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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 200,000
Max Cl/Cd: 63.07 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1010-il-200000.txt
Download as CSV file: xf-hq1010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4657   0.10907   0.10576  -0.0149   1.0000   0.0541
 -10.750  -0.4760   0.10350   0.10023  -0.0190   1.0000   0.0545
 -10.500  -0.4838   0.09769   0.09444  -0.0225   1.0000   0.0547
 -10.250  -0.4931   0.09120   0.08797  -0.0265   1.0000   0.0548
 -10.000  -0.4809   0.08725   0.08405  -0.0224   1.0000   0.0566
  -9.750  -0.4777   0.08339   0.08020  -0.0227   1.0000   0.0576
  -9.500  -0.4793   0.07879   0.07561  -0.0240   1.0000   0.0587
  -9.250  -0.4860   0.07337   0.07022  -0.0263   1.0000   0.0595
  -9.000  -0.4988   0.06681   0.06370  -0.0300   1.0000   0.0601
  -8.000  -0.6683   0.04381   0.03892  -0.0378   1.0000   0.0319
  -7.750  -0.6617   0.03862   0.03359  -0.0367   1.0000   0.0299
  -7.500  -0.6558   0.03422   0.02878  -0.0348   1.0000   0.0288
  -7.250  -0.6460   0.03040   0.02447  -0.0327   1.0000   0.0281
  -7.000  -0.6327   0.02732   0.02097  -0.0306   1.0000   0.0281
  -6.750  -0.6168   0.02484   0.01811  -0.0286   1.0000   0.0288
  -6.500  -0.5995   0.02296   0.01593  -0.0266   1.0000   0.0299
  -6.250  -0.5828   0.02142   0.01412  -0.0247   1.0000   0.0322
  -6.000  -0.5676   0.01990   0.01260  -0.0228   1.0000   0.0356
  -5.750  -0.5515   0.01890   0.01150  -0.0208   1.0000   0.0390
  -5.500  -0.5351   0.01797   0.01041  -0.0186   1.0000   0.0429
  -5.250  -0.5205   0.01684   0.00934  -0.0168   1.0000   0.0503
  -5.000  -0.5047   0.01593   0.00839  -0.0149   1.0000   0.0592
  -4.750  -0.4860   0.01528   0.00771  -0.0137   0.9996   0.0705
  -4.500  -0.4478   0.01452   0.00699  -0.0164   0.9947   0.0882
  -4.250  -0.4113   0.01375   0.00629  -0.0187   0.9890   0.1111
  -4.000  -0.3745   0.01271   0.00560  -0.0213   0.9838   0.1694
  -3.750  -0.3440   0.01130   0.00509  -0.0231   0.9773   0.3536
  -3.500  -0.3108   0.01056   0.00504  -0.0246   0.9714   0.5290
  -3.250  -0.2757   0.01042   0.00508  -0.0260   0.9653   0.6048
  -3.000  -0.2398   0.01040   0.00509  -0.0274   0.9591   0.6536
  -2.750  -0.1990   0.01041   0.00512  -0.0297   0.9554   0.6907
  -2.500  -0.1672   0.01043   0.00512  -0.0303   0.9474   0.7168
  -2.250  -0.1298   0.01046   0.00513  -0.0318   0.9424   0.7432
  -2.000  -0.0996   0.01049   0.00518  -0.0317   0.9346   0.7650
  -1.750  -0.0654   0.01047   0.00514  -0.0325   0.9286   0.7839
  -1.500  -0.0361   0.01044   0.00509  -0.0325   0.9202   0.7979
  -1.250  -0.0041   0.01037   0.00499  -0.0328   0.9137   0.8110
  -1.000   0.0218   0.01035   0.00496  -0.0320   0.9041   0.8254
  -0.750   0.0492   0.01030   0.00491  -0.0314   0.8967   0.8409
  -0.500   0.0737   0.01027   0.00488  -0.0302   0.8874   0.8560
  -0.250   0.0983   0.01023   0.00485  -0.0291   0.8780   0.8697
   0.000   0.1242   0.01014   0.00475  -0.0281   0.8687   0.8813
   0.250   0.1493   0.01004   0.00464  -0.0269   0.8573   0.8930
   0.500   0.1746   0.00996   0.00457  -0.0259   0.8453   0.9053
   0.750   0.2017   0.00990   0.00449  -0.0252   0.8334   0.9177
   1.000   0.2315   0.00984   0.00442  -0.0252   0.8218   0.9302
   1.250   0.2644   0.00980   0.00437  -0.0258   0.8111   0.9426
   1.500   0.2999   0.00977   0.00434  -0.0272   0.8007   0.9547
   1.750   0.3404   0.00975   0.00433  -0.0296   0.7887   0.9639
   2.000   0.3811   0.00971   0.00430  -0.0322   0.7763   0.9733
   2.250   0.4222   0.00966   0.00428  -0.0349   0.7627   0.9830
   2.500   0.4646   0.00959   0.00421  -0.0379   0.7471   0.9923
   2.750   0.5000   0.00951   0.00412  -0.0396   0.7297   1.0000
   3.000   0.5152   0.00948   0.00410  -0.0374   0.7117   1.0000
   3.250   0.5330   0.00948   0.00408  -0.0355   0.6914   1.0000
   3.500   0.5536   0.00953   0.00408  -0.0340   0.6691   1.0000
   3.750   0.5755   0.00960   0.00409  -0.0327   0.6418   1.0000
   4.000   0.5979   0.00971   0.00416  -0.0314   0.6077   1.0000
   4.250   0.6203   0.00989   0.00423  -0.0302   0.5659   1.0000
   4.500   0.6421   0.01018   0.00434  -0.0289   0.5128   1.0000
   4.750   0.6625   0.01067   0.00454  -0.0275   0.4470   1.0000
   5.000   0.6824   0.01130   0.00486  -0.0262   0.3794   1.0000
   5.250   0.7029   0.01196   0.00529  -0.0251   0.3241   1.0000
   5.500   0.7240   0.01262   0.00574  -0.0242   0.2815   1.0000
   5.750   0.7457   0.01325   0.00624  -0.0233   0.2447   1.0000
   6.000   0.7673   0.01389   0.00675  -0.0225   0.2028   1.0000
   6.250   0.7882   0.01465   0.00729  -0.0216   0.1568   1.0000
   6.500   0.8080   0.01557   0.00803  -0.0206   0.1223   1.0000
   6.750   0.8271   0.01659   0.00889  -0.0194   0.0988   1.0000
   7.000   0.8477   0.01747   0.00978  -0.0184   0.0804   1.0000
   7.250   0.8671   0.01851   0.01080  -0.0172   0.0663   1.0000
   7.500   0.8865   0.01955   0.01183  -0.0161   0.0537   1.0000
   7.750   0.9050   0.02077   0.01308  -0.0148   0.0440   1.0000
   8.000   0.9219   0.02232   0.01461  -0.0134   0.0364   1.0000
   8.250   0.9423   0.02319   0.01563  -0.0123   0.0304   1.0000
   8.500   0.9579   0.02582   0.01831  -0.0108   0.0270   1.0000
   8.750   0.9782   0.02748   0.02019  -0.0096   0.0251   1.0000
   9.000   0.9972   0.02957   0.02252  -0.0083   0.0236   1.0000
   9.250   1.0144   0.03168   0.02487  -0.0071   0.0225   1.0000
   9.500   1.0296   0.03323   0.02654  -0.0059   0.0209   1.0000
   9.750   1.0395   0.03654   0.03005  -0.0045   0.0196   1.0000
  10.000   1.0408   0.04072   0.03467  -0.0022   0.0190   1.0000
  10.250   1.0427   0.04358   0.03789   0.0001   0.0189   1.0000
  10.500   1.0381   0.04692   0.04157   0.0027   0.0188   1.0000
  10.750   1.0266   0.05008   0.04500   0.0058   0.0188   1.0000
  11.000   1.0120   0.05358   0.04874   0.0082   0.0189   1.0000
  11.250   0.9944   0.05704   0.05245   0.0097   0.0188   1.0000
  11.500   0.9110   0.05420   0.05000   0.0116   0.0193   1.0000
  11.750   0.8946   0.05872   0.05469   0.0108   0.0194   1.0000
  12.000   0.8752   0.06422   0.06037   0.0090   0.0195   1.0000
  12.250   0.8555   0.07030   0.06663   0.0063   0.0197   1.0000
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