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

HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 500,000
Max Cl/Cd: 86.26 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3514-il-500000-n5.txt
Download as CSV file: xf-hq3514-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/14 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.8091   0.06064   0.05738  -0.0824   1.0000   0.0098
 -15.000  -0.8458   0.05100   0.04752  -0.0891   1.0000   0.0096
 -14.750  -0.8679   0.04512   0.04148  -0.0926   1.0000   0.0095
 -14.500  -0.8790   0.04123   0.03745  -0.0943   1.0000   0.0097
 -14.250  -0.8887   0.03795   0.03405  -0.0952   1.0000   0.0098
 -14.000  -0.8989   0.03513   0.03111  -0.0951   1.0000   0.0100
 -13.500  -0.8888   0.03023   0.02594  -0.0984   0.9877   0.0104
 -13.250  -0.8702   0.02802   0.02361  -0.1019   0.9807   0.0107
 -13.000  -0.8470   0.02632   0.02178  -0.1050   0.9742   0.0112
 -12.750  -0.8252   0.02489   0.02022  -0.1070   0.9661   0.0117
 -12.500  -0.8005   0.02362   0.01881  -0.1088   0.9597   0.0122
 -12.250  -0.7799   0.02262   0.01766  -0.1092   0.9501   0.0128
 -12.000  -0.7603   0.02164   0.01658  -0.1093   0.9404   0.0133
 -11.750  -0.7392   0.02088   0.01575  -0.1092   0.9309   0.0140
 -11.500  -0.7204   0.02020   0.01496  -0.1085   0.9199   0.0147
 -11.250  -0.7001   0.01956   0.01420  -0.1079   0.9102   0.0154
 -11.000  -0.6792   0.01893   0.01343  -0.1073   0.9009   0.0161
 -10.750  -0.6583   0.01835   0.01279  -0.1067   0.8918   0.0169
 -10.500  -0.6355   0.01791   0.01227  -0.1063   0.8843   0.0179
 -10.250  -0.6126   0.01746   0.01172  -0.1058   0.8769   0.0190
 -10.000  -0.5894   0.01701   0.01112  -0.1054   0.8708   0.0198
  -9.750  -0.5667   0.01652   0.01059  -0.1049   0.8641   0.0208
  -9.500  -0.5427   0.01614   0.01015  -0.1046   0.8581   0.0218
  -9.250  -0.5184   0.01578   0.00970  -0.1042   0.8518   0.0229
  -9.000  -0.4939   0.01542   0.00925  -0.1038   0.8454   0.0239
  -8.750  -0.4698   0.01500   0.00874  -0.1035   0.8398   0.0250
  -8.500  -0.4449   0.01464   0.00836  -0.1032   0.8338   0.0262
  -8.250  -0.4194   0.01435   0.00802  -0.1030   0.8281   0.0275
  -8.000  -0.3937   0.01406   0.00765  -0.1028   0.8226   0.0289
  -7.750  -0.3681   0.01374   0.00726  -0.1026   0.8164   0.0301
  -7.500  -0.3429   0.01334   0.00684  -0.1023   0.8109   0.0316
  -7.250  -0.3168   0.01305   0.00651  -0.1022   0.8053   0.0330
  -7.000  -0.2906   0.01278   0.00619  -0.1020   0.7991   0.0345
  -6.750  -0.2642   0.01253   0.00585  -0.1018   0.7935   0.0359
  -6.500  -0.2381   0.01219   0.00547  -0.1017   0.7873   0.0373
  -6.250  -0.2117   0.01190   0.00516  -0.1015   0.7813   0.0393
  -6.000  -0.1849   0.01169   0.00490  -0.1014   0.7754   0.0414
  -5.750  -0.1579   0.01148   0.00464  -0.1013   0.7690   0.0435
  -5.500  -0.1310   0.01125   0.00435  -0.1012   0.7637   0.0457
  -5.250  -0.1039   0.01102   0.00411  -0.1012   0.7585   0.0486
  -5.000  -0.0765   0.01085   0.00391  -0.1011   0.7530   0.0518
  -4.750  -0.0490   0.01070   0.00370  -0.1011   0.7481   0.0545
  -4.500  -0.0216   0.01049   0.00350  -0.1011   0.7436   0.0588
  -4.250   0.0060   0.01034   0.00333  -0.1011   0.7386   0.0628
  -4.000   0.0337   0.01022   0.00316  -0.1011   0.7337   0.0670
  -3.750   0.0613   0.01006   0.00300  -0.1011   0.7289   0.0731
  -3.500   0.0892   0.00995   0.00286  -0.1012   0.7234   0.0781
  -3.250   0.1167   0.00981   0.00271  -0.1011   0.7175   0.0860
  -3.000   0.1445   0.00970   0.00259  -0.1012   0.7119   0.0942
  -2.750   0.1722   0.00954   0.00245  -0.1012   0.7059   0.1067
  -2.500   0.1989   0.00920   0.00231  -0.1012   0.7003   0.1683
  -2.250   0.2267   0.00902   0.00221  -0.1013   0.6954   0.2068
  -2.000   0.2540   0.00877   0.00210  -0.1014   0.6896   0.2510
  -1.750   0.2809   0.00846   0.00198  -0.1015   0.6840   0.3256
  -1.500   0.3074   0.00802   0.00195  -0.1016   0.6788   0.4625
  -1.250   0.3355   0.00797   0.00195  -0.1016   0.6735   0.4952
  -1.000   0.3634   0.00796   0.00194  -0.1016   0.6684   0.5137
  -0.750   0.3916   0.00795   0.00194  -0.1017   0.6628   0.5280
  -0.500   0.4195   0.00793   0.00195  -0.1016   0.6562   0.5435
  -0.250   0.4471   0.00794   0.00196  -0.1016   0.6499   0.5593
   0.000   0.4751   0.00793   0.00199  -0.1016   0.6433   0.5705
   0.250   0.5028   0.00796   0.00201  -0.1015   0.6371   0.5825
   0.500   0.5307   0.00798   0.00206  -0.1015   0.6309   0.5964
   0.750   0.5583   0.00801   0.00210  -0.1014   0.6230   0.6062
   1.000   0.5858   0.00806   0.00214  -0.1013   0.6135   0.6141
   1.250   0.6127   0.00813   0.00218  -0.1011   0.6016   0.6238
   1.500   0.6391   0.00822   0.00224  -0.1008   0.5862   0.6324
   1.750   0.6650   0.00834   0.00229  -0.1004   0.5653   0.6412
   2.000   0.6898   0.00850   0.00238  -0.0998   0.5412   0.6491
   2.250   0.7136   0.00873   0.00249  -0.0990   0.5109   0.6579
   2.750   0.7600   0.00928   0.00282  -0.0974   0.4607   0.6749
   3.000   0.7839   0.00952   0.00300  -0.0967   0.4445   0.6822
   3.500   0.8338   0.00990   0.00333  -0.0957   0.4219   0.6953
   3.750   0.8585   0.01010   0.00350  -0.0952   0.4115   0.7027
   4.000   0.8825   0.01032   0.00369  -0.0946   0.3972   0.7098
   4.250   0.9066   0.01051   0.00388  -0.0940   0.3780   0.7180
   4.500   0.9289   0.01080   0.00407  -0.0931   0.3487   0.7250
   5.250   0.9925   0.01176   0.00485  -0.0899   0.2973   0.7454
   5.500   1.0140   0.01205   0.00513  -0.0888   0.2877   0.7534
   5.750   1.0356   0.01230   0.00539  -0.0878   0.2782   0.7613
   6.000   1.0572   0.01255   0.00567  -0.0868   0.2710   0.7701
   6.250   1.0785   0.01278   0.00593  -0.0857   0.2630   0.7795
   6.500   1.0981   0.01304   0.00621  -0.0843   0.2553   0.7900
   6.750   1.1168   0.01328   0.00649  -0.0828   0.2454   0.8022
   7.000   1.1343   0.01355   0.00679  -0.0810   0.2334   0.8168
   7.500   1.1619   0.01430   0.00754  -0.0763   0.1957   0.8686
   7.750   1.1834   0.01467   0.00797  -0.0757   0.1810   1.0000
   8.000   1.1995   0.01517   0.00843  -0.0740   0.1718   1.0000
   8.250   1.2158   0.01567   0.00891  -0.0724   0.1639   1.0000
   8.500   1.2309   0.01624   0.00945  -0.0707   0.1565   1.0000
   8.750   1.2480   0.01672   0.00995  -0.0693   0.1518   1.0000
   9.000   1.2650   0.01721   0.01047  -0.0679   0.1471   1.0000
   9.250   1.2810   0.01777   0.01103  -0.0665   0.1430   1.0000
   9.500   1.2964   0.01837   0.01165  -0.0650   0.1387   1.0000
   9.750   1.3136   0.01889   0.01221  -0.0638   0.1341   1.0000
  10.000   1.3278   0.01959   0.01290  -0.0623   0.1274   1.0000
  10.250   1.3432   0.02024   0.01357  -0.0610   0.1215   1.0000
  10.500   1.3573   0.02099   0.01430  -0.0596   0.1142   1.0000
  10.750   1.3717   0.02173   0.01506  -0.0583   0.1087   1.0000
  11.000   1.3854   0.02253   0.01587  -0.0569   0.1019   1.0000
  11.250   1.3981   0.02342   0.01676  -0.0556   0.0943   1.0000
  11.500   1.4084   0.02450   0.01779  -0.0540   0.0835   1.0000
  11.750   1.4170   0.02573   0.01897  -0.0524   0.0714   1.0000
  12.250   1.4250   0.02897   0.02206  -0.0488   0.0447   1.0000
  12.500   1.4298   0.03062   0.02369  -0.0472   0.0377   1.0000
  12.750   1.4379   0.03205   0.02517  -0.0460   0.0342   1.0000
  13.000   1.4444   0.03364   0.02680  -0.0448   0.0313   1.0000
  13.250   1.4530   0.03511   0.02832  -0.0438   0.0294   1.0000
  13.500   1.4602   0.03673   0.03001  -0.0428   0.0273   1.0000
  13.750   1.4651   0.03861   0.03193  -0.0418   0.0251   1.0000
  14.000   1.4723   0.04033   0.03372  -0.0410   0.0233   1.0000
  14.250   1.4774   0.04229   0.03573  -0.0403   0.0209   1.0000
  14.500   1.4816   0.04440   0.03791  -0.0396   0.0188   1.0000
  14.750   1.4846   0.04670   0.04025  -0.0390   0.0161   1.0000
  15.000   1.4872   0.04910   0.04272  -0.0386   0.0140   1.0000
  15.250   1.4883   0.05177   0.04544  -0.0382   0.0123   1.0000
  15.500   1.4890   0.05456   0.04830  -0.0380   0.0111   1.0000
  15.750   1.4881   0.05761   0.05142  -0.0380   0.0101   1.0000
  16.000   1.4879   0.06069   0.05460  -0.0381   0.0096   1.0000
  16.250   1.4861   0.06407   0.05808  -0.0384   0.0090   1.0000
  16.500   1.4829   0.06776   0.06187  -0.0390   0.0086   1.0000
  16.750   1.4789   0.07166   0.06588  -0.0397   0.0083   1.0000
  17.000   1.4735   0.07591   0.07024  -0.0407   0.0080   1.0000
  17.250   1.4672   0.08043   0.07488  -0.0420   0.0077   1.0000
  17.500   1.4611   0.08507   0.07965  -0.0434   0.0075   1.0000
  17.750   1.4542   0.08993   0.08464  -0.0451   0.0074   1.0000
  18.000   1.4456   0.09517   0.09001  -0.0471   0.0072   1.0000
  18.250   1.4363   0.10063   0.09560  -0.0492   0.0070   1.0000
  18.500   1.4262   0.10630   0.10140  -0.0516   0.0069   1.0000
  18.750   1.4152   0.11222   0.10745  -0.0543   0.0068   1.0000
  19.000   1.4033   0.11845   0.11381  -0.0572   0.0067   1.0000
  19.250   1.3917   0.12475   0.12023  -0.0604   0.0066   1.0000
<< Back to HQ 3.5/14 AIRFOIL (hq3514-il)

Polar data table (+)

Polar graphs


<< Back to HQ 3.5/14 AIRFOIL (hq3514-il)