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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.71 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2510-il-1000000.txt
Download as CSV file: xf-hq2510-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.3571   0.14727   0.14568  -0.0167   1.0000   0.0069
 -13.750  -0.3532   0.14425   0.14265  -0.0182   1.0000   0.0069
  -7.500  -0.4397   0.02125   0.01792  -0.0819   0.9667   0.0064
  -7.250  -0.4165   0.01904   0.01537  -0.0821   0.9575   0.0066
  -7.000  -0.3938   0.01726   0.01331  -0.0817   0.9479   0.0067
  -6.750  -0.3697   0.01604   0.01185  -0.0813   0.9392   0.0068
  -6.500  -0.3458   0.01502   0.01064  -0.0808   0.9299   0.0069
  -6.250  -0.3247   0.01288   0.00817  -0.0798   0.9205   0.0072
  -6.000  -0.3016   0.01157   0.00665  -0.0791   0.9124   0.0075
  -5.750  -0.2771   0.01071   0.00565  -0.0785   0.9041   0.0077
  -5.500  -0.2519   0.01004   0.00486  -0.0781   0.8968   0.0083
  -5.250  -0.2258   0.00959   0.00433  -0.0777   0.8892   0.0091
  -5.000  -0.1993   0.00921   0.00386  -0.0774   0.8823   0.0101
  -4.750  -0.1726   0.00891   0.00348  -0.0772   0.8751   0.0108
  -4.500  -0.1461   0.00842   0.00287  -0.0769   0.8683   0.0131
  -4.250  -0.1191   0.00815   0.00258  -0.0767   0.8613   0.0166
  -4.000  -0.0921   0.00785   0.00235  -0.0765   0.8547   0.0327
  -3.750  -0.0645   0.00774   0.00219  -0.0765   0.8476   0.0384
  -3.500  -0.0370   0.00758   0.00201  -0.0764   0.8409   0.0460
  -3.250  -0.0095   0.00743   0.00185  -0.0763   0.8333   0.0546
  -3.000   0.0179   0.00725   0.00170  -0.0762   0.8257   0.0706
  -2.750   0.0450   0.00701   0.00155  -0.0762   0.8178   0.1062
  -2.500   0.0717   0.00658   0.00138  -0.0762   0.8101   0.1897
  -2.250   0.0980   0.00613   0.00123  -0.0761   0.8029   0.2982
  -2.000   0.1240   0.00558   0.00112  -0.0761   0.7952   0.4431
  -1.750   0.1510   0.00537   0.00106  -0.0760   0.7874   0.5167
  -1.500   0.1784   0.00526   0.00103  -0.0759   0.7779   0.5602
  -1.250   0.2061   0.00521   0.00101  -0.0758   0.7687   0.5902
  -1.000   0.2336   0.00518   0.00100  -0.0757   0.7592   0.6201
  -0.750   0.2612   0.00516   0.00099  -0.0755   0.7491   0.6425
  -0.500   0.2890   0.00516   0.00099  -0.0755   0.7400   0.6608
  -0.250   0.3165   0.00516   0.00101  -0.0753   0.7315   0.6851
   0.000   0.3442   0.00517   0.00102  -0.0752   0.7221   0.7021
   0.250   0.3719   0.00518   0.00103  -0.0751   0.7120   0.7138
   0.500   0.3995   0.00521   0.00105  -0.0750   0.7012   0.7258
   0.750   0.4270   0.00525   0.00107  -0.0749   0.6905   0.7366
   1.250   0.4823   0.00532   0.00112  -0.0747   0.6677   0.7543
   1.500   0.5099   0.00537   0.00115  -0.0746   0.6554   0.7631
   1.750   0.5371   0.00544   0.00119  -0.0745   0.6398   0.7726
   2.000   0.5639   0.00551   0.00124  -0.0742   0.6221   0.7822
   2.250   0.5909   0.00558   0.00130  -0.0740   0.6044   0.7925
   2.500   0.6175   0.00568   0.00137  -0.0738   0.5835   0.8037
   2.750   0.6436   0.00581   0.00144  -0.0734   0.5573   0.8162
   3.000   0.6693   0.00595   0.00154  -0.0730   0.5300   0.8302
   3.250   0.6941   0.00613   0.00166  -0.0724   0.4965   0.8470
   3.500   0.7177   0.00635   0.00180  -0.0717   0.4569   0.8701
   3.750   0.7391   0.00650   0.00196  -0.0703   0.4159   0.9258
   4.000   0.7730   0.00684   0.00215  -0.0719   0.3683   1.0000
   4.250   0.7979   0.00719   0.00235  -0.0715   0.3322   1.0000
   4.500   0.8230   0.00752   0.00255  -0.0712   0.3021   1.0000
   4.750   0.8476   0.00788   0.00277  -0.0708   0.2704   1.0000
   5.000   0.8721   0.00826   0.00300  -0.0703   0.2394   1.0000
   5.250   0.8959   0.00869   0.00325  -0.0698   0.2038   1.0000
   5.500   0.9203   0.00906   0.00351  -0.0693   0.1776   1.0000
   5.750   0.9445   0.00945   0.00378  -0.0689   0.1532   1.0000
   6.000   0.9691   0.00979   0.00404  -0.0684   0.1343   1.0000
   6.250   0.9919   0.01029   0.00439  -0.0677   0.1051   1.0000
   6.500   1.0129   0.01098   0.00483  -0.0668   0.0677   1.0000
   7.000   1.0507   0.01280   0.00626  -0.0641   0.0059   1.0000
   7.250   1.0740   0.01324   0.00676  -0.0634   0.0051   1.0000
   7.500   1.0971   0.01369   0.00728  -0.0626   0.0048   1.0000
   7.750   1.1196   0.01418   0.00782  -0.0618   0.0046   1.0000
   8.000   1.1415   0.01473   0.00843  -0.0609   0.0042   1.0000
   8.250   1.1623   0.01536   0.00914  -0.0598   0.0039   1.0000
   8.500   1.1820   0.01608   0.00994  -0.0586   0.0036   1.0000
   8.750   1.2010   0.01682   0.01077  -0.0573   0.0035   1.0000
   9.000   1.2168   0.01781   0.01187  -0.0555   0.0033   1.0000
   9.250   1.2323   0.01876   0.01291  -0.0537   0.0033   1.0000
   9.500   1.2464   0.01975   0.01399  -0.0517   0.0033   1.0000
   9.750   1.2574   0.02089   0.01524  -0.0492   0.0032   1.0000
  10.000   1.2654   0.02197   0.01642  -0.0462   0.0032   1.0000
  10.250   1.2728   0.02305   0.01760  -0.0432   0.0033   1.0000
  10.500   1.2780   0.02435   0.01902  -0.0401   0.0033   1.0000
  10.750   1.2835   0.02574   0.02055  -0.0372   0.0034   1.0000
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