   1.5014   0.04905   0.04168  -0.0705   0.0266   1.0000
  12.750   1.5051   0.05127   0.04406  -0.0689   0.0258   1.0000
  13.000   1.5097   0.05339   0.04637  -0.0675   0.0249   1.0000
  13.250   1.5126   0.05569   0.04887  -0.0662   0.0240   1.0000
  13.500   1.5143   0.05818   0.05153  -0.0649   0.0231   1.0000
  13.750   1.5149   0.06079   0.05430  -0.0639   0.0222   1.0000
  14.000   1.5147   0.06354   0.05719  -0.0632   0.0214   1.0000
  14.250   1.5133   0.06650   0.06028  -0.0626   0.0207   1.0000
  14.500   1.5101   0.06982   0.06371  -0.0623   0.0200   1.0000
  14.750   1.5042   0.07364   0.06764  -0.0620   0.0194   1.0000
  15.000   1.4988   0.07760   0.07179  -0.0620   0.0188   1.0000
  15.250   1.4936   0.08172   0.07616  -0.0625   0.0183   1.0000
  15.500   1.4871   0.08619   0.08088  -0.0632   0.0177   1.0000
  15.750   1.4797   0.09098   0.08588  -0.0644   0.0171   1.0000
  16.000   1.4716   0.09607   0.09117  -0.0660   0.0165   1.0000
  16.250   1.4628   0.10145   0.09673  -0.0680   0.0160   1.0000
  16.500   1.4534   0.10710   0.10256  -0.0704   0.0156   1.0000
  16.750   1.4435   0.11301   0.10863  -0.0731   0.0153   1.0000
  17.000   1.4333   0.11914   0.11491  -0.0762   0.0149   1.0000
  17.250   1.4226   0.12558   0.12150  -0.0796   0.0147   1.0000
  17.500   1.4117   0.13223   0.12828  -0.0834   0.0144   1.0000
  17.750   1.3998   0.13926   0.13545  -0.0875   0.0142   1.0000
  18.000   1.3869   0.14665   0.14299  -0.0920   0.0140   1.0000
  18.250   1.3730   0.15451   0.15098  -0.0969   0.0138   1.0000
  18.500   1.3577   0.16309   0.15971  -0.1025   0.0137   1.0000
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