Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.56 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2012-il-1000000-n5.txt
Download as CSV file: xf-hq2012-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.8055   0.10273   0.10051  -0.0302   1.0000   0.0043
 -15.750  -0.9335   0.07447   0.07198  -0.0460   1.0000   0.0040
 -15.500  -1.0026   0.05651   0.05371  -0.0582   1.0000   0.0039
 -15.250  -1.0265   0.04884   0.04585  -0.0636   1.0000   0.0040
 -15.000  -1.0298   0.04502   0.04193  -0.0660   1.0000   0.0040
 -14.750  -1.0424   0.04027   0.03703  -0.0687   1.0000   0.0040
 -14.500  -1.0488   0.03671   0.03334  -0.0703   1.0000   0.0040
 -14.250  -1.0526   0.03374   0.03024  -0.0712   1.0000   0.0041
 -14.000  -1.0578   0.03098   0.02734  -0.0715   1.0000   0.0040
 -13.750  -1.0508   0.02954   0.02583  -0.0712   1.0000   0.0042
 -13.500  -1.0502   0.02782   0.02398  -0.0703   1.0000   0.0042
 -13.250  -1.0473   0.02660   0.02268  -0.0686   1.0000   0.0043
 -13.000  -1.0499   0.02534   0.02130  -0.0655   1.0000   0.0043
 -12.750  -1.0411   0.02434   0.02022  -0.0636   1.0000   0.0043
 -12.500  -1.0292   0.02350   0.01930  -0.0620   1.0000   0.0044
 -12.250  -1.0229   0.02214   0.01781  -0.0598   1.0000   0.0046
 -11.750  -0.9850   0.02007   0.01555  -0.0590   0.9919   0.0049
 -11.500  -0.9561   0.01923   0.01464  -0.0603   0.9865   0.0050
 -11.250  -0.9261   0.01838   0.01369  -0.0618   0.9806   0.0052
 -11.000  -0.8951   0.01763   0.01287  -0.0633   0.9733   0.0054
 -10.750  -0.8642   0.01690   0.01205  -0.0648   0.9639   0.0056
 -10.500  -0.8340   0.01626   0.01132  -0.0659   0.9513   0.0059
 -10.250  -0.8074   0.01566   0.01062  -0.0663   0.9341   0.0060
 -10.000  -0.7834   0.01517   0.01001  -0.0659   0.9173   0.0062
  -9.750  -0.7603   0.01473   0.00946  -0.0653   0.9038   0.0063
  -9.500  -0.7370   0.01432   0.00894  -0.0647   0.8931   0.0065
  -9.250  -0.7144   0.01378   0.00829  -0.0640   0.8834   0.0068
  -9.000  -0.6909   0.01328   0.00772  -0.0635   0.8750   0.0071
  -8.750  -0.6665   0.01291   0.00729  -0.0630   0.8676   0.0076
  -8.500  -0.6417   0.01254   0.00687  -0.0627   0.8607   0.0080
  -8.000  -0.5912   0.01187   0.00606  -0.0620   0.8481   0.0088
  -7.750  -0.5656   0.01157   0.00568  -0.0617   0.8419   0.0091
  -7.500  -0.5401   0.01121   0.00528  -0.0614   0.8363   0.0099
  -7.250  -0.5143   0.01089   0.00493  -0.0611   0.8301   0.0110
  -7.000  -0.4882   0.01063   0.00462  -0.0608   0.8244   0.0121
  -6.750  -0.4619   0.01033   0.00430  -0.0607   0.8186   0.0144
  -6.500  -0.4356   0.01007   0.00403  -0.0604   0.8124   0.0170
  -6.250  -0.4090   0.00982   0.00378  -0.0603   0.8067   0.0211
  -6.000  -0.3822   0.00960   0.00355  -0.0602   0.8004   0.0245
  -5.750  -0.3554   0.00941   0.00334  -0.0600   0.7945   0.0279
  -5.500  -0.3280   0.00925   0.00313  -0.0599   0.7882   0.0298
  -5.250  -0.3010   0.00906   0.00293  -0.0598   0.7821   0.0336
  -5.000  -0.2736   0.00889   0.00275  -0.0597   0.7761   0.0369
  -4.750  -0.2463   0.00872   0.00258  -0.0597   0.7694   0.0419
  -4.500  -0.2190   0.00856   0.00241  -0.0596   0.7635   0.0478
  -4.250  -0.1917   0.00838   0.00225  -0.0595   0.7569   0.0573
  -4.000  -0.1644   0.00822   0.00210  -0.0594   0.7507   0.0673
  -3.750  -0.1367   0.00807   0.00196  -0.0594   0.7439   0.0776
  -3.250  -0.0820   0.00775   0.00170  -0.0593   0.7293   0.1101
  -3.000  -0.0548   0.00759   0.00158  -0.0592   0.7212   0.1333
  -2.750  -0.0275   0.00738   0.00146  -0.0592   0.7130   0.1658
  -2.500  -0.0003   0.00722   0.00136  -0.0591   0.7040   0.1960
  -2.000   0.0539   0.00687   0.00117  -0.0590   0.6829   0.2707
  -1.750   0.0799   0.00650   0.00106  -0.0588   0.6739   0.3552
  -1.500   0.1065   0.00623   0.00099  -0.0587   0.6653   0.4309
  -1.250   0.1337   0.00607   0.00095  -0.0586   0.6575   0.4824
  -1.000   0.1610   0.00597   0.00094  -0.0585   0.6481   0.5240
  -0.750   0.1888   0.00593   0.00094  -0.0585   0.6379   0.5482
  -0.500   0.2167   0.00591   0.00094  -0.0585   0.6288   0.5699
   0.000   0.2722   0.00596   0.00096  -0.0583   0.6045   0.6020
   0.250   0.2998   0.00600   0.00098  -0.0583   0.5898   0.6136
   0.500   0.3277   0.00604   0.00101  -0.0582   0.5774   0.6239
   0.750   0.3554   0.00608   0.00104  -0.0582   0.5647   0.6372
   1.000   0.3829   0.00615   0.00109  -0.0581   0.5496   0.6494
   1.250   0.4102   0.00625   0.00113  -0.0579   0.5309   0.6566
   1.500   0.4375   0.00637   0.00119  -0.0578   0.5100   0.6619
   1.750   0.4644   0.00650   0.00126  -0.0576   0.4889   0.6674
   2.000   0.4911   0.00666   0.00134  -0.0574   0.4639   0.6736
   2.250   0.5174   0.00686   0.00144  -0.0572   0.4360   0.6792
   2.500   0.5437   0.00705   0.00154  -0.0569   0.4101   0.6852
   2.750   0.5697   0.00728   0.00167  -0.0566   0.3813   0.6914
   3.000   0.5952   0.00753   0.00181  -0.0563   0.3480   0.6977
   3.250   0.6200   0.00785   0.00198  -0.0558   0.3091   0.7046
   3.500   0.6451   0.00814   0.00216  -0.0554   0.2797   0.7111
   3.750   0.6711   0.00834   0.00232  -0.0551   0.2628   0.7185
   4.000   0.6971   0.00854   0.00247  -0.0548   0.2474   0.7253
   4.250   0.7226   0.00877   0.00265  -0.0545   0.2287   0.7330
   4.500   0.7486   0.00895   0.00280  -0.0542   0.2157   0.7401
   4.750   0.7748   0.00911   0.00296  -0.0540   0.2063   0.7481
   5.000   0.8006   0.00929   0.00312  -0.0537   0.1964   0.7558
   5.250   0.8263   0.00948   0.00330  -0.0533   0.1837   0.7644
   5.500   0.8516   0.00968   0.00349  -0.0530   0.1712   0.7731
   5.750   0.8767   0.00990   0.00369  -0.0525   0.1581   0.7824
   6.000   0.9003   0.01022   0.00394  -0.0519   0.1381   0.7925
   6.250   0.9220   0.01068   0.00429  -0.0510   0.1089   0.8035
   6.500   0.9432   0.01115   0.00465  -0.0500   0.0836   0.8160
   6.750   0.9661   0.01146   0.00495  -0.0492   0.0721   0.8304
   7.000   0.9880   0.01179   0.00528  -0.0483   0.0600   0.8485
   7.250   1.0091   0.01206   0.00560  -0.0471   0.0511   0.8757
   7.500   1.0421   0.01231   0.00599  -0.0486   0.0422   0.9811
   7.750   1.0651   0.01265   0.00631  -0.0479   0.0370   1.0000
   8.000   1.0876   0.01302   0.00665  -0.0471   0.0327   1.0000
   8.250   1.1105   0.01335   0.00698  -0.0464   0.0298   1.0000
   8.500   1.1329   0.01370   0.00733  -0.0457   0.0268   1.0000
   8.750   1.1542   0.01411   0.00772  -0.0448   0.0232   1.0000
   9.000   1.1756   0.01450   0.00810  -0.0439   0.0201   1.0000
   9.250   1.1952   0.01499   0.00856  -0.0427   0.0158   1.0000
   9.500   1.2142   0.01549   0.00904  -0.0414   0.0123   1.0000
   9.750   1.2279   0.01632   0.00984  -0.0394   0.0044   1.0000
  10.000   1.2440   0.01685   0.01039  -0.0376   0.0038   1.0000
  10.250   1.2586   0.01739   0.01097  -0.0356   0.0033   1.0000
  10.500   1.2737   0.01788   0.01150  -0.0337   0.0031   1.0000
  10.750   1.2883   0.01841   0.01208  -0.0318   0.0030   1.0000
  11.000   1.3022   0.01900   0.01273  -0.0299   0.0028   1.0000
  11.250   1.3159   0.01962   0.01340  -0.0281   0.0027   1.0000
  11.500   1.3288   0.02031   0.01415  -0.0262   0.0026   1.0000
  11.750   1.3413   0.02104   0.01494  -0.0245   0.0025   1.0000
  12.000   1.3526   0.02187   0.01584  -0.0227   0.0024   1.0000
  12.250   1.3636   0.02275   0.01679  -0.0209   0.0023   1.0000
  12.500   1.3740   0.02371   0.01781  -0.0193   0.0023   1.0000
  12.750   1.3835   0.02476   0.01893  -0.0176   0.0022   1.0000
  13.000   1.3914   0.02597   0.02021  -0.0160   0.0022   1.0000
  13.250   1.3974   0.02737   0.02171  -0.0143   0.0020   1.0000
  13.500   1.4043   0.02874   0.02316  -0.0129   0.0020   1.0000
  13.750   1.4087   0.03038   0.02489  -0.0115   0.0020   1.0000
  14.000   1.4110   0.03227   0.02689  -0.0101   0.0019   1.0000
  14.250   1.4145   0.03412   0.02884  -0.0091   0.0019   1.0000
  14.500   1.4187   0.03599   0.03079  -0.0082   0.0018   1.0000
  14.750   1.4225   0.03795   0.03284  -0.0075   0.0018   1.0000
  15.000   1.4236   0.04026   0.03524  -0.0069   0.0018   1.0000
  15.250   1.4243   0.04272   0.03780  -0.0065   0.0018   1.0000
  15.500   1.4238   0.04539   0.04057  -0.0064   0.0018   1.0000
  15.750   1.4225   0.04829   0.04357  -0.0065   0.0018   1.0000
  16.000   1.4158   0.05199   0.04740  -0.0069   0.0018   1.0000
  16.250   1.4138   0.05528   0.05078  -0.0075   0.0018   1.0000
  16.500   1.4097   0.05901   0.05463  -0.0084   0.0017   1.0000
  16.750   1.3989   0.06389   0.05964  -0.0099   0.0017   1.0000
  17.000   1.3933   0.06821   0.06407  -0.0115   0.0017   1.0000
  17.250   1.3813   0.07377   0.06976  -0.0138   0.0017   1.0000
  17.500   1.3632   0.08061   0.07675  -0.0169   0.0017   1.0000
  17.750   1.3468   0.08748   0.08376  -0.0202   0.0017   1.0000
  18.000   1.3301   0.09468   0.09110  -0.0239   0.0017   1.0000
  18.250   1.3057   0.10359   0.10016  -0.0286   0.0017   1.0000
  18.500   1.2852   0.11202   0.10874  -0.0331   0.0017   1.0000
<< Back to HQ 2.0/12 AIRFOIL (hq2012-il)

Polar data table (+)

Polar graphs


<< Back to HQ 2.0/12 AIRFOIL (hq2012-il)