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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 100,000
Max Cl/Cd: 58.37 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1712-il-100000-n5.txt
Download as CSV file: xf-hs1712-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3857   0.12181   0.11685  -0.0293   1.0000   0.0605
  -9.000  -0.3949   0.11902   0.11413  -0.0291   1.0000   0.0607
  -8.500  -0.4228   0.10752   0.10267  -0.0283   1.0000   0.0368
  -8.250  -0.4202   0.10439   0.09957  -0.0290   0.9981   0.0364
  -8.000  -0.4154   0.10012   0.09532  -0.0323   0.9942   0.0360
  -7.750  -0.4087   0.09458   0.08978  -0.0379   0.9891   0.0361
  -7.500  -0.3974   0.08687   0.08204  -0.0475   0.9839   0.0366
  -7.000  -0.3645   0.06816   0.06309  -0.0693   0.9733   0.0369
  -6.750  -0.3355   0.05048   0.04463  -0.0871   0.9703   0.0368
  -6.500  -0.3076   0.04516   0.03888  -0.0921   0.9660   0.0378
  -6.250  -0.2706   0.03846   0.03111  -0.0989   0.9635   0.0407
  -6.000  -0.2355   0.03617   0.02850  -0.1020   0.9609   0.0424
  -5.750  -0.1971   0.03347   0.02523  -0.1055   0.9592   0.0443
  -5.500  -0.1652   0.03198   0.02345  -0.1072   0.9555   0.0468
  -5.250  -0.1331   0.03067   0.02181  -0.1087   0.9515   0.0498
  -5.000  -0.0987   0.02970   0.02072  -0.1105   0.9485   0.0521
  -4.750  -0.0619   0.02871   0.01947  -0.1127   0.9461   0.0560
  -4.500  -0.0239   0.02789   0.01844  -0.1151   0.9442   0.0606
  -4.250   0.0018   0.02732   0.01788  -0.1150   0.9376   0.0640
  -4.000   0.0368   0.02670   0.01717  -0.1167   0.9336   0.0693
  -3.750   0.0751   0.02608   0.01647  -0.1190   0.9305   0.0756
  -3.500   0.1056   0.02565   0.01600  -0.1197   0.9242   0.0826
  -3.250   0.1388   0.02517   0.01554  -0.1210   0.9184   0.0908
  -3.000   0.1773   0.02460   0.01499  -0.1232   0.9149   0.1008
  -2.750   0.2065   0.02420   0.01463  -0.1236   0.9075   0.1131
  -2.500   0.2405   0.02375   0.01421  -0.1248   0.9015   0.1320
  -2.250   0.2789   0.02329   0.01384  -0.1270   0.8980   0.1561
  -2.000   0.3039   0.02317   0.01375  -0.1265   0.8885   0.1788
  -1.750   0.3390   0.02286   0.01344  -0.1279   0.8837   0.2049
  -1.500   0.3714   0.02256   0.01317  -0.1288   0.8777   0.2275
  -1.250   0.4009   0.02229   0.01296  -0.1291   0.8693   0.2533
  -1.000   0.4384   0.02175   0.01251  -0.1310   0.8653   0.2836
  -0.750   0.4647   0.02155   0.01242  -0.1307   0.8553   0.3192
  -0.500   0.5012   0.02081   0.01213  -0.1325   0.8506   0.4326
  -0.250   0.5140   0.01949   0.01210  -0.1279   0.8431   0.8697
   0.000   0.5441   0.01889   0.01140  -0.1278   0.8342   1.0000
   0.250   0.5748   0.01873   0.01109  -0.1281   0.8236   1.0000
   0.500   0.6143   0.01829   0.01050  -0.1300   0.8166   1.0000
   0.750   0.6440   0.01821   0.01031  -0.1301   0.8044   1.0000
   1.000   0.6805   0.01795   0.00994  -0.1316   0.7949   1.0000
   1.250   0.7252   0.01754   0.00940  -0.1347   0.7875   1.0000
   1.500   0.7573   0.01752   0.00931  -0.1354   0.7747   1.0000
   1.750   0.7697   0.01793   0.00972  -0.1323   0.7533   1.0000
   2.000   0.8113   0.01764   0.00931  -0.1348   0.7416   1.0000
   2.250   0.8541   0.01736   0.00892  -0.1375   0.7296   1.0000
   2.500   0.8959   0.01719   0.00861  -0.1401   0.7160   1.0000
   2.750   0.9335   0.01718   0.00848  -0.1420   0.7003   1.0000
   3.000   0.9638   0.01735   0.00858  -0.1424   0.6826   1.0000
   3.250   0.9921   0.01756   0.00872  -0.1423   0.6635   1.0000
   3.500   1.0188   0.01780   0.00889  -0.1420   0.6433   1.0000
   3.750   1.0440   0.01807   0.00910  -0.1414   0.6211   1.0000
   4.000   1.0677   0.01836   0.00931  -0.1404   0.5964   1.0000
   4.250   1.0910   0.01869   0.00951  -0.1394   0.5700   1.0000
   4.500   1.1119   0.01907   0.00979  -0.1379   0.5405   1.0000
   4.750   1.1316   0.01951   0.01008  -0.1362   0.5084   1.0000
   5.000   1.1503   0.02001   0.01041  -0.1343   0.4773   1.0000
   5.500   1.1868   0.02116   0.01124  -0.1307   0.4255   1.0000
   5.750   1.2049   0.02175   0.01174  -0.1289   0.4049   1.0000
   6.000   1.2233   0.02235   0.01225  -0.1272   0.3881   1.0000
   6.250   1.2416   0.02296   0.01278  -0.1256   0.3739   1.0000
   6.500   1.2594   0.02358   0.01334  -0.1238   0.3616   1.0000
   6.750   1.2777   0.02420   0.01394  -0.1222   0.3509   1.0000
   7.000   1.2959   0.02489   0.01456  -0.1206   0.3412   1.0000
   7.250   1.3144   0.02551   0.01523  -0.1191   0.3303   1.0000
   7.500   1.3325   0.02615   0.01592  -0.1175   0.3196   1.0000
   7.750   1.3496   0.02682   0.01661  -0.1157   0.3092   1.0000
   8.000   1.3671   0.02740   0.01732  -0.1141   0.2986   1.0000
   8.250   1.3832   0.02807   0.01804  -0.1122   0.2889   1.0000
   8.500   1.3987   0.02876   0.01880  -0.1103   0.2787   1.0000
   8.750   1.4141   0.02947   0.01959  -0.1084   0.2690   1.0000
   9.000   1.4279   0.03026   0.02041  -0.1063   0.2593   1.0000
   9.250   1.4426   0.03103   0.02130  -0.1044   0.2494   1.0000
   9.500   1.4544   0.03195   0.02223  -0.1021   0.2400   1.0000
   9.750   1.4678   0.03282   0.02322  -0.1001   0.2290   1.0000
  10.000   1.4789   0.03382   0.02428  -0.0978   0.2187   1.0000
  10.250   1.4883   0.03492   0.02543  -0.0954   0.2080   1.0000
  10.500   1.4987   0.03604   0.02663  -0.0932   0.1968   1.0000
  10.750   1.5066   0.03732   0.02795  -0.0908   0.1866   1.0000
  11.000   1.5138   0.03869   0.02937  -0.0884   0.1764   1.0000
  11.250   1.5217   0.04008   0.03087  -0.0862   0.1668   1.0000
  11.500   1.5261   0.04173   0.03253  -0.0838   0.1586   1.0000
  11.750   1.5330   0.04330   0.03422  -0.0817   0.1500   1.0000
  12.000   1.5364   0.04514   0.03610  -0.0794   0.1432   1.0000
  12.250   1.5414   0.04694   0.03803  -0.0774   0.1363   1.0000
  12.750   1.5471   0.05104   0.04232  -0.0735   0.1256   1.0000
  13.000   1.5486   0.05329   0.04467  -0.0717   0.1212   1.0000
  13.250   1.5489   0.05571   0.04716  -0.0700   0.1175   1.0000
  13.500   1.5520   0.05800   0.04963  -0.0686   0.1133   1.0000
  13.750   1.5524   0.06059   0.05234  -0.0673   0.1098   1.0000
  14.000   1.5506   0.06347   0.05526  -0.0661   0.1066   1.0000
  14.250   1.5515   0.06622   0.05821  -0.0652   0.1026   1.0000
  14.500   1.5497   0.06930   0.06142  -0.0644   0.0993   1.0000
  14.750   1.5462   0.07262   0.06478  -0.0638   0.0967   1.0000
  15.000   1.5451   0.07585   0.06824  -0.0634   0.0934   1.0000
  15.250   1.5417   0.07939   0.07194  -0.0632   0.0904   1.0000
  15.500   1.5368   0.08315   0.07577  -0.0632   0.0879   1.0000
  15.750   1.5323   0.08707   0.07990  -0.0634   0.0848   1.0000
  16.000   1.5264   0.09124   0.08422  -0.0639   0.0820   1.0000
  16.250   1.5200   0.09548   0.08852  -0.0646   0.0797   1.0000
  16.500   1.5137   0.09990   0.09312  -0.0655   0.0772   1.0000
  16.750   1.5077   0.10425   0.09755  -0.0666   0.0749   1.0000
  17.000   1.5041   0.10811   0.10140  -0.0675   0.0726   1.0000
  17.250   1.4954   0.11323   0.10676  -0.0693   0.0700   1.0000
  17.500   1.4913   0.11738   0.11098  -0.0706   0.0676   1.0000
  17.750   1.4833   0.12257   0.11635  -0.0728   0.0653   1.0000
  18.000   1.4732   0.12837   0.12238  -0.0756   0.0629   1.0000
  18.250   1.4692   0.13285   0.12693  -0.0778   0.0608   1.0000
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