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HT05 (ht05-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HT05 (ht05-il)
Reynolds number: 200,000
Max Cl/Cd: 31.11 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ht05-il-200000.txt
Download as CSV file: xf-ht05-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7217   0.11398   0.11046   0.0325   1.0000   0.0461
  -9.250  -0.7253   0.10937   0.10590   0.0262   1.0000   0.0471
  -9.000  -0.7274   0.10460   0.10119   0.0211   1.0000   0.0473
  -8.750  -0.7288   0.09955   0.09617   0.0160   1.0000   0.0475
  -8.500  -0.7280   0.09362   0.09023   0.0096   1.0000   0.0475
  -8.250  -0.7329   0.08757   0.08422   0.0125   1.0000   0.0488
  -8.000  -0.7259   0.08458   0.08122   0.0138   1.0000   0.0499
  -7.750  -0.7188   0.08082   0.07746   0.0124   1.0000   0.0512
  -7.500  -0.7112   0.07616   0.07277   0.0090   1.0000   0.0529
  -7.250  -0.7022   0.07040   0.06693   0.0039   1.0000   0.0553
  -7.000  -0.6900   0.06201   0.05784  -0.0074   1.0000   0.0602
  -6.750  -0.6360   0.04390   0.04030  -0.0090   1.0000   0.0628
  -6.250  -0.6575   0.03452   0.02877  -0.0092   1.0000   0.0363
  -6.000  -0.6401   0.02956   0.02332  -0.0088   1.0000   0.0373
  -5.750  -0.6174   0.02617   0.01938  -0.0079   1.0000   0.0368
  -5.500  -0.5940   0.02304   0.01577  -0.0071   1.0000   0.0371
  -5.250  -0.5696   0.02063   0.01308  -0.0064   1.0000   0.0385
  -5.000  -0.5442   0.01922   0.01150  -0.0058   1.0000   0.0414
  -4.750  -0.5180   0.01817   0.01020  -0.0052   1.0000   0.0457
  -4.500  -0.4921   0.01654   0.00834  -0.0044   1.0000   0.0485
  -4.250  -0.4670   0.01517   0.00699  -0.0037   1.0000   0.0540
  -4.000  -0.4413   0.01425   0.00600  -0.0031   1.0000   0.0625
  -3.750  -0.4154   0.01347   0.00520  -0.0025   1.0000   0.0730
  -3.500  -0.3903   0.01255   0.00438  -0.0019   1.0000   0.0920
  -3.250  -0.3647   0.01181   0.00378  -0.0014   1.0000   0.1242
  -3.000  -0.3393   0.01113   0.00337  -0.0009   1.0000   0.1768
  -2.750  -0.3139   0.01056   0.00306  -0.0005   1.0000   0.2387
  -2.500  -0.2890   0.00995   0.00281   0.0000   1.0000   0.3173
  -2.250  -0.2656   0.00921   0.00262   0.0008   1.0000   0.4453
  -2.000  -0.2422   0.00876   0.00262   0.0019   1.0000   0.5852
  -1.750  -0.2178   0.00833   0.00233   0.0028   1.0000   0.6495
  -1.500  -0.1552   0.00750   0.00246  -0.0031   1.0000   0.9919
  -1.250  -0.1214   0.00748   0.00233  -0.0043   1.0000   1.0000
  -1.000  -0.0969   0.00744   0.00222  -0.0035   1.0000   1.0000
  -0.750  -0.0725   0.00742   0.00214  -0.0027   1.0000   1.0000
  -0.500  -0.0483   0.00740   0.00208  -0.0018   1.0000   1.0000
  -0.250  -0.0241   0.00739   0.00204  -0.0009   1.0000   1.0000
   0.000   0.0001   0.00739   0.00203   0.0000   1.0000   1.0000
   0.250   0.0242   0.00739   0.00204   0.0009   1.0000   1.0000
   0.500   0.0484   0.00740   0.00208   0.0018   1.0000   1.0000
   0.750   0.0726   0.00742   0.00214   0.0027   1.0000   1.0000
   1.000   0.0970   0.00744   0.00222   0.0035   1.0000   1.0000
   1.250   0.1215   0.00748   0.00233   0.0043   1.0000   1.0000
   1.500   0.1558   0.00750   0.00246   0.0030   0.9913   1.0000
   1.750   0.2179   0.00833   0.00233  -0.0028   0.6493   1.0000
   2.000   0.2424   0.00876   0.00262  -0.0019   0.5850   1.0000
   2.250   0.2657   0.00922   0.00262  -0.0008   0.4446   1.0000
   2.500   0.2891   0.00995   0.00281   0.0000   0.3166   1.0000
   2.750   0.3140   0.01056   0.00306   0.0005   0.2382   1.0000
   3.000   0.3394   0.01113   0.00337   0.0009   0.1765   1.0000
   3.250   0.3648   0.01181   0.00378   0.0014   0.1242   1.0000
   3.500   0.3904   0.01255   0.00438   0.0019   0.0919   1.0000
   3.750   0.4156   0.01347   0.00520   0.0025   0.0730   1.0000
   4.000   0.4414   0.01427   0.00602   0.0031   0.0624   1.0000
   4.250   0.4672   0.01516   0.00698   0.0037   0.0539   1.0000
   4.500   0.4921   0.01665   0.00845   0.0044   0.0484   1.0000
   4.750   0.5182   0.01816   0.01020   0.0052   0.0457   1.0000
   5.000   0.5443   0.01920   0.01147   0.0058   0.0414   1.0000
   5.250   0.5697   0.02063   0.01308   0.0064   0.0385   1.0000
   5.500   0.5940   0.02311   0.01585   0.0071   0.0371   1.0000
   5.750   0.6175   0.02629   0.01951   0.0079   0.0369   1.0000
   6.000   0.6400   0.02963   0.02338   0.0088   0.0372   1.0000
   6.250   0.6570   0.03485   0.02912   0.0092   0.0363   1.0000
   6.750   0.6843   0.05435   0.05025   0.0082   0.0620   1.0000
   7.000   0.6902   0.06206   0.05789   0.0073   0.0604   1.0000
   7.250   0.7025   0.07047   0.06700  -0.0040   0.0553   1.0000
   7.500   0.7115   0.07615   0.07276  -0.0090   0.0530   1.0000
   7.750   0.7192   0.08074   0.07737  -0.0123   0.0513   1.0000
   8.000   0.7265   0.08444   0.08108  -0.0135   0.0500   1.0000
   8.250   0.7334   0.08740   0.08406  -0.0119   0.0489   1.0000
   8.500   0.7283   0.09374   0.09035  -0.0098   0.0477   1.0000
   8.750   0.7291   0.09964   0.09627  -0.0163   0.0476   1.0000
   9.000   0.7278   0.10468   0.10126  -0.0215   0.0475   1.0000
   9.250   0.7255   0.10947   0.10599  -0.0267   0.0472   1.0000
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