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HT22 (ht22-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HT22 (ht22-il)
Reynolds number: 200,000
Max Cl/Cd: 46.48 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht22-il-200000-n5.txt
Download as CSV file: xf-ht22-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT22                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6668   0.10793   0.10445   0.0334   1.0001   0.0200
  -8.500  -0.6635   0.10362   0.10017   0.0311   1.0001   0.0201
  -8.000  -0.6567   0.09471   0.09131   0.0252   1.0001   0.0201
  -7.000  -0.6276   0.07850   0.07513   0.0157   1.0001   0.0235
  -6.500  -0.5968   0.06418   0.06061   0.0016   1.0001   0.0187
  -6.000  -0.5555   0.04556   0.04131  -0.0097   1.0001   0.0146
  -5.750  -0.5349   0.04010   0.03554  -0.0116   1.0001   0.0145
  -5.500  -0.5125   0.03431   0.02930  -0.0130   1.0001   0.0144
  -5.250  -0.4884   0.02863   0.02297  -0.0137   1.0001   0.0145
  -5.000  -0.4631   0.02425   0.01790  -0.0138   1.0001   0.0148
  -4.750  -0.4377   0.02244   0.01587  -0.0140   1.0001   0.0157
  -4.500  -0.4115   0.02148   0.01476  -0.0139   1.0001   0.0172
  -4.250  -0.3843   0.01941   0.01225  -0.0136   1.0001   0.0184
  -4.000  -0.3569   0.01751   0.00997  -0.0132   1.0001   0.0192
  -3.750  -0.3295   0.01615   0.00833  -0.0128   1.0001   0.0200
  -3.500  -0.3029   0.01479   0.00690  -0.0125   1.0001   0.0214
  -3.250  -0.2758   0.01422   0.00631  -0.0123   1.0001   0.0242
  -3.000  -0.2486   0.01346   0.00544  -0.0119   1.0001   0.0266
  -2.750  -0.2217   0.01253   0.00449  -0.0116   1.0001   0.0290
  -2.500  -0.1945   0.01203   0.00401  -0.0114   1.0001   0.0334
  -2.250  -0.1672   0.01148   0.00343  -0.0112   1.0001   0.0386
  -2.000  -0.1399   0.01105   0.00299  -0.0110   1.0001   0.0465
  -1.750  -0.1125   0.01062   0.00261  -0.0108   1.0001   0.0591
  -1.500  -0.0852   0.01020   0.00232  -0.0106   1.0001   0.0851
  -1.250  -0.0582   0.00966   0.00210  -0.0106   1.0001   0.1574
  -1.000  -0.0324   0.00871   0.00195  -0.0107   1.0001   0.3684
  -0.750  -0.0112   0.00749   0.00190  -0.0093   1.0001   0.6720
  -0.500   0.0221   0.00675   0.00185  -0.0092   1.0001   0.9999
  -0.250   0.0495   0.00675   0.00178  -0.0090   0.9976   0.9999
   0.000   0.0924   0.00684   0.00174  -0.0120   0.9139   0.9999
   0.250   0.1216   0.00706   0.00165  -0.0114   0.8056   0.9999
   0.500   0.1440   0.00742   0.00160  -0.0095   0.7094   0.9999
   0.750   0.1684   0.00779   0.00157  -0.0084   0.6295   0.9999
   1.000   0.1941   0.00812   0.00158  -0.0078   0.5664   0.9999
   1.250   0.2206   0.00842   0.00161  -0.0074   0.5154   0.9999
   1.500   0.2473   0.00869   0.00167  -0.0070   0.4730   0.9999
   1.750   0.2743   0.00895   0.00175  -0.0068   0.4362   0.9999
   2.000   0.3015   0.00919   0.00184  -0.0066   0.4025   0.9999
   2.250   0.3286   0.00944   0.00194  -0.0064   0.3703   0.9999
   2.500   0.3558   0.00969   0.00206  -0.0062   0.3386   0.9999
   2.750   0.3830   0.00995   0.00221  -0.0060   0.3064   0.9999
   3.000   0.4102   0.01023   0.00237  -0.0059   0.2736   0.9999
   3.250   0.4373   0.01054   0.00255  -0.0057   0.2392   0.9999
   3.500   0.4644   0.01088   0.00275  -0.0056   0.2054   0.9999
   3.750   0.4914   0.01125   0.00303  -0.0055   0.1729   0.9999
   4.000   0.5183   0.01167   0.00331  -0.0054   0.1421   0.9999
   4.250   0.5452   0.01210   0.00365  -0.0053   0.1168   0.9999
   4.500   0.5719   0.01257   0.00403  -0.0052   0.0952   0.9999
   4.750   0.5987   0.01304   0.00448  -0.0051   0.0795   0.9999
   5.000   0.6254   0.01355   0.00497  -0.0049   0.0683   0.9999
   5.250   0.6520   0.01409   0.00551  -0.0048   0.0589   0.9999
   5.500   0.6786   0.01460   0.00611  -0.0045   0.0524   0.9999
   5.750   0.7047   0.01527   0.00679  -0.0044   0.0475   0.9999
   6.000   0.7308   0.01598   0.00759  -0.0041   0.0441   0.9999
   6.250   0.7568   0.01661   0.00833  -0.0039   0.0406   0.9999
   6.500   0.7825   0.01732   0.00911  -0.0037   0.0374   0.9999
   6.750   0.8071   0.01842   0.01028  -0.0033   0.0352   0.9999
   7.000   0.8324   0.01934   0.01136  -0.0030   0.0337   0.9999
   7.250   0.8573   0.02035   0.01254  -0.0026   0.0319   0.9999
   7.500   0.8821   0.02124   0.01357  -0.0023   0.0299   0.9999
   7.750   0.9064   0.02220   0.01464  -0.0021   0.0282   0.9999
   8.000   0.9284   0.02410   0.01668  -0.0017   0.0268   0.9999
   8.250   0.9517   0.02558   0.01846  -0.0013   0.0260   0.9999
   8.500   0.9740   0.02727   0.02049  -0.0009   0.0248   0.9999
   8.750   0.9957   0.02891   0.02244  -0.0006   0.0234   0.9999
   9.000   1.0168   0.03044   0.02424  -0.0004   0.0221   0.9999
   9.250   1.0364   0.03225   0.02629  -0.0001   0.0213   0.9999
   9.500   1.0541   0.03435   0.02861   0.0001   0.0205   0.9999
  10.000   1.0731   0.04203   0.03719  -0.0002   0.0194   0.9999
  10.250   1.0725   0.04721   0.04294  -0.0013   0.0188   0.9999
  10.500   1.0604   0.05380   0.05001  -0.0043   0.0185   0.9999
  10.750   1.0369   0.06266   0.05917  -0.0132   0.0188   0.9999
  11.000   1.0062   0.07717   0.07380  -0.0278   0.0194   0.9999
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