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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 500,000
Max Cl/Cd: 106.04 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq358-il-500000-n5.txt
Download as CSV file: xf-hq358-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3375   0.10140   0.09914  -0.0336   1.0000   0.0052
  -8.750  -0.3358   0.09876   0.09654  -0.0337   1.0000   0.0052
  -8.500  -0.3363   0.09611   0.09393  -0.0334   1.0000   0.0052
  -8.250  -0.3285   0.09236   0.09019  -0.0358   0.9984   0.0052
  -8.000  -0.3149   0.08832   0.08613  -0.0397   0.9938   0.0052
  -7.750  -0.3011   0.08429   0.08211  -0.0439   0.9889   0.0052
  -7.500  -0.2869   0.07999   0.07782  -0.0486   0.9834   0.0052
  -7.250  -0.2717   0.07551   0.07334  -0.0540   0.9769   0.0052
  -7.000  -0.2509   0.07062   0.06845  -0.0613   0.9716   0.0052
  -6.750  -0.2280   0.06534   0.06316  -0.0698   0.9647   0.0052
  -6.250  -0.1818   0.05291   0.05060  -0.0888   0.9486   0.0047
  -6.000  -0.1609   0.04800   0.04557  -0.0945   0.9388   0.0044
  -5.750  -0.1384   0.04305   0.04046  -0.0992   0.9300   0.0042
  -5.500  -0.1150   0.03831   0.03551  -0.1027   0.9219   0.0040
  -5.250  -0.0916   0.03383   0.03078  -0.1049   0.9137   0.0038
  -5.000  -0.0660   0.02931   0.02593  -0.1065   0.9072   0.0037
  -4.750  -0.0401   0.02495   0.02121  -0.1073   0.9000   0.0038
  -4.500  -0.0126   0.02057   0.01637  -0.1076   0.8944   0.0041
  -4.250   0.0148   0.01695   0.01229  -0.1074   0.8880   0.0046
  -4.000   0.0425   0.01560   0.01065  -0.1072   0.8825   0.0052
  -3.750   0.0691   0.01367   0.00838  -0.1073   0.8769   0.0065
  -3.500   0.0963   0.01266   0.00715  -0.1072   0.8710   0.0071
  -3.250   0.1238   0.01138   0.00563  -0.1069   0.8657   0.0072
  -3.000   0.1510   0.01045   0.00455  -0.1066   0.8595   0.0074
  -2.750   0.1785   0.00974   0.00370  -0.1064   0.8541   0.0081
  -2.500   0.2060   0.00923   0.00309  -0.1063   0.8476   0.0091
  -2.250   0.2337   0.00893   0.00271  -0.1062   0.8415   0.0104
  -2.000   0.2613   0.00857   0.00222  -0.1061   0.8333   0.0110
  -1.750   0.2888   0.00836   0.00186  -0.1059   0.8227   0.0113
  -1.500   0.3160   0.00823   0.00160  -0.1056   0.8099   0.0122
  -1.250   0.3434   0.00813   0.00143  -0.1054   0.7978   0.0153
  -1.000   0.3708   0.00800   0.00131  -0.1053   0.7867   0.0373
  -0.750   0.3982   0.00784   0.00120  -0.1052   0.7756   0.0789
  -0.500   0.4252   0.00719   0.00112  -0.1056   0.7645   0.3060
  -0.250   0.4507   0.00651   0.00121  -0.1056   0.7524   0.5886
   0.000   0.4753   0.00631   0.00133  -0.1048   0.7383   0.7176
   0.250   0.5013   0.00630   0.00136  -0.1043   0.7244   0.7541
   0.500   0.5282   0.00634   0.00135  -0.1040   0.7107   0.7665
   0.750   0.5549   0.00639   0.00136  -0.1037   0.6964   0.7789
   1.000   0.5814   0.00644   0.00138  -0.1034   0.6822   0.7924
   1.250   0.6076   0.00650   0.00141  -0.1030   0.6661   0.8075
   1.750   0.6584   0.00660   0.00150  -0.1019   0.6283   0.8497
   2.000   0.6815   0.00657   0.00154  -0.1008   0.6061   0.9031
   2.250   0.7126   0.00672   0.00159  -0.1016   0.5753   1.0000
   2.500   0.7379   0.00698   0.00171  -0.1011   0.5423   1.0000
   2.750   0.7627   0.00730   0.00187  -0.1007   0.5036   1.0000
   3.000   0.7869   0.00768   0.00205  -0.1001   0.4612   1.0000
   3.250   0.8110   0.00808   0.00226  -0.0996   0.4193   1.0000
   3.500   0.8351   0.00850   0.00249  -0.0991   0.3778   1.0000
   3.750   0.8597   0.00887   0.00272  -0.0986   0.3423   1.0000
   4.250   0.9087   0.00963   0.00326  -0.0978   0.2836   1.0000
   4.500   0.9314   0.01020   0.00359  -0.0971   0.2398   1.0000
   4.750   0.9555   0.01062   0.00387  -0.0966   0.2091   1.0000
   5.000   0.9800   0.01099   0.00414  -0.0962   0.1854   1.0000
   5.250   1.0031   0.01151   0.00453  -0.0956   0.1482   1.0000
   5.500   1.0241   0.01228   0.00503  -0.0947   0.0982   1.0000
   5.750   1.0393   0.01377   0.00598  -0.0930   0.0148   1.0000
   6.000   1.0619   0.01438   0.00658  -0.0922   0.0044   1.0000
   6.250   1.0855   0.01485   0.00713  -0.0915   0.0037   1.0000
   6.500   1.1085   0.01538   0.00776  -0.0907   0.0033   1.0000
   6.750   1.1310   0.01597   0.00846  -0.0899   0.0030   1.0000
   7.000   1.1527   0.01664   0.00928  -0.0889   0.0029   1.0000
   7.250   1.1735   0.01741   0.01017  -0.0878   0.0028   1.0000
   7.500   1.1931   0.01828   0.01117  -0.0865   0.0027   1.0000
   7.750   1.2114   0.01926   0.01228  -0.0850   0.0027   1.0000
   8.000   1.2281   0.02037   0.01351  -0.0833   0.0026   1.0000
   8.250   1.2420   0.02173   0.01500  -0.0813   0.0023   1.0000
   8.500   1.2496   0.02385   0.01731  -0.0784   0.0019   1.0000
   8.750   1.2682   0.02457   0.01813  -0.0771   0.0018   1.0000
   9.000   1.2819   0.02586   0.01957  -0.0752   0.0017   1.0000
   9.250   1.2935   0.02724   0.02110  -0.0729   0.0016   1.0000
   9.500   1.3029   0.02874   0.02278  -0.0703   0.0016   1.0000
   9.750   1.3110   0.03036   0.02457  -0.0677   0.0015   1.0000
  10.000   1.3176   0.03211   0.02656  -0.0650   0.0014   1.0000
  10.250   1.3223   0.03402   0.02868  -0.0623   0.0013   1.0000
  10.500   1.3247   0.03617   0.03104  -0.0596   0.0012   1.0000
  10.750   1.3255   0.03841   0.03349  -0.0570   0.0011   1.0000
  11.000   1.3232   0.04105   0.03636  -0.0545   0.0011   1.0000
  11.250   1.3192   0.04382   0.03935  -0.0523   0.0011   1.0000
  11.500   1.3126   0.04699   0.04275  -0.0504   0.0010   1.0000
  11.750   1.3041   0.05052   0.04650  -0.0490   0.0010   1.0000
  12.000   1.2934   0.05451   0.05071  -0.0481   0.0010   1.0000
  12.250   1.2806   0.05904   0.05546  -0.0480   0.0010   1.0000
  12.500   1.2668   0.06407   0.06071  -0.0487   0.0010   1.0000
  12.750   1.2508   0.06991   0.06675  -0.0504   0.0010   1.0000
  13.000   1.2342   0.07641   0.07345  -0.0530   0.0010   1.0000
  13.250   1.2167   0.08376   0.08099  -0.0568   0.0010   1.0000
  13.500   1.1988   0.09206   0.08947  -0.0616   0.0010   1.0000
  13.750   1.1805   0.10130   0.09889  -0.0672   0.0010   1.0000
  14.000   1.1629   0.11111   0.10885  -0.0734   0.0010   1.0000
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