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

HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il)
Reynolds number: 500,000
Max Cl/Cd: 97.08 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3015-il-500000.txt
Download as CSV file: xf-hq3015-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/15 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.6985   0.08704   0.08412  -0.0646   1.0000   0.0148
 -15.500  -0.7575   0.07185   0.06861  -0.0743   1.0000   0.0144
 -15.250  -0.7861   0.06329   0.05984  -0.0798   1.0000   0.0142
 -15.000  -0.8038   0.05732   0.05372  -0.0834   1.0000   0.0143
 -14.750  -0.8197   0.05212   0.04836  -0.0861   1.0000   0.0143
 -14.500  -0.8262   0.04849   0.04463  -0.0879   1.0000   0.0145
 -14.250  -0.8366   0.04464   0.04064  -0.0893   1.0000   0.0145
 -14.000  -0.8439   0.04142   0.03730  -0.0901   1.0000   0.0147
 -13.750  -0.8475   0.03883   0.03461  -0.0904   1.0000   0.0149
 -13.500  -0.8528   0.03630   0.03196  -0.0902   1.0000   0.0150
 -13.250  -0.8574   0.03414   0.02969  -0.0893   1.0000   0.0152
 -13.000  -0.8635   0.03230   0.02775  -0.0877   1.0000   0.0154
 -12.750  -0.8767   0.03098   0.02637  -0.0842   1.0000   0.0155
 -12.500  -0.8695   0.02927   0.02452  -0.0847   0.9971   0.0157
 -12.250  -0.8458   0.02731   0.02238  -0.0879   0.9909   0.0160
 -12.000  -0.8248   0.02506   0.02001  -0.0909   0.9843   0.0166
 -11.750  -0.7993   0.02369   0.01856  -0.0930   0.9788   0.0171
 -11.500  -0.7701   0.02263   0.01744  -0.0951   0.9738   0.0178
 -11.250  -0.7381   0.02158   0.01629  -0.0975   0.9704   0.0187
 -11.000  -0.7104   0.02068   0.01524  -0.0987   0.9635   0.0197
 -10.750  -0.6834   0.01959   0.01412  -0.1001   0.9569   0.0209
 -10.500  -0.6573   0.01905   0.01355  -0.1005   0.9488   0.0224
 -10.250  -0.6302   0.01853   0.01289  -0.1009   0.9413   0.0241
 -10.000  -0.6122   0.01773   0.01209  -0.1000   0.9310   0.0262
  -9.750  -0.5875   0.01736   0.01162  -0.0998   0.9237   0.0286
  -9.500  -0.5688   0.01673   0.01095  -0.0987   0.9146   0.0311
  -9.250  -0.5442   0.01651   0.01068  -0.0983   0.9079   0.0336
  -9.000  -0.5203   0.01636   0.01042  -0.0977   0.9001   0.0356
  -8.750  -0.4997   0.01572   0.00975  -0.0969   0.8934   0.0381
  -8.500  -0.4763   0.01549   0.00949  -0.0963   0.8861   0.0401
  -8.250  -0.4515   0.01527   0.00918  -0.0959   0.8799   0.0420
  -8.000  -0.4291   0.01481   0.00866  -0.0952   0.8734   0.0441
  -7.750  -0.4058   0.01443   0.00827  -0.0946   0.8670   0.0463
  -7.500  -0.3806   0.01419   0.00796  -0.0942   0.8618   0.0484
  -7.250  -0.3555   0.01398   0.00771  -0.0938   0.8554   0.0506
  -7.000  -0.3310   0.01365   0.00730  -0.0933   0.8497   0.0525
  -6.750  -0.3077   0.01316   0.00681  -0.0928   0.8444   0.0559
  -6.500  -0.2824   0.01292   0.00654  -0.0924   0.8384   0.0587
  -6.250  -0.2565   0.01269   0.00624  -0.0921   0.8331   0.0613
  -6.000  -0.2323   0.01225   0.00575  -0.0916   0.8279   0.0642
  -5.750  -0.2076   0.01186   0.00537  -0.0912   0.8221   0.0684
  -5.500  -0.1813   0.01162   0.00507  -0.0909   0.8172   0.0729
  -5.250  -0.1560   0.01127   0.00471  -0.0906   0.8121   0.0797
  -5.000  -0.1297   0.01104   0.00447  -0.0903   0.8065   0.0869
  -4.750  -0.1038   0.01070   0.00415  -0.0900   0.8016   0.0994
  -4.500  -0.0778   0.01038   0.00389  -0.0898   0.7968   0.1186
  -4.250  -0.0526   0.00997   0.00365  -0.0896   0.7912   0.1572
  -4.000  -0.0272   0.00955   0.00342  -0.0894   0.7862   0.2138
  -3.750  -0.0013   0.00919   0.00322  -0.0893   0.7815   0.2710
  -3.500   0.0229   0.00862   0.00298  -0.0889   0.7757   0.3517
  -3.250   0.0476   0.00818   0.00288  -0.0886   0.7704   0.4644
  -3.000   0.0749   0.00808   0.00285  -0.0884   0.7654   0.5087
  -2.750   0.1022   0.00802   0.00285  -0.0882   0.7597   0.5379
  -2.500   0.1303   0.00801   0.00281  -0.0881   0.7548   0.5581
  -2.250   0.1587   0.00804   0.00281  -0.0881   0.7501   0.5740
  -2.000   0.1865   0.00803   0.00281  -0.0880   0.7447   0.5866
  -1.750   0.2147   0.00803   0.00280  -0.0880   0.7397   0.5974
  -1.500   0.2433   0.00809   0.00281  -0.0880   0.7352   0.6106
  -1.250   0.2708   0.00811   0.00285  -0.0878   0.7292   0.6248
  -1.000   0.2987   0.00815   0.00286  -0.0876   0.7233   0.6370
  -0.750   0.3266   0.00816   0.00286  -0.0875   0.7170   0.6445
  -0.500   0.3544   0.00816   0.00285  -0.0874   0.7099   0.6521
  -0.250   0.3826   0.00819   0.00281  -0.0874   0.7036   0.6587
   0.000   0.4101   0.00818   0.00284  -0.0872   0.6966   0.6653
   0.250   0.4382   0.00822   0.00282  -0.0872   0.6904   0.6730
   0.500   0.4657   0.00823   0.00287  -0.0870   0.6842   0.6804
   0.750   0.4936   0.00828   0.00288  -0.0869   0.6777   0.6882
   1.000   0.5214   0.00830   0.00290  -0.0868   0.6717   0.6939
   1.250   0.5488   0.00831   0.00294  -0.0867   0.6643   0.7000
   1.500   0.5767   0.00837   0.00293  -0.0867   0.6576   0.7059
   1.750   0.6036   0.00836   0.00298  -0.0864   0.6492   0.7112
   2.000   0.6307   0.00841   0.00299  -0.0862   0.6404   0.7173
   2.250   0.6575   0.00843   0.00302  -0.0860   0.6305   0.7231
   2.500   0.6842   0.00847   0.00308  -0.0857   0.6217   0.7291
   2.750   0.7110   0.00854   0.00312  -0.0854   0.6121   0.7359
   3.000   0.7373   0.00856   0.00318  -0.0851   0.6016   0.7418
   3.250   0.7634   0.00864   0.00325  -0.0847   0.5910   0.7483
   3.500   0.7890   0.00873   0.00331  -0.0843   0.5793   0.7551
   3.750   0.8143   0.00880   0.00341  -0.0838   0.5659   0.7618
   4.000   0.8393   0.00892   0.00350  -0.0832   0.5510   0.7694
   4.250   0.8633   0.00903   0.00361  -0.0824   0.5352   0.7761
   4.500   0.8868   0.00921   0.00373  -0.0817   0.5177   0.7843
   4.750   0.9096   0.00937   0.00388  -0.0807   0.4988   0.7918
   5.250   0.9527   0.00982   0.00424  -0.0784   0.4572   0.8090
   5.500   0.9733   0.01008   0.00445  -0.0771   0.4369   0.8187
   5.750   0.9930   0.01035   0.00468  -0.0757   0.4150   0.8296
   6.000   1.0108   0.01066   0.00494  -0.0739   0.3928   0.8415
   6.250   1.0289   0.01093   0.00519  -0.0722   0.3717   0.8555
   6.500   1.0453   0.01120   0.00546  -0.0701   0.3513   0.8750
   6.750   1.0618   0.01143   0.00576  -0.0680   0.3321   0.9189
   7.000   1.0918   0.01187   0.00613  -0.0692   0.3118   1.0000
   7.250   1.1075   0.01229   0.00646  -0.0672   0.2970   1.0000
   7.750   1.1394   0.01312   0.00719  -0.0635   0.2715   1.0000
   8.000   1.1557   0.01354   0.00758  -0.0617   0.2599   1.0000
   8.250   1.1710   0.01400   0.00800  -0.0598   0.2486   1.0000
   8.500   1.1858   0.01450   0.00845  -0.0580   0.2376   1.0000
   8.750   1.2025   0.01495   0.00889  -0.0564   0.2264   1.0000
   9.000   1.2175   0.01547   0.00938  -0.0547   0.2147   1.0000
   9.250   1.2314   0.01606   0.00993  -0.0529   0.2047   1.0000
   9.500   1.2450   0.01669   0.01050  -0.0511   0.1932   1.0000
   9.750   1.2604   0.01725   0.01107  -0.0496   0.1847   1.0000
  10.000   1.2729   0.01798   0.01177  -0.0478   0.1757   1.0000
  10.250   1.2872   0.01864   0.01242  -0.0463   0.1671   1.0000
  10.500   1.3004   0.01938   0.01316  -0.0447   0.1597   1.0000
  10.750   1.3132   0.02016   0.01392  -0.0432   0.1516   1.0000
  11.000   1.3266   0.02094   0.01471  -0.0418   0.1440   1.0000
  11.250   1.3381   0.02185   0.01560  -0.0403   0.1361   1.0000
  11.500   1.3513   0.02268   0.01644  -0.0390   0.1284   1.0000
  11.750   1.3615   0.02373   0.01746  -0.0375   0.1213   1.0000
  12.000   1.3747   0.02461   0.01838  -0.0363   0.1149   1.0000
  12.250   1.3838   0.02578   0.01952  -0.0349   0.1081   1.0000
  12.500   1.3958   0.02678   0.02057  -0.0338   0.1021   1.0000
  12.750   1.4038   0.02809   0.02186  -0.0324   0.0953   1.0000
  13.000   1.4144   0.02925   0.02305  -0.0313   0.0891   1.0000
  13.250   1.4211   0.03073   0.02451  -0.0300   0.0828   1.0000
  13.500   1.4304   0.03204   0.02586  -0.0290   0.0774   1.0000
  13.750   1.4354   0.03374   0.02754  -0.0279   0.0710   1.0000
  14.000   1.4435   0.03522   0.02907  -0.0269   0.0664   1.0000
  14.250   1.4478   0.03708   0.03093  -0.0260   0.0614   1.0000
  14.500   1.4543   0.03880   0.03270  -0.0252   0.0575   1.0000
  14.750   1.4588   0.04075   0.03467  -0.0244   0.0533   1.0000
  15.000   1.4619   0.04289   0.03684  -0.0237   0.0502   1.0000
  15.250   1.4683   0.04478   0.03881  -0.0232   0.0478   1.0000
  15.500   1.4711   0.04707   0.04114  -0.0228   0.0444   1.0000
  15.750   1.4722   0.04961   0.04372  -0.0224   0.0420   1.0000
  16.000   1.4763   0.05189   0.04607  -0.0222   0.0391   1.0000
  16.250   1.4780   0.05450   0.04874  -0.0221   0.0368   1.0000
  16.500   1.4763   0.05759   0.05187  -0.0222   0.0341   1.0000
  16.750   1.4783   0.06031   0.05468  -0.0224   0.0321   1.0000
  17.000   1.4764   0.06357   0.05800  -0.0227   0.0294   1.0000
  17.250   1.4735   0.06707   0.06156  -0.0232   0.0274   1.0000
  17.500   1.4719   0.07049   0.06507  -0.0238   0.0252   1.0000
  17.750   1.4641   0.07485   0.06948  -0.0248   0.0220   1.0000
  18.000   1.4577   0.07913   0.07384  -0.0260   0.0193   1.0000
  18.250   1.4457   0.08435   0.07911  -0.0276   0.0159   1.0000
  18.500   1.4371   0.08923   0.08408  -0.0292   0.0148   1.0000
  18.750   1.4265   0.09453   0.08949  -0.0312   0.0132   1.0000
  19.000   1.4104   0.10085   0.09590  -0.0337   0.0112   1.0000
  19.250   1.4009   0.10622   0.10139  -0.0360   0.0108   1.0000
<< Back to HQ 3.0/15 AIRFOIL (hq3015-il)

Polar data table (+)

Polar graphs


<< Back to HQ 3.0/15 AIRFOIL (hq3015-il)