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HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il)
Reynolds number: 100,000
Max Cl/Cd: 56.48 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3012-il-100000-n5.txt
Download as CSV file: xf-hq3012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3793   0.09371   0.08873  -0.0483   1.0000   0.0263
  -9.750  -0.3855   0.08937   0.08446  -0.0495   1.0000   0.0261
  -9.500  -0.3937   0.08497   0.08015  -0.0507   1.0000   0.0260
  -9.250  -0.4051   0.08044   0.07573  -0.0519   1.0000   0.0258
  -9.000  -0.4196   0.07620   0.07160  -0.0526   1.0000   0.0254
  -8.750  -0.4429   0.07165   0.06716  -0.0532   1.0000   0.0251
  -8.500  -0.4747   0.06865   0.06425  -0.0516   1.0000   0.0248
  -8.250  -0.4853   0.06092   0.05639  -0.0600   0.9902   0.0245
  -8.000  -0.4833   0.05306   0.04815  -0.0677   0.9790   0.0243
  -7.750  -0.4732   0.04624   0.04080  -0.0730   0.9707   0.0244
  -7.500  -0.4609   0.04102   0.03503  -0.0754   0.9616   0.0247
  -7.250  -0.4391   0.03630   0.02960  -0.0779   0.9560   0.0256
  -7.000  -0.4183   0.03286   0.02541  -0.0785   0.9485   0.0277
  -6.750  -0.3886   0.03096   0.02337  -0.0804   0.9444   0.0295
  -6.500  -0.3623   0.02915   0.02127  -0.0811   0.9386   0.0313
  -6.250  -0.3339   0.02714   0.01891  -0.0817   0.9334   0.0336
  -6.000  -0.3013   0.02521   0.01659  -0.0828   0.9299   0.0368
  -5.750  -0.2750   0.02433   0.01570  -0.0832   0.9238   0.0415
  -5.500  -0.2455   0.02326   0.01440  -0.0837   0.9187   0.0482
  -5.250  -0.2128   0.02242   0.01352  -0.0851   0.9151   0.0564
  -5.000  -0.1877   0.02164   0.01269  -0.0848   0.9085   0.0642
  -4.750  -0.1576   0.02102   0.01189  -0.0854   0.9036   0.0731
  -4.500  -0.1259   0.02012   0.01103  -0.0864   0.9001   0.0804
  -4.250  -0.1027   0.01963   0.01048  -0.0857   0.8926   0.0891
  -4.000  -0.0730   0.01902   0.00983  -0.0862   0.8879   0.0997
  -3.750  -0.0441   0.01844   0.00924  -0.0866   0.8831   0.1138
  -3.500  -0.0197   0.01791   0.00882  -0.0862   0.8762   0.1402
  -3.250   0.0096   0.01707   0.00833  -0.0870   0.8719   0.2199
  -3.000   0.0295   0.01603   0.00819  -0.0863   0.8651   0.4132
  -2.750   0.0547   0.01581   0.00830  -0.0854   0.8596   0.5412
  -2.500   0.0851   0.01577   0.00828  -0.0853   0.8559   0.5991
  -2.250   0.1066   0.01591   0.00840  -0.0838   0.8478   0.6351
  -2.000   0.1341   0.01597   0.00845  -0.0830   0.8431   0.6722
  -1.750   0.1565   0.01612   0.00860  -0.0813   0.8364   0.7064
  -1.250   0.2103   0.01612   0.00852  -0.0798   0.8260   0.7482
  -1.000   0.2321   0.01618   0.00853  -0.0784   0.8176   0.7622
  -0.750   0.2624   0.01606   0.00832  -0.0786   0.8128   0.7727
  -0.500   0.2869   0.01608   0.00827  -0.0780   0.8046   0.7822
  -0.250   0.3162   0.01595   0.00809  -0.0780   0.7990   0.7903
   0.000   0.3417   0.01595   0.00804  -0.0775   0.7914   0.7998
   0.250   0.3703   0.01587   0.00791  -0.0774   0.7852   0.8095
   0.500   0.3964   0.01584   0.00787  -0.0769   0.7780   0.8191
   0.750   0.4240   0.01577   0.00778  -0.0767   0.7711   0.8297
   1.000   0.4507   0.01574   0.00774  -0.0764   0.7640   0.8415
   1.250   0.4779   0.01563   0.00764  -0.0759   0.7560   0.8534
   1.500   0.5034   0.01553   0.00756  -0.0752   0.7457   0.8670
   1.750   0.5324   0.01534   0.00737  -0.0750   0.7364   0.8825
   2.000   0.5616   0.01522   0.00729  -0.0749   0.7262   0.9015
   2.250   0.5951   0.01516   0.00730  -0.0760   0.7159   0.9266
   2.500   0.6355   0.01506   0.00722  -0.0785   0.7060   0.9744
   2.750   0.6656   0.01506   0.00718  -0.0790   0.6956   1.0000
   3.000   0.6916   0.01515   0.00725  -0.0788   0.6832   1.0000
   3.250   0.7181   0.01522   0.00729  -0.0786   0.6700   1.0000
   3.500   0.7445   0.01528   0.00735  -0.0783   0.6556   1.0000
   3.750   0.7707   0.01535   0.00739  -0.0779   0.6398   1.0000
   4.000   0.7967   0.01543   0.00745  -0.0774   0.6234   1.0000
   4.250   0.8218   0.01556   0.00756  -0.0769   0.6058   1.0000
   4.500   0.8461   0.01571   0.00773  -0.0762   0.5862   1.0000
   4.750   0.8707   0.01587   0.00785  -0.0755   0.5655   1.0000
   5.000   0.8943   0.01608   0.00803  -0.0746   0.5419   1.0000
   5.250   0.9176   0.01632   0.00823  -0.0737   0.5165   1.0000
   5.500   0.9399   0.01664   0.00844  -0.0727   0.4886   1.0000
   5.750   0.9613   0.01703   0.00873  -0.0715   0.4602   1.0000
   6.000   0.9817   0.01749   0.00907  -0.0703   0.4316   1.0000
   6.250   1.0014   0.01802   0.00952  -0.0690   0.4042   1.0000
   6.500   1.0206   0.01858   0.01000  -0.0677   0.3779   1.0000
   6.750   1.0392   0.01918   0.01052  -0.0663   0.3530   1.0000
   7.000   1.0571   0.01983   0.01108  -0.0648   0.3305   1.0000
   7.250   1.0749   0.02048   0.01169  -0.0634   0.3092   1.0000
   7.500   1.0920   0.02118   0.01236  -0.0619   0.2903   1.0000
   7.750   1.1085   0.02191   0.01304  -0.0604   0.2728   1.0000
   8.000   1.1248   0.02264   0.01375  -0.0588   0.2563   1.0000
   8.250   1.1406   0.02337   0.01450  -0.0573   0.2404   1.0000
   8.500   1.1546   0.02411   0.01525  -0.0554   0.2252   1.0000
   8.750   1.1679   0.02490   0.01607  -0.0535   0.2111   1.0000
   9.000   1.1806   0.02573   0.01692  -0.0516   0.1977   1.0000
   9.250   1.1925   0.02662   0.01782  -0.0497   0.1850   1.0000
   9.500   1.2041   0.02756   0.01878  -0.0478   0.1726   1.0000
   9.750   1.2161   0.02852   0.01982  -0.0461   0.1609   1.0000
  10.000   1.2272   0.02955   0.02092  -0.0444   0.1497   1.0000
  10.250   1.2374   0.03068   0.02210  -0.0426   0.1396   1.0000
  10.500   1.2455   0.03194   0.02342  -0.0409   0.1301   1.0000
  10.750   1.2549   0.03319   0.02478  -0.0393   0.1194   1.0000
  11.000   1.2631   0.03456   0.02623  -0.0377   0.1094   1.0000
  11.250   1.2693   0.03610   0.02781  -0.0362   0.1005   1.0000
  11.500   1.2742   0.03778   0.02953  -0.0348   0.0920   1.0000
  11.750   1.2808   0.03944   0.03131  -0.0335   0.0836   1.0000
  12.000   1.2838   0.04141   0.03329  -0.0323   0.0772   1.0000
  12.250   1.2889   0.04331   0.03534  -0.0313   0.0704   1.0000
  12.500   1.2897   0.04562   0.03768  -0.0303   0.0656   1.0000
  12.750   1.2938   0.04776   0.04001  -0.0295   0.0606   1.0000
  13.000   1.2936   0.05034   0.04272  -0.0288   0.0567   1.0000
  13.250   1.2927   0.05311   0.04560  -0.0283   0.0532   1.0000
  13.500   1.2932   0.05585   0.04853  -0.0281   0.0487   1.0000
  13.750   1.2883   0.05925   0.05202  -0.0282   0.0453   1.0000
  14.000   1.2852   0.06266   0.05558  -0.0285   0.0415   1.0000
  14.250   1.2807   0.06640   0.05949  -0.0291   0.0375   1.0000
  14.500   1.2710   0.07100   0.06418  -0.0303   0.0351   1.0000
  14.750   1.2638   0.07552   0.06888  -0.0315   0.0325   1.0000
  15.000   1.2553   0.08046   0.07403  -0.0331   0.0303   1.0000
  15.250   1.2437   0.08614   0.07988  -0.0353   0.0286   1.0000
  15.500   1.2305   0.09234   0.08624  -0.0381   0.0274   1.0000
  15.750   1.2157   0.09912   0.09315  -0.0413   0.0266   1.0000
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