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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 500,000
Max Cl/Cd: 111.3 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3011-il-500000.txt
Download as CSV file: xf-hq3011-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2841   0.10028   0.09815  -0.0439   1.0000   0.0194
 -10.500  -0.2861   0.09616   0.09405  -0.0447   1.0000   0.0194
 -10.250  -0.2967   0.09023   0.08817  -0.0451   1.0000   0.0200
 -10.000  -0.2972   0.08748   0.08544  -0.0444   1.0000   0.0204
  -9.750  -0.2994   0.08588   0.08389  -0.0425   1.0000   0.0209
  -9.500  -0.3027   0.08288   0.08091  -0.0423   0.9992   0.0211
  -9.250  -0.2941   0.07846   0.07650  -0.0453   0.9970   0.0220
  -9.000  -0.2892   0.07295   0.07099  -0.0492   0.9943   0.0223
  -8.750  -0.2864   0.06730   0.06536  -0.0532   0.9907   0.0226
  -8.500  -0.2844   0.06105   0.05911  -0.0582   0.9869   0.0236
  -8.250  -0.2839   0.05365   0.05172  -0.0653   0.9835   0.0239
  -8.000  -0.2944   0.04313   0.04115  -0.0798   0.9749   0.0240
  -7.750  -0.2962   0.03494   0.03273  -0.0896   0.9657   0.0243
  -7.500  -0.3686   0.02569   0.02175  -0.0964   0.9582   0.0134
  -7.250  -0.3443   0.02342   0.01908  -0.0969   0.9522   0.0139
  -7.000  -0.3224   0.02119   0.01646  -0.0967   0.9449   0.0141
  -6.750  -0.3006   0.01846   0.01335  -0.0963   0.9388   0.0140
  -6.500  -0.2776   0.01693   0.01156  -0.0956   0.9316   0.0141
  -6.250  -0.2551   0.01470   0.00904  -0.0949   0.9259   0.0146
  -6.000  -0.2324   0.01356   0.00778  -0.0941   0.9187   0.0154
  -5.750  -0.2065   0.01297   0.00712  -0.0937   0.9133   0.0165
  -5.500  -0.1816   0.01240   0.00647  -0.0932   0.9065   0.0176
  -5.250  -0.1557   0.01191   0.00587  -0.0927   0.9007   0.0190
  -5.000  -0.1307   0.01128   0.00519  -0.0923   0.8946   0.0220
  -4.750  -0.1041   0.01101   0.00489  -0.0920   0.8884   0.0259
  -4.500  -0.0776   0.01060   0.00444  -0.0916   0.8831   0.0357
  -4.250  -0.0514   0.01028   0.00412  -0.0914   0.8763   0.0453
  -4.000  -0.0244   0.01001   0.00381  -0.0912   0.8709   0.0521
  -3.750   0.0026   0.00987   0.00364  -0.0910   0.8647   0.0587
  -3.500   0.0295   0.00959   0.00336  -0.0908   0.8587   0.0680
  -3.250   0.0566   0.00934   0.00309  -0.0907   0.8531   0.0799
  -3.000   0.0834   0.00903   0.00284  -0.0905   0.8463   0.1039
  -2.750   0.1094   0.00840   0.00256  -0.0905   0.8406   0.2088
  -2.500   0.1330   0.00744   0.00235  -0.0903   0.8329   0.4266
  -2.250   0.1595   0.00719   0.00231  -0.0900   0.8268   0.5264
  -2.000   0.1867   0.00712   0.00229  -0.0898   0.8194   0.5648
  -1.750   0.2144   0.00708   0.00224  -0.0896   0.8133   0.5903
  -1.500   0.2418   0.00705   0.00222  -0.0894   0.8066   0.6126
  -1.250   0.2695   0.00703   0.00219  -0.0892   0.8003   0.6328
  -1.000   0.2971   0.00701   0.00216  -0.0890   0.7934   0.6495
  -0.750   0.3245   0.00699   0.00212  -0.0888   0.7855   0.6673
  -0.500   0.3510   0.00694   0.00211  -0.0883   0.7761   0.6900
  -0.250   0.3782   0.00691   0.00207  -0.0880   0.7676   0.7069
   0.000   0.4053   0.00687   0.00205  -0.0877   0.7591   0.7214
   0.250   0.4327   0.00685   0.00204  -0.0875   0.7517   0.7346
   0.500   0.4600   0.00683   0.00204  -0.0873   0.7437   0.7473
   0.750   0.4871   0.00681   0.00205  -0.0871   0.7353   0.7616
   1.000   0.5140   0.00680   0.00207  -0.0868   0.7270   0.7795
   1.250   0.5402   0.00679   0.00211  -0.0863   0.7166   0.8009
   1.500   0.5662   0.00680   0.00216  -0.0858   0.7058   0.8258
   1.750   0.5918   0.00682   0.00220  -0.0851   0.6952   0.8506
   2.000   0.6171   0.00682   0.00222  -0.0844   0.6846   0.8740
   2.250   0.6416   0.00679   0.00223  -0.0836   0.6733   0.8985
   2.500   0.6667   0.00673   0.00224  -0.0827   0.6612   0.9303
   2.750   0.7071   0.00673   0.00226  -0.0854   0.6469   1.0000
   3.000   0.7340   0.00684   0.00232  -0.0853   0.6317   1.0000
   3.250   0.7604   0.00697   0.00239  -0.0851   0.6146   1.0000
   3.500   0.7865   0.00712   0.00247  -0.0848   0.5952   1.0000
   3.750   0.8121   0.00730   0.00258  -0.0844   0.5724   1.0000
   4.000   0.8370   0.00752   0.00270  -0.0839   0.5459   1.0000
   4.250   0.8613   0.00779   0.00285  -0.0833   0.5162   1.0000
   4.500   0.8846   0.00812   0.00305  -0.0825   0.4827   1.0000
   4.750   0.9079   0.00848   0.00327  -0.0818   0.4495   1.0000
   5.000   0.9307   0.00888   0.00353  -0.0810   0.4159   1.0000
   5.250   0.9531   0.00931   0.00380  -0.0801   0.3826   1.0000
   5.500   0.9756   0.00974   0.00411  -0.0793   0.3492   1.0000
   5.750   0.9978   0.01019   0.00442  -0.0785   0.3177   1.0000
   6.000   1.0199   0.01065   0.00475  -0.0777   0.2905   1.0000
   6.250   1.0420   0.01110   0.00509  -0.0769   0.2675   1.0000
   6.500   1.0648   0.01150   0.00543  -0.0761   0.2468   1.0000
   6.750   1.0867   0.01195   0.00579  -0.0753   0.2261   1.0000
   7.000   1.1082   0.01241   0.00615  -0.0744   0.2011   1.0000
   7.250   1.1291   0.01292   0.00654  -0.0735   0.1773   1.0000
   7.500   1.1496   0.01344   0.00696  -0.0724   0.1578   1.0000
   7.750   1.1705   0.01391   0.00738  -0.0715   0.1419   1.0000
   8.000   1.1912   0.01438   0.00782  -0.0705   0.1270   1.0000
   8.250   1.2111   0.01489   0.00829  -0.0694   0.1110   1.0000
   8.500   1.2295   0.01549   0.00880  -0.0680   0.0940   1.0000
   8.750   1.2462   0.01617   0.00938  -0.0665   0.0759   1.0000
   9.000   1.2622   0.01685   0.00998  -0.0648   0.0607   1.0000
   9.250   1.2768   0.01750   0.01058  -0.0629   0.0504   1.0000
   9.500   1.2909   0.01816   0.01124  -0.0608   0.0423   1.0000
   9.750   1.3037   0.01891   0.01194  -0.0587   0.0336   1.0000
  10.000   1.3169   0.01964   0.01267  -0.0567   0.0265   1.0000
  10.250   1.3263   0.02065   0.01362  -0.0542   0.0165   1.0000
  10.500   1.3359   0.02166   0.01463  -0.0519   0.0112   1.0000
  10.750   1.3445   0.02277   0.01577  -0.0495   0.0085   1.0000
  11.000   1.3548   0.02380   0.01688  -0.0475   0.0075   1.0000
  11.250   1.3652   0.02482   0.01800  -0.0456   0.0072   1.0000
  11.500   1.3734   0.02604   0.01933  -0.0436   0.0067   1.0000
  11.750   1.3819   0.02727   0.02066  -0.0418   0.0066   1.0000
  12.000   1.3836   0.02909   0.02260  -0.0395   0.0061   1.0000
  12.250   1.3878   0.03075   0.02438  -0.0376   0.0061   1.0000
  12.500   1.3864   0.03294   0.02671  -0.0356   0.0059   1.0000
  12.750   1.3883   0.03495   0.02884  -0.0340   0.0059   1.0000
  13.000   1.3897   0.03708   0.03110  -0.0326   0.0058   1.0000
  13.250   1.3879   0.03963   0.03379  -0.0314   0.0058   1.0000
  13.500   1.3855   0.04236   0.03665  -0.0304   0.0057   1.0000
  13.750   1.3848   0.04503   0.03944  -0.0297   0.0057   1.0000
  14.000   1.3824   0.04802   0.04257  -0.0293   0.0056   1.0000
  14.250   1.3791   0.05125   0.04592  -0.0291   0.0055   1.0000
  14.500   1.3751   0.05473   0.04954  -0.0293   0.0054   1.0000
  14.750   1.3692   0.05866   0.05361  -0.0297   0.0053   1.0000
  15.000   1.3645   0.06260   0.05770  -0.0305   0.0052   1.0000
  15.250   1.3575   0.06707   0.06231  -0.0316   0.0052   1.0000
  15.500   1.3496   0.07190   0.06729  -0.0331   0.0051   1.0000
  15.750   1.3400   0.07718   0.07272  -0.0350   0.0052   1.0000
  16.000   1.3325   0.08239   0.07807  -0.0371   0.0051   1.0000
  16.250   1.3216   0.08832   0.08415  -0.0396   0.0051   1.0000
  16.500   1.3115   0.09431   0.09028  -0.0423   0.0051   1.0000
  16.750   1.3018   0.10042   0.09654  -0.0452   0.0051   1.0000
  17.000   1.2908   0.10694   0.10320  -0.0485   0.0051   1.0000
  17.250   1.2791   0.11367   0.11008  -0.0519   0.0051   1.0000
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