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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 200,000
Max Cl/Cd: 75.32 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3513-il-200000-n5.txt
Download as CSV file: xf-hq3513-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/13 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3740   0.08882   0.08543  -0.0531   0.9982   0.0154
 -10.000  -0.3770   0.08069   0.07733  -0.0600   0.9913   0.0152
  -9.750  -0.4851   0.04407   0.04017  -0.0960   0.9649   0.0138
  -9.500  -0.4916   0.03698   0.03246  -0.1015   0.9525   0.0139
  -9.250  -0.4812   0.03279   0.02777  -0.1037   0.9442   0.0142
  -9.000  -0.4670   0.02990   0.02448  -0.1043   0.9358   0.0145
  -8.750  -0.4466   0.02733   0.02151  -0.1052   0.9297   0.0149
  -8.500  -0.4263   0.02535   0.01919  -0.1053   0.9229   0.0154
  -8.250  -0.4031   0.02370   0.01722  -0.1054   0.9170   0.0161
  -8.000  -0.3772   0.02240   0.01571  -0.1060   0.9123   0.0170
  -7.750  -0.3539   0.02176   0.01500  -0.1057   0.9052   0.0180
  -7.500  -0.3276   0.02080   0.01389  -0.1059   0.9003   0.0190
  -7.250  -0.3039   0.01979   0.01271  -0.1056   0.8942   0.0200
  -7.000  -0.2797   0.01883   0.01158  -0.1052   0.8880   0.0213
  -6.750  -0.2529   0.01813   0.01081  -0.1053   0.8835   0.0232
  -6.500  -0.2297   0.01751   0.01010  -0.1047   0.8764   0.0259
  -6.250  -0.2039   0.01687   0.00939  -0.1046   0.8712   0.0295
  -6.000  -0.1778   0.01646   0.00887  -0.1044   0.8657   0.0340
  -5.750  -0.1525   0.01607   0.00846  -0.1041   0.8596   0.0384
  -5.500  -0.1246   0.01583   0.00809  -0.1041   0.8550   0.0437
  -5.250  -0.0991   0.01556   0.00783  -0.1040   0.8490   0.0501
  -5.000  -0.0721   0.01539   0.00756  -0.1038   0.8433   0.0561
  -4.750  -0.0456   0.01484   0.00700  -0.1038   0.8390   0.0609
  -4.500  -0.0207   0.01449   0.00659  -0.1034   0.8324   0.0647
  -4.250   0.0061   0.01418   0.00619  -0.1032   0.8271   0.0692
  -4.000   0.0328   0.01378   0.00579  -0.1031   0.8224   0.0768
  -3.750   0.0586   0.01350   0.00547  -0.1028   0.8162   0.0852
  -3.500   0.0858   0.01320   0.00514  -0.1028   0.8112   0.0982
  -3.250   0.1124   0.01287   0.00487  -0.1027   0.8060   0.1217
  -3.000   0.1380   0.01244   0.00465  -0.1026   0.8000   0.1749
  -2.750   0.1639   0.01181   0.00437  -0.1027   0.7953   0.2824
  -2.500   0.1872   0.01116   0.00434  -0.1023   0.7893   0.4496
  -2.250   0.2130   0.01100   0.00438  -0.1018   0.7836   0.5264
  -2.000   0.2408   0.01095   0.00434  -0.1015   0.7790   0.5685
  -1.750   0.2669   0.01097   0.00437  -0.1011   0.7721   0.5963
  -1.500   0.2941   0.01099   0.00438  -0.1007   0.7664   0.6251
  -1.250   0.3202   0.01106   0.00447  -0.1000   0.7602   0.6575
  -1.000   0.3464   0.01110   0.00452  -0.0994   0.7531   0.6775
  -0.750   0.3735   0.01111   0.00448  -0.0990   0.7458   0.6905
  -0.500   0.4005   0.01111   0.00442  -0.0986   0.7373   0.7004
  -0.250   0.4273   0.01111   0.00437  -0.0983   0.7285   0.7073
   0.000   0.4550   0.01110   0.00429  -0.0981   0.7207   0.7141
   0.250   0.4817   0.01112   0.00428  -0.0978   0.7118   0.7210
   0.500   0.5092   0.01112   0.00423  -0.0976   0.7042   0.7275
   0.750   0.5359   0.01115   0.00423  -0.0974   0.6950   0.7349
   1.000   0.5626   0.01116   0.00423  -0.0970   0.6865   0.7412
   1.250   0.5895   0.01120   0.00421  -0.0967   0.6768   0.7490
   1.500   0.6154   0.01122   0.00425  -0.0963   0.6666   0.7554
   1.750   0.6422   0.01127   0.00426  -0.0960   0.6576   0.7634
   2.000   0.6682   0.01131   0.00431  -0.0956   0.6483   0.7703
   2.250   0.6944   0.01136   0.00436  -0.0952   0.6383   0.7787
   2.500   0.7202   0.01141   0.00442  -0.0947   0.6275   0.7861
   2.750   0.7460   0.01148   0.00447  -0.0943   0.6153   0.7950
   3.000   0.7707   0.01153   0.00454  -0.0936   0.6021   0.8034
   3.250   0.7954   0.01161   0.00463  -0.0930   0.5884   0.8129
   3.500   0.8196   0.01169   0.00471  -0.0922   0.5726   0.8235
   3.750   0.8430   0.01179   0.00480  -0.0913   0.5545   0.8349
   4.000   0.8662   0.01191   0.00490  -0.0903   0.5338   0.8484
   4.250   0.8883   0.01207   0.00503  -0.0892   0.5119   0.8653
   4.500   0.9102   0.01223   0.00518  -0.0880   0.4866   0.8920
   4.750   0.9392   0.01247   0.00536  -0.0885   0.4573   1.0000
   5.000   0.9599   0.01288   0.00564  -0.0874   0.4298   1.0000
   5.250   0.9797   0.01334   0.00595  -0.0862   0.4036   1.0000
   5.500   0.9989   0.01382   0.00629  -0.0849   0.3784   1.0000
   5.750   1.0182   0.01429   0.00666  -0.0836   0.3551   1.0000
   6.000   1.0368   0.01479   0.00706  -0.0823   0.3342   1.0000
   6.250   1.0553   0.01528   0.00746  -0.0809   0.3167   1.0000
   6.500   1.0736   0.01578   0.00789  -0.0795   0.3028   1.0000
   6.750   1.0920   0.01626   0.00833  -0.0781   0.2909   1.0000
   7.000   1.1102   0.01671   0.00878  -0.0767   0.2815   1.0000
   7.250   1.1265   0.01722   0.00925  -0.0749   0.2729   1.0000
   7.500   1.1447   0.01768   0.00973  -0.0735   0.2648   1.0000
   7.750   1.1612   0.01822   0.01025  -0.0719   0.2574   1.0000
   8.000   1.1790   0.01870   0.01078  -0.0705   0.2491   1.0000
   8.250   1.1954   0.01925   0.01134  -0.0690   0.2419   1.0000
   8.500   1.2130   0.01975   0.01189  -0.0676   0.2342   1.0000
   8.750   1.2291   0.02034   0.01249  -0.0661   0.2275   1.0000
   9.000   1.2464   0.02086   0.01309  -0.0648   0.2199   1.0000
   9.250   1.2617   0.02150   0.01376  -0.0633   0.2133   1.0000
   9.500   1.2788   0.02205   0.01441  -0.0620   0.2060   1.0000
   9.750   1.2930   0.02274   0.01513  -0.0604   0.1980   1.0000
  10.000   1.3073   0.02343   0.01587  -0.0590   0.1880   1.0000
  10.250   1.3208   0.02418   0.01666  -0.0575   0.1763   1.0000
  10.500   1.3338   0.02501   0.01754  -0.0560   0.1660   1.0000
  10.750   1.3450   0.02596   0.01850  -0.0544   0.1542   1.0000
  11.000   1.3551   0.02703   0.01956  -0.0529   0.1415   1.0000
  11.250   1.3638   0.02823   0.02074  -0.0512   0.1282   1.0000
  11.500   1.3712   0.02958   0.02205  -0.0497   0.1148   1.0000
  11.750   1.3778   0.03104   0.02348  -0.0481   0.1019   1.0000
  12.000   1.3840   0.03258   0.02501  -0.0466   0.0908   1.0000
  12.250   1.3903   0.03417   0.02661  -0.0453   0.0811   1.0000
  12.500   1.3969   0.03577   0.02828  -0.0440   0.0729   1.0000
  12.750   1.4017   0.03758   0.03011  -0.0428   0.0652   1.0000
  13.000   1.4045   0.03962   0.03216  -0.0417   0.0571   1.0000
  13.250   1.4078   0.04167   0.03426  -0.0406   0.0488   1.0000
  13.500   1.4095   0.04394   0.03657  -0.0397   0.0412   1.0000
  13.750   1.4098   0.04644   0.03911  -0.0389   0.0346   1.0000
  14.000   1.4070   0.04935   0.04204  -0.0382   0.0275   1.0000
  14.500   1.3972   0.05604   0.04883  -0.0375   0.0174   1.0000
  14.750   1.3925   0.05960   0.05249  -0.0375   0.0148   1.0000
  15.000   1.3856   0.06358   0.05657  -0.0379   0.0130   1.0000
  15.250   1.3800   0.06758   0.06074  -0.0384   0.0116   1.0000
  15.500   1.3734   0.07187   0.06517  -0.0392   0.0108   1.0000
  15.750   1.3642   0.07671   0.07014  -0.0405   0.0100   1.0000
  16.000   1.3545   0.08185   0.07542  -0.0420   0.0095   1.0000
  16.250   1.3456   0.08705   0.08080  -0.0438   0.0092   1.0000
  16.500   1.3361   0.09253   0.08645  -0.0458   0.0090   1.0000
  16.750   1.3249   0.09849   0.09258  -0.0483   0.0087   1.0000
  17.000   1.3131   0.10470   0.09896  -0.0510   0.0085   1.0000
  17.250   1.3007   0.11118   0.10561  -0.0541   0.0083   1.0000
  17.500   1.2883   0.11779   0.11238  -0.0573   0.0082   1.0000
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