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HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il)
Reynolds number: 50,000
Max Cl/Cd: 31.01 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1012-il-50000.txt
Download as CSV file: xf-hq1012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5667   0.09457   0.08777  -0.0249   1.0000   0.1851
  -9.500  -0.5489   0.08958   0.08272  -0.0242   1.0000   0.1789
  -9.250  -0.6569   0.07382   0.06710  -0.0396   1.0000   0.1411
  -9.000  -0.6606   0.06891   0.06216  -0.0398   1.0000   0.1393
  -8.750  -0.6721   0.06392   0.05706  -0.0398   1.0000   0.1370
  -8.500  -0.6858   0.05890   0.05181  -0.0393   1.0000   0.1344
  -8.250  -0.6966   0.05408   0.04662  -0.0381   1.0000   0.1325
  -8.000  -0.6960   0.05042   0.04267  -0.0365   1.0000   0.1351
  -7.750  -0.6958   0.04688   0.03868  -0.0345   1.0000   0.1385
  -7.500  -0.6941   0.04347   0.03464  -0.0321   1.0000   0.1413
  -7.250  -0.6787   0.04079   0.03205  -0.0306   1.0000   0.1485
  -7.000  -0.6712   0.03821   0.02887  -0.0281   1.0000   0.1556
  -6.750  -0.6546   0.03584   0.02654  -0.0265   1.0000   0.1640
  -6.500  -0.6410   0.03381   0.02427  -0.0245   1.0000   0.1748
  -6.250  -0.6258   0.03186   0.02193  -0.0225   1.0000   0.1853
  -6.000  -0.6093   0.03023   0.02019  -0.0207   1.0000   0.1995
  -5.750  -0.5916   0.02861   0.01864  -0.0189   1.0000   0.2162
  -5.500  -0.5733   0.02708   0.01720  -0.0172   1.0000   0.2360
  -5.250  -0.5567   0.02564   0.01590  -0.0153   1.0000   0.2654
  -5.000  -0.5407   0.02411   0.01463  -0.0131   1.0000   0.3065
  -4.750  -0.5286   0.02261   0.01373  -0.0104   1.0000   0.3765
  -4.500  -0.5206   0.02166   0.01374  -0.0058   1.0000   0.4861
  -4.250  -0.5146   0.02206   0.01462   0.0004   1.0000   0.5863
  -4.000  -0.5080   0.02289   0.01555   0.0069   1.0000   0.6524
  -3.750  -0.5011   0.02358   0.01620   0.0130   1.0000   0.7034
  -3.500  -0.4936   0.02420   0.01675   0.0193   1.0000   0.7460
  -3.250  -0.4841   0.02469   0.01717   0.0253   1.0000   0.7851
  -3.000  -0.4716   0.02500   0.01736   0.0304   1.0000   0.8249
  -2.750  -0.4448   0.02543   0.01761   0.0331   1.0000   0.8665
  -2.500  -0.3559   0.02648   0.01819   0.0251   1.0000   0.9081
  -2.250  -0.2460   0.02683   0.01802   0.0107   1.0000   0.9391
  -2.000  -0.1510   0.02654   0.01739  -0.0025   1.0000   0.9662
  -1.750  -0.0460   0.02581   0.01633  -0.0183   1.0000   0.9956
  -1.500  -0.0357   0.02559   0.01605  -0.0183   1.0000   1.0000
  -1.250  -0.0439   0.02548   0.01592  -0.0150   1.0000   1.0000
  -1.000  -0.0520   0.02533   0.01575  -0.0116   1.0000   1.0000
  -0.750  -0.0604   0.02514   0.01552  -0.0083   1.0000   1.0000
  -0.500  -0.0693   0.02490   0.01526  -0.0048   1.0000   1.0000
  -0.250  -0.0789   0.02460   0.01493  -0.0012   1.0000   1.0000
   0.000  -0.0892   0.02423   0.01454   0.0025   1.0000   1.0000
   0.250  -0.0976   0.02387   0.01413   0.0060   1.0000   1.0000
   0.500  -0.0991   0.02367   0.01385   0.0086   1.0000   1.0000
   0.750  -0.0913   0.02375   0.01383   0.0097   1.0000   1.0000
   1.000  -0.0782   0.02404   0.01402   0.0102   1.0000   1.0000
   1.250  -0.0352   0.02509   0.01499   0.0051   0.9886   1.0000
   1.500   0.0089   0.02621   0.01605   0.0001   0.9755   1.0000
   1.750   0.0516   0.02730   0.01710  -0.0045   0.9613   1.0000
   2.000   0.0977   0.02840   0.01819  -0.0094   0.9444   1.0000
   2.250   0.1510   0.02950   0.01931  -0.0151   0.9234   1.0000
   2.500   0.1981   0.03031   0.02017  -0.0193   0.9006   1.0000
   2.750   0.2497   0.03112   0.02106  -0.0239   0.8801   1.0000
   3.000   0.2845   0.03176   0.02178  -0.0257   0.8591   1.0000
   3.250   0.3350   0.03232   0.02247  -0.0295   0.8385   1.0000
   3.500   0.3712   0.03283   0.02308  -0.0310   0.8166   1.0000
   3.750   0.4241   0.03297   0.02344  -0.0343   0.7942   1.0000
   4.000   0.4641   0.03311   0.02374  -0.0356   0.7699   1.0000
   4.250   0.5275   0.03232   0.02323  -0.0386   0.7476   1.0000
   4.500   0.5610   0.03202   0.02309  -0.0377   0.7206   1.0000
   4.750   0.5994   0.03127   0.02253  -0.0367   0.6930   1.0000
   5.000   0.6386   0.03019   0.02164  -0.0353   0.6643   1.0000
   5.250   0.6763   0.02891   0.02049  -0.0333   0.6334   1.0000
   5.500   0.7127   0.02757   0.01923  -0.0311   0.6007   1.0000
   5.750   0.7395   0.02691   0.01858  -0.0285   0.5641   1.0000
   6.000   0.7691   0.02617   0.01772  -0.0261   0.5268   1.0000
   6.250   0.7913   0.02617   0.01762  -0.0236   0.4871   1.0000
   6.500   0.8138   0.02640   0.01769  -0.0214   0.4473   1.0000
   6.750   0.8360   0.02696   0.01798  -0.0193   0.4074   1.0000
   7.000   0.8544   0.02799   0.01886  -0.0173   0.3681   1.0000
   7.250   0.8741   0.02926   0.01992  -0.0155   0.3313   1.0000
   7.500   0.8933   0.03081   0.02135  -0.0139   0.2980   1.0000
   7.750   0.9131   0.03259   0.02307  -0.0126   0.2691   1.0000
   8.000   0.9344   0.03453   0.02489  -0.0115   0.2446   1.0000
   8.250   0.9509   0.03656   0.02709  -0.0099   0.2241   1.0000
   8.500   0.9694   0.03863   0.02924  -0.0086   0.2067   1.0000
   8.750   0.9861   0.04093   0.03170  -0.0073   0.1921   1.0000
   9.000   0.9998   0.04327   0.03426  -0.0056   0.1788   1.0000
   9.250   1.0107   0.04618   0.03749  -0.0039   0.1690   1.0000
   9.500   1.0247   0.04863   0.04002  -0.0026   0.1580   1.0000
   9.750   1.0250   0.05201   0.04387  -0.0002   0.1513   1.0000
  10.000   1.0323   0.05517   0.04717   0.0013   0.1437   1.0000
  10.250   1.0190   0.05921   0.05166   0.0039   0.1405   1.0000
  10.500   1.0068   0.06321   0.05596   0.0060   0.1376   1.0000
  10.750   0.9986   0.06716   0.06008   0.0076   0.1352   1.0000
  11.000   0.9826   0.07132   0.06438   0.0093   0.1341   1.0000
  11.250   0.9657   0.07588   0.06904   0.0102   0.1332   1.0000
  11.500   0.9490   0.08107   0.07431   0.0101   0.1325   1.0000
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