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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 100,000
Max Cl/Cd: 58.86 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3010-il-100000-n5.txt
Download as CSV file: xf-hq3010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3678   0.09135   0.08654  -0.0416   1.0000   0.0278
  -8.500  -0.3696   0.08832   0.08358  -0.0415   1.0000   0.0270
  -8.250  -0.3761   0.08510   0.08046  -0.0417   1.0000   0.0270
  -8.000  -0.3852   0.08234   0.07781  -0.0410   1.0000   0.0265
  -7.750  -0.3998   0.08011   0.07569  -0.0393   1.0000   0.0261
  -7.500  -0.4182   0.07807   0.07377  -0.0373   1.0000   0.0258
  -7.250  -0.4330   0.07509   0.07087  -0.0373   1.0000   0.0254
  -7.000  -0.4245   0.06843   0.06415  -0.0458   0.9943   0.0244
  -6.750  -0.4068   0.06051   0.05603  -0.0555   0.9860   0.0233
  -6.500  -0.3889   0.05266   0.04785  -0.0630   0.9776   0.0222
  -6.250  -0.3649   0.04489   0.03951  -0.0692   0.9715   0.0214
  -6.000  -0.3426   0.03941   0.03346  -0.0720   0.9643   0.0211
  -5.750  -0.3131   0.03514   0.02865  -0.0749   0.9599   0.0213
  -5.500  -0.2859   0.03188   0.02490  -0.0764   0.9544   0.0218
  -5.250  -0.2564   0.02933   0.02192  -0.0778   0.9493   0.0228
  -5.000  -0.2224   0.02741   0.01959  -0.0796   0.9459   0.0260
  -4.750  -0.1921   0.02532   0.01702  -0.0802   0.9411   0.0279
  -4.500  -0.1615   0.02349   0.01478  -0.0806   0.9362   0.0291
  -4.250  -0.1286   0.02163   0.01280  -0.0818   0.9329   0.0318
  -4.000  -0.0968   0.02049   0.01157  -0.0827   0.9288   0.0361
  -3.750  -0.0692   0.01959   0.01059  -0.0828   0.9228   0.0445
  -3.500  -0.0361   0.01887   0.00985  -0.0840   0.9189   0.0621
  -3.250  -0.0065   0.01828   0.00916  -0.0845   0.9136   0.0806
  -3.000   0.0225   0.01764   0.00855  -0.0850   0.9080   0.1000
  -2.750   0.0560   0.01694   0.00790  -0.0863   0.9042   0.1311
  -2.500   0.0813   0.01599   0.00749  -0.0865   0.8976   0.2626
  -2.250   0.1061   0.01502   0.00760  -0.0860   0.8923   0.5572
  -2.000   0.1335   0.01496   0.00765  -0.0853   0.8873   0.6437
  -1.750   0.1571   0.01499   0.00770  -0.0840   0.8801   0.6933
  -1.500   0.1827   0.01495   0.00775  -0.0824   0.8756   0.7537
  -1.250   0.2001   0.01497   0.00779  -0.0795   0.8670   0.7960
  -1.000   0.2299   0.01485   0.00757  -0.0794   0.8621   0.8178
  -0.750   0.2547   0.01481   0.00746  -0.0787   0.8539   0.8313
  -0.500   0.2856   0.01466   0.00723  -0.0790   0.8484   0.8449
  -0.250   0.3108   0.01459   0.00711  -0.0783   0.8399   0.8605
   0.000   0.3422   0.01441   0.00689  -0.0786   0.8341   0.8773
   0.250   0.3701   0.01434   0.00682  -0.0785   0.8254   0.8994
   0.500   0.4091   0.01416   0.00660  -0.0804   0.8199   0.9254
   0.750   0.4488   0.01409   0.00652  -0.0830   0.8112   0.9920
   1.000   0.4800   0.01407   0.00641  -0.0838   0.8042   1.0000
   1.250   0.5076   0.01408   0.00636  -0.0838   0.7937   1.0000
   1.500   0.5353   0.01406   0.00628  -0.0836   0.7821   1.0000
   1.750   0.5633   0.01404   0.00620  -0.0835   0.7704   1.0000
   2.000   0.5918   0.01403   0.00615  -0.0835   0.7597   1.0000
   2.250   0.6210   0.01401   0.00611  -0.0835   0.7495   1.0000
   2.500   0.6478   0.01407   0.00616  -0.0832   0.7369   1.0000
   2.750   0.6747   0.01412   0.00619  -0.0829   0.7234   1.0000
   3.250   0.7283   0.01420   0.00628  -0.0820   0.6918   1.0000
   3.500   0.7541   0.01429   0.00637  -0.0814   0.6732   1.0000
   3.750   0.7805   0.01437   0.00644  -0.0809   0.6542   1.0000
   4.000   0.8059   0.01449   0.00657  -0.0802   0.6333   1.0000
   4.250   0.8314   0.01463   0.00672  -0.0796   0.6102   1.0000
   4.500   0.8560   0.01482   0.00689  -0.0788   0.5834   1.0000
   4.750   0.8802   0.01505   0.00707  -0.0779   0.5532   1.0000
   5.000   0.9035   0.01535   0.00730  -0.0769   0.5193   1.0000
   5.250   0.9260   0.01574   0.00760  -0.0758   0.4835   1.0000
   5.500   0.9477   0.01621   0.00796  -0.0747   0.4470   1.0000
   5.750   0.9684   0.01678   0.00839  -0.0735   0.4117   1.0000
   6.000   0.9889   0.01738   0.00890  -0.0723   0.3780   1.0000
   6.250   1.0087   0.01803   0.00945  -0.0711   0.3459   1.0000
   6.500   1.0282   0.01872   0.01009  -0.0698   0.3162   1.0000
   6.750   1.0471   0.01945   0.01074  -0.0686   0.2884   1.0000
   7.000   1.0660   0.02019   0.01143  -0.0674   0.2624   1.0000
   7.250   1.0846   0.02094   0.01216  -0.0661   0.2378   1.0000
   7.500   1.1025   0.02172   0.01291  -0.0648   0.2147   1.0000
   7.750   1.1201   0.02252   0.01369  -0.0635   0.1922   1.0000
   8.000   1.1373   0.02335   0.01458  -0.0621   0.1721   1.0000
   8.250   1.1536   0.02424   0.01548  -0.0607   0.1518   1.0000
   8.500   1.1689   0.02518   0.01640  -0.0592   0.1288   1.0000
   8.750   1.1828   0.02622   0.01737  -0.0576   0.1070   1.0000
   9.000   1.1964   0.02727   0.01842  -0.0559   0.0890   1.0000
   9.250   1.2080   0.02839   0.01955  -0.0540   0.0750   1.0000
   9.500   1.2185   0.02961   0.02079  -0.0520   0.0620   1.0000
   9.750   1.2277   0.03097   0.02211  -0.0500   0.0489   1.0000
  10.000   1.2364   0.03241   0.02362  -0.0480   0.0391   1.0000
  10.250   1.2427   0.03406   0.02541  -0.0459   0.0300   1.0000
  10.500   1.2451   0.03608   0.02750  -0.0436   0.0242   1.0000
  10.750   1.2470   0.03817   0.02976  -0.0414   0.0201   1.0000
  11.000   1.2445   0.04068   0.03238  -0.0392   0.0179   1.0000
  11.250   1.2437   0.04313   0.03503  -0.0374   0.0166   1.0000
  11.500   1.2432   0.04565   0.03777  -0.0359   0.0151   1.0000
  11.750   1.2420   0.04833   0.04064  -0.0347   0.0141   1.0000
  12.000   1.2402   0.05117   0.04365  -0.0338   0.0131   1.0000
  12.250   1.2365   0.05431   0.04696  -0.0334   0.0123   1.0000
  12.500   1.2292   0.05807   0.05088  -0.0332   0.0118   1.0000
  12.750   1.2211   0.06212   0.05509  -0.0334   0.0114   1.0000
  13.000   1.2155   0.06612   0.05933  -0.0338   0.0111   1.0000
  13.250   1.2083   0.07053   0.06397  -0.0347   0.0107   1.0000
  13.500   1.1995   0.07538   0.06905  -0.0360   0.0106   1.0000
  13.750   1.1895   0.08070   0.07460  -0.0378   0.0104   1.0000
  14.000   1.1788   0.08644   0.08055  -0.0400   0.0103   1.0000
  14.250   1.1671   0.09269   0.08701  -0.0429   0.0103   1.0000
  14.500   1.1545   0.09948   0.09401  -0.0463   0.0103   1.0000
  14.750   1.1412   0.10674   0.10146  -0.0502   0.0103   1.0000
  15.000   1.1267   0.11465   0.10957  -0.0546   0.0103   1.0000
  15.250   1.1124   0.12289   0.11797  -0.0594   0.0104   1.0000
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