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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 500,000
Max Cl/Cd: 116.5 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq308-il-500000.txt
Download as CSV file: xf-hq308-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/8 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3687   0.08456   0.08245  -0.0335   1.0000   0.0104
  -7.500  -0.3809   0.08276   0.08072  -0.0311   1.0000   0.0104
  -7.250  -0.4022   0.08197   0.08000  -0.0267   1.0000   0.0104
  -7.000  -0.3770   0.07589   0.07391  -0.0364   0.9963   0.0105
  -6.750  -0.3487   0.06906   0.06705  -0.0483   0.9920   0.0105
  -6.500  -0.3276   0.05825   0.05614  -0.0623   0.9861   0.0110
  -6.250  -0.3004   0.05235   0.05013  -0.0703   0.9832   0.0115
  -6.000  -0.2737   0.04807   0.04572  -0.0757   0.9792   0.0121
  -5.750  -0.2447   0.04372   0.04122  -0.0808   0.9748   0.0130
  -5.500  -0.2106   0.03907   0.03635  -0.0861   0.9721   0.0141
  -5.250  -0.1724   0.03453   0.03151  -0.0906   0.9702   0.0165
  -5.000  -0.1319   0.03277   0.02941  -0.0924   0.9677   0.0183
  -3.500   0.0365   0.01350   0.00813  -0.0966   0.9361   0.0162
  -3.250   0.0642   0.01168   0.00607  -0.0961   0.9307   0.0147
  -3.000   0.0905   0.01048   0.00473  -0.0954   0.9246   0.0142
  -2.750   0.1172   0.00967   0.00381  -0.0949   0.9182   0.0147
  -2.500   0.1444   0.00911   0.00313  -0.0946   0.9121   0.0167
  -2.250   0.1715   0.00862   0.00254  -0.0942   0.9050   0.0229
  -2.000   0.1986   0.00814   0.00220  -0.0939   0.8980   0.0790
  -1.750   0.2242   0.00732   0.00197  -0.0939   0.8899   0.2756
  -1.500   0.2481   0.00641   0.00195  -0.0936   0.8812   0.5777
  -1.250   0.2740   0.00623   0.00195  -0.0929   0.8743   0.6637
  -1.000   0.3004   0.00618   0.00192  -0.0924   0.8660   0.6955
  -0.750   0.3270   0.00613   0.00186  -0.0919   0.8580   0.7243
  -0.500   0.3523   0.00606   0.00185  -0.0911   0.8483   0.7658
  -0.250   0.3768   0.00598   0.00184  -0.0900   0.8377   0.8051
   0.000   0.4022   0.00590   0.00181  -0.0893   0.8286   0.8314
   0.250   0.4285   0.00585   0.00174  -0.0887   0.8202   0.8491
   0.500   0.4539   0.00576   0.00170  -0.0880   0.8102   0.8729
   0.750   0.4787   0.00561   0.00165  -0.0871   0.7992   0.9166
   1.000   0.5155   0.00554   0.00156  -0.0889   0.7855   1.0000
   1.250   0.5432   0.00560   0.00155  -0.0889   0.7727   1.0000
   1.500   0.5708   0.00567   0.00156  -0.0888   0.7607   1.0000
   1.750   0.5982   0.00575   0.00158  -0.0887   0.7477   1.0000
   2.000   0.6254   0.00584   0.00161  -0.0886   0.7337   1.0000
   2.250   0.6523   0.00593   0.00165  -0.0884   0.7178   1.0000
   2.500   0.6790   0.00605   0.00171  -0.0881   0.7003   1.0000
   2.750   0.7056   0.00617   0.00180  -0.0878   0.6804   1.0000
   3.000   0.7317   0.00633   0.00188  -0.0874   0.6580   1.0000
   3.250   0.7575   0.00651   0.00198  -0.0870   0.6315   1.0000
   3.500   0.7829   0.00672   0.00210  -0.0865   0.5992   1.0000
   3.750   0.8075   0.00701   0.00225  -0.0859   0.5601   1.0000
   4.000   0.8303   0.00745   0.00248  -0.0850   0.5023   1.0000
   4.250   0.8520   0.00804   0.00275  -0.0840   0.4337   1.0000
   4.500   0.8736   0.00868   0.00308  -0.0831   0.3657   1.0000
   4.750   0.8956   0.00933   0.00342  -0.0823   0.3035   1.0000
   5.000   0.9175   0.01001   0.00379  -0.0815   0.2423   1.0000
   5.250   0.9408   0.01053   0.00416  -0.0809   0.2027   1.0000
   5.750   0.9881   0.01150   0.00489  -0.0798   0.1443   1.0000
   6.000   1.0088   0.01233   0.00539  -0.0790   0.0890   1.0000
   6.250   1.0290   0.01323   0.00600  -0.0780   0.0440   1.0000
   6.500   1.0502   0.01404   0.00668  -0.0770   0.0186   1.0000
   6.750   1.0713   0.01490   0.00750  -0.0759   0.0074   1.0000
   7.000   1.0939   0.01555   0.00831  -0.0749   0.0066   1.0000
   7.250   1.1155   0.01632   0.00922  -0.0738   0.0062   1.0000
   7.500   1.1356   0.01725   0.01030  -0.0725   0.0059   1.0000
   7.750   1.1543   0.01831   0.01151  -0.0710   0.0059   1.0000
   8.000   1.1712   0.01958   0.01294  -0.0692   0.0059   1.0000
   8.250   1.1863   0.02109   0.01463  -0.0672   0.0059   1.0000
   8.500   1.2005   0.02286   0.01658  -0.0651   0.0060   1.0000
   8.750   1.2147   0.02495   0.01889  -0.0630   0.0062   1.0000
   9.000   1.2286   0.02756   0.02175  -0.0609   0.0064   1.0000
   9.250   1.2406   0.03088   0.02539  -0.0587   0.0068   1.0000
   9.500   1.2462   0.03538   0.03029  -0.0561   0.0072   1.0000
   9.750   1.2581   0.03819   0.03327  -0.0542   0.0077   1.0000
  10.000   1.2636   0.04074   0.03612  -0.0517   0.0078   1.0000
  10.250   1.2674   0.04289   0.03850  -0.0489   0.0080   1.0000
  10.500   1.2600   0.04567   0.04152  -0.0450   0.0079   1.0000
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