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

HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 500,000
Max Cl/Cd: 84.56 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-500000-n5.txt
Download as CSV file: xf-hq2590sm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4671   0.08507   0.08274  -0.0354   1.0000   0.0084
  -9.500  -0.4796   0.07859   0.07630  -0.0384   1.0000   0.0085
  -9.250  -0.4945   0.07232   0.07009  -0.0416   1.0000   0.0085
  -8.750  -0.5585   0.04515   0.04268  -0.0662   0.9894   0.0085
  -8.500  -0.5524   0.03291   0.02980  -0.0743   0.9800   0.0089
  -8.250  -0.5317   0.02746   0.02386  -0.0774   0.9735   0.0094
  -8.000  -0.5064   0.02314   0.01898  -0.0798   0.9687   0.0102
  -7.750  -0.4812   0.02037   0.01572  -0.0808   0.9617   0.0112
  -7.500  -0.4516   0.01853   0.01351  -0.0821   0.9567   0.0119
  -7.250  -0.4238   0.01732   0.01213  -0.0829   0.9499   0.0124
  -7.000  -0.3941   0.01663   0.01134  -0.0837   0.9435   0.0128
  -6.750  -0.3657   0.01589   0.01048  -0.0842   0.9366   0.0134
  -6.500  -0.3377   0.01515   0.00959  -0.0845   0.9292   0.0142
  -6.250  -0.3102   0.01452   0.00880  -0.0846   0.9216   0.0150
  -6.000  -0.2827   0.01394   0.00808  -0.0846   0.9139   0.0156
  -5.750  -0.2566   0.01310   0.00709  -0.0844   0.9059   0.0161
  -5.500  -0.2304   0.01232   0.00622  -0.0843   0.8981   0.0168
  -5.250  -0.2039   0.01188   0.00573  -0.0842   0.8902   0.0175
  -4.750  -0.1500   0.01115   0.00486  -0.0839   0.8760   0.0194
  -4.500  -0.1231   0.01075   0.00438  -0.0838   0.8695   0.0201
  -4.250  -0.0960   0.01040   0.00396  -0.0836   0.8631   0.0207
  -4.000  -0.0688   0.01010   0.00358  -0.0835   0.8569   0.0212
  -3.750  -0.0416   0.00968   0.00310  -0.0835   0.8511   0.0226
  -3.500  -0.0142   0.00943   0.00283  -0.0834   0.8449   0.0245
  -3.250   0.0134   0.00924   0.00258  -0.0833   0.8395   0.0265
  -3.000   0.0410   0.00905   0.00234  -0.0833   0.8322   0.0284
  -2.750   0.0683   0.00885   0.00210  -0.0831   0.8232   0.0334
  -2.500   0.0956   0.00869   0.00192  -0.0829   0.8130   0.0414
  -2.250   0.1231   0.00853   0.00177  -0.0828   0.8046   0.0571
  -2.000   0.1505   0.00832   0.00164  -0.0828   0.7968   0.0881
  -1.750   0.1779   0.00803   0.00152  -0.0828   0.7895   0.1498
  -1.500   0.2043   0.00732   0.00135  -0.0831   0.7819   0.3311
  -1.250   0.2305   0.00676   0.00134  -0.0831   0.7741   0.5110
  -0.750   0.2846   0.00653   0.00137  -0.0826   0.7576   0.6235
  -0.500   0.3118   0.00650   0.00139  -0.0823   0.7499   0.6590
  -0.250   0.3391   0.00647   0.00142  -0.0821   0.7422   0.6899
   0.000   0.3667   0.00648   0.00142  -0.0819   0.7350   0.7024
   0.250   0.3946   0.00650   0.00142  -0.0818   0.7268   0.7114
   0.500   0.4222   0.00651   0.00143  -0.0817   0.7182   0.7206
   0.750   0.4497   0.00654   0.00145  -0.0815   0.7085   0.7296
   1.250   0.5044   0.00659   0.00151  -0.0811   0.6839   0.7489
   1.500   0.5313   0.00664   0.00155  -0.0808   0.6671   0.7595
   1.750   0.5577   0.00671   0.00159  -0.0804   0.6418   0.7708
   2.250   0.6043   0.00731   0.00176  -0.0785   0.5209   0.7968
   2.750   0.6487   0.00824   0.00221  -0.0764   0.3993   0.8288
   3.000   0.6725   0.00853   0.00239  -0.0757   0.3638   0.8468
   3.250   0.6969   0.00871   0.00255  -0.0750   0.3424   0.8674
   3.500   0.7209   0.00886   0.00270  -0.0742   0.3224   0.8916
   3.750   0.7454   0.00897   0.00284  -0.0734   0.3045   0.9290
   4.000   0.7771   0.00919   0.00301  -0.0744   0.2835   1.0000
   4.250   0.8026   0.00951   0.00322  -0.0741   0.2570   1.0000
   4.500   0.8277   0.00986   0.00344  -0.0738   0.2264   1.0000
   4.750   0.8514   0.01037   0.00373  -0.0732   0.1822   1.0000
   5.000   0.8746   0.01093   0.00408  -0.0727   0.1410   1.0000
   5.250   0.8984   0.01144   0.00445  -0.0721   0.1111   1.0000
   5.750   0.9472   0.01229   0.00514  -0.0712   0.0776   1.0000
   6.000   0.9717   0.01269   0.00550  -0.0708   0.0664   1.0000
   6.250   0.9963   0.01307   0.00587  -0.0703   0.0577   1.0000
   6.500   1.0207   0.01346   0.00625  -0.0699   0.0503   1.0000
   6.750   1.0446   0.01390   0.00666  -0.0693   0.0418   1.0000
   7.000   1.0684   0.01434   0.00708  -0.0688   0.0344   1.0000
   7.250   1.0919   0.01481   0.00757  -0.0682   0.0295   1.0000
   7.500   1.1148   0.01532   0.00807  -0.0675   0.0260   1.0000
   7.750   1.1376   0.01584   0.00862  -0.0668   0.0237   1.0000
   8.000   1.1606   0.01631   0.00916  -0.0661   0.0223   1.0000
   8.250   1.1829   0.01683   0.00972  -0.0654   0.0208   1.0000
   8.500   1.2043   0.01743   0.01037  -0.0645   0.0194   1.0000
   8.750   1.2241   0.01818   0.01117  -0.0634   0.0180   1.0000
   9.000   1.2457   0.01869   0.01176  -0.0626   0.0173   1.0000
   9.250   1.2663   0.01929   0.01244  -0.0616   0.0164   1.0000
   9.500   1.2863   0.01990   0.01312  -0.0606   0.0155   1.0000
   9.750   1.3054   0.02056   0.01385  -0.0594   0.0146   1.0000
  10.000   1.3216   0.02147   0.01481  -0.0579   0.0135   1.0000
  10.250   1.3393   0.02217   0.01560  -0.0566   0.0128   1.0000
  10.500   1.3564   0.02287   0.01641  -0.0552   0.0122   1.0000
  10.750   1.3714   0.02359   0.01722  -0.0535   0.0115   1.0000
  11.000   1.3849   0.02434   0.01805  -0.0515   0.0109   1.0000
  11.250   1.3977   0.02513   0.01889  -0.0496   0.0103   1.0000
  11.500   1.4068   0.02617   0.02001  -0.0473   0.0097   1.0000
  11.750   1.4171   0.02714   0.02111  -0.0452   0.0092   1.0000
  12.000   1.4276   0.02812   0.02219  -0.0433   0.0087   1.0000
  12.250   1.4381   0.02912   0.02329  -0.0415   0.0082   1.0000
  12.500   1.4463   0.03032   0.02460  -0.0397   0.0078   1.0000
  12.750   1.4538   0.03162   0.02600  -0.0379   0.0075   1.0000
  13.000   1.4603   0.03305   0.02751  -0.0363   0.0072   1.0000
  13.250   1.4627   0.03490   0.02946  -0.0346   0.0069   1.0000
  13.500   1.4640   0.03694   0.03163  -0.0330   0.0067   1.0000
  13.750   1.4655   0.03906   0.03390  -0.0318   0.0065   1.0000
  14.000   1.4652   0.04146   0.03646  -0.0307   0.0063   1.0000
  14.250   1.4641   0.04407   0.03922  -0.0299   0.0062   1.0000
  14.500   1.4612   0.04702   0.04234  -0.0294   0.0060   1.0000
  14.750   1.4568   0.05033   0.04580  -0.0293   0.0059   1.0000
  15.000   1.4509   0.05401   0.04964  -0.0297   0.0057   1.0000
  15.250   1.4436   0.05814   0.05393  -0.0305   0.0056   1.0000
  15.500   1.4341   0.06288   0.05883  -0.0320   0.0055   1.0000
  15.750   1.4233   0.06828   0.06439  -0.0342   0.0054   1.0000
  16.000   1.4092   0.07472   0.07101  -0.0373   0.0054   1.0000
  16.250   1.3943   0.08176   0.07822  -0.0411   0.0054   1.0000
  16.500   1.3771   0.08961   0.08625  -0.0454   0.0054   1.0000
  16.750   1.3570   0.09826   0.09507  -0.0503   0.0054   1.0000
  17.000   1.3357   0.10739   0.10436  -0.0556   0.0053   1.0000
  17.250   1.3121   0.11723   0.11437  -0.0613   0.0054   1.0000
  17.500   1.2882   0.12744   0.12473  -0.0673   0.0054   1.0000
  17.750   1.2638   0.13819   0.13564  -0.0737   0.0055   1.0000
  18.000   1.2393   0.14941   0.14699  -0.0805   0.0055   1.0000
  18.250   1.2136   0.16147   0.15919  -0.0879   0.0056   1.0000
  18.500   1.1829   0.17565   0.17353  -0.0966   0.0057   1.0000
<< Back to HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)

Polar data table (+)

Polar graphs


<< Back to HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)