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HT05 (ht05-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HT05 (ht05-il)
Reynolds number: 100,000
Max Cl/Cd: 26.22 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht05-il-100000-n5.txt
Download as CSV file: xf-ht05-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT05                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7347   0.09634   0.09142   0.0220   1.0000   0.0252
  -8.750  -0.7373   0.09082   0.08594   0.0183   1.0000   0.0253
  -8.500  -0.7408   0.08498   0.08015   0.0137   1.0000   0.0254
  -8.250  -0.7406   0.07803   0.07318   0.0078   1.0000   0.0254
  -8.000  -0.7385   0.07003   0.06510   0.0015   1.0000   0.0254
  -7.750  -0.7366   0.06201   0.05685  -0.0033   1.0000   0.0254
  -7.500  -0.7327   0.05487   0.04934  -0.0066   1.0000   0.0255
  -7.250  -0.7257   0.04854   0.04259  -0.0084   1.0000   0.0257
  -7.000  -0.7151   0.04282   0.03635  -0.0091   1.0000   0.0258
  -6.750  -0.7010   0.03794   0.03094  -0.0093   1.0000   0.0262
  -6.500  -0.6831   0.03420   0.02675  -0.0090   1.0000   0.0269
  -6.250  -0.6626   0.03123   0.02330  -0.0086   1.0000   0.0279
  -6.000  -0.6401   0.02899   0.02069  -0.0082   1.0000   0.0299
  -5.750  -0.6164   0.02696   0.01822  -0.0076   1.0000   0.0331
  -5.500  -0.5917   0.02471   0.01546  -0.0068   1.0000   0.0350
  -5.250  -0.5673   0.02254   0.01301  -0.0061   1.0000   0.0369
  -5.000  -0.5427   0.02117   0.01156  -0.0056   1.0000   0.0403
  -4.750  -0.5172   0.02014   0.01027  -0.0050   1.0000   0.0461
  -4.500  -0.4925   0.01878   0.00884  -0.0043   1.0000   0.0505
  -4.250  -0.4672   0.01786   0.00782  -0.0037   1.0000   0.0579
  -4.000  -0.4421   0.01698   0.00694  -0.0031   1.0000   0.0688
  -3.750  -0.4168   0.01613   0.00608  -0.0025   1.0000   0.0820
  -3.500  -0.3915   0.01541   0.00541  -0.0020   1.0000   0.1055
  -3.250  -0.3660   0.01475   0.00486  -0.0015   1.0000   0.1371
  -3.000  -0.3405   0.01416   0.00443  -0.0011   1.0000   0.1808
  -2.750  -0.3151   0.01359   0.00406  -0.0006   1.0000   0.2329
  -2.500  -0.2898   0.01302   0.00375  -0.0002   1.0000   0.2972
  -2.250  -0.2647   0.01239   0.00348   0.0004   1.0000   0.3889
  -2.000  -0.2408   0.01179   0.00339   0.0014   1.0000   0.5156
  -1.750  -0.2160   0.01146   0.00319   0.0023   1.0000   0.6116
  -1.500  -0.1924   0.01078   0.00289   0.0036   1.0000   0.6761
  -1.250  -0.1224   0.01029   0.00292  -0.0040   1.0000   1.0000
  -1.000  -0.0979   0.01025   0.00278  -0.0032   1.0000   1.0000
  -0.750  -0.0734   0.01023   0.00267  -0.0024   1.0000   1.0000
  -0.500  -0.0489   0.01021   0.00259  -0.0016   1.0000   1.0000
  -0.250  -0.0244   0.01019   0.00255  -0.0008   1.0000   1.0000
   0.000   0.0001   0.01019   0.00253   0.0000   1.0000   1.0000
   0.250   0.0245   0.01019   0.00255   0.0008   1.0000   1.0000
   0.500   0.0490   0.01020   0.00259   0.0016   1.0000   1.0000
   0.750   0.0735   0.01023   0.00267   0.0024   1.0000   1.0000
   1.000   0.0980   0.01025   0.00278   0.0032   1.0000   1.0000
   1.250   0.1225   0.01029   0.00292   0.0040   1.0000   1.0000
   1.500   0.1925   0.01079   0.00289  -0.0036   0.6754   1.0000
   1.750   0.2161   0.01146   0.00319  -0.0023   0.6113   1.0000
   2.000   0.2409   0.01179   0.00339  -0.0014   0.5149   1.0000
   2.250   0.2648   0.01239   0.00348  -0.0004   0.3884   1.0000
   2.500   0.2899   0.01302   0.00375   0.0002   0.2971   1.0000
   2.750   0.3152   0.01360   0.00406   0.0006   0.2327   1.0000
   3.000   0.3407   0.01416   0.00443   0.0011   0.1806   1.0000
   3.250   0.3662   0.01475   0.00486   0.0015   0.1370   1.0000
   3.500   0.3916   0.01541   0.00541   0.0020   0.1054   1.0000
   3.750   0.4169   0.01613   0.00608   0.0025   0.0819   1.0000
   4.000   0.4422   0.01699   0.00695   0.0031   0.0687   1.0000
   4.250   0.4674   0.01785   0.00782   0.0037   0.0577   1.0000
   4.500   0.4926   0.01879   0.00884   0.0043   0.0505   1.0000
   4.750   0.5174   0.02014   0.01028   0.0050   0.0460   1.0000
   5.000   0.5429   0.02116   0.01154   0.0056   0.0402   1.0000
   5.250   0.5674   0.02257   0.01303   0.0061   0.0369   1.0000
   5.500   0.5919   0.02472   0.01548   0.0068   0.0350   1.0000
   5.750   0.6166   0.02698   0.01824   0.0076   0.0331   1.0000
   6.000   0.6403   0.02896   0.02065   0.0081   0.0299   1.0000
   6.250   0.6627   0.03122   0.02333   0.0086   0.0279   1.0000
   6.500   0.6832   0.03419   0.02672   0.0090   0.0269   1.0000
   6.750   0.7010   0.03799   0.03099   0.0092   0.0262   1.0000
   7.000   0.7149   0.04298   0.03651   0.0091   0.0258   1.0000
   7.500   0.7326   0.05510   0.04960   0.0065   0.0256   1.0000
   7.750   0.7364   0.06241   0.05728   0.0030   0.0255   1.0000
   8.000   0.7386   0.07057   0.06565  -0.0021   0.0254   1.0000
   8.250   0.7407   0.07854   0.07370  -0.0085   0.0254   1.0000
   8.500   0.7408   0.08538   0.08055  -0.0144   0.0254   1.0000
   8.750   0.7373   0.09118   0.08630  -0.0189   0.0253   1.0000
   9.000   0.7348   0.09666   0.09173  -0.0225   0.0252   1.0000
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