HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 500,000 Max Cl/Cd: 90.57 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3512-il-500000-n5.txt Download as CSV file: xf-hq3512-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5153 0.03938 0.03679 -0.0988 0.9661 0.0070
-10.000 -0.5244 0.03097 0.02771 -0.1066 0.9474 0.0070
-9.750 -0.5158 0.02738 0.02367 -0.1078 0.9350 0.0071
-9.500 -0.5011 0.02500 0.02095 -0.1081 0.9252 0.0072
-9.250 -0.4842 0.02304 0.01868 -0.1080 0.9165 0.0074
-9.000 -0.4657 0.02146 0.01682 -0.1076 0.9083 0.0075
-8.750 -0.4453 0.02005 0.01515 -0.1072 0.9012 0.0077
-8.500 -0.4239 0.01894 0.01383 -0.1068 0.8939 0.0078
-8.250 -0.4014 0.01788 0.01256 -0.1064 0.8874 0.0079
-8.000 -0.3777 0.01710 0.01162 -0.1061 0.8809 0.0081
-7.750 -0.3535 0.01639 0.01073 -0.1058 0.8745 0.0083
-7.500 -0.3309 0.01529 0.00948 -0.1054 0.8686 0.0087
-7.250 -0.3066 0.01456 0.00864 -0.1051 0.8622 0.0089
-7.000 -0.2815 0.01394 0.00790 -0.1048 0.8568 0.0091
-6.750 -0.2561 0.01338 0.00727 -0.1045 0.8507 0.0094
-6.500 -0.2304 0.01289 0.00667 -0.1043 0.8449 0.0097
-6.250 -0.2043 0.01244 0.00612 -0.1041 0.8394 0.0101
-6.000 -0.1780 0.01203 0.00563 -0.1039 0.8334 0.0105
-5.750 -0.1514 0.01167 0.00517 -0.1038 0.8281 0.0110
-5.500 -0.1247 0.01134 0.00477 -0.1036 0.8221 0.0115
-5.250 -0.0980 0.01098 0.00435 -0.1035 0.8163 0.0127
-5.000 -0.0710 0.01069 0.00401 -0.1034 0.8110 0.0144
-4.750 -0.0439 0.01040 0.00373 -0.1033 0.8050 0.0189
-4.500 -0.0166 0.01020 0.00352 -0.1033 0.7995 0.0270
-4.250 0.0108 0.01000 0.00333 -0.1032 0.7938 0.0331
-4.000 0.0384 0.00987 0.00314 -0.1032 0.7880 0.0369
-3.750 0.0659 0.00969 0.00296 -0.1032 0.7825 0.0427
-3.500 0.0937 0.00956 0.00279 -0.1032 0.7765 0.0471
-3.250 0.1213 0.00942 0.00261 -0.1031 0.7709 0.0522
-3.000 0.1491 0.00928 0.00246 -0.1032 0.7649 0.0597
-2.750 0.1766 0.00913 0.00232 -0.1031 0.7586 0.0729
-2.500 0.2040 0.00895 0.00219 -0.1031 0.7518 0.0965
-2.250 0.2311 0.00872 0.00204 -0.1031 0.7431 0.1356
-2.000 0.2579 0.00842 0.00192 -0.1031 0.7335 0.2051
-1.750 0.2844 0.00806 0.00178 -0.1031 0.7242 0.2935
-1.500 0.3106 0.00763 0.00169 -0.1031 0.7153 0.4203
-1.250 0.3375 0.00744 0.00167 -0.1030 0.7069 0.4908
-1.000 0.3645 0.00736 0.00168 -0.1028 0.6987 0.5413
-0.750 0.3917 0.00731 0.00173 -0.1026 0.6911 0.5895
-0.500 0.4185 0.00731 0.00179 -0.1023 0.6827 0.6296
-0.250 0.4459 0.00734 0.00182 -0.1021 0.6735 0.6520
0.000 0.4733 0.00738 0.00184 -0.1020 0.6650 0.6634
0.250 0.5006 0.00743 0.00185 -0.1018 0.6554 0.6715
0.500 0.5281 0.00748 0.00187 -0.1017 0.6450 0.6780
0.750 0.5553 0.00754 0.00189 -0.1015 0.6336 0.6839
1.000 0.5824 0.00761 0.00192 -0.1013 0.6225 0.6904
1.250 0.6095 0.00768 0.00196 -0.1012 0.6114 0.6967
1.500 0.6365 0.00775 0.00201 -0.1010 0.5996 0.7029
1.750 0.6631 0.00785 0.00207 -0.1008 0.5851 0.7097
2.000 0.6891 0.00797 0.00214 -0.1004 0.5681 0.7160
2.250 0.7149 0.00811 0.00222 -0.1000 0.5496 0.7232
2.500 0.7404 0.00826 0.00232 -0.0995 0.5296 0.7301
2.750 0.7650 0.00847 0.00244 -0.0990 0.5058 0.7376
3.000 0.7889 0.00871 0.00259 -0.0983 0.4783 0.7449
3.250 0.8125 0.00899 0.00276 -0.0975 0.4501 0.7530
3.500 0.8359 0.00927 0.00296 -0.0968 0.4234 0.7608
4.000 0.8818 0.00990 0.00339 -0.0952 0.3676 0.7783
4.250 0.9043 0.01023 0.00363 -0.0943 0.3395 0.7877
4.500 0.9264 0.01059 0.00389 -0.0934 0.3119 0.7984
4.750 0.9487 0.01088 0.00414 -0.0925 0.2930 0.8101
5.000 0.9712 0.01115 0.00439 -0.0916 0.2787 0.8240
5.250 0.9939 0.01136 0.00464 -0.0907 0.2684 0.8419
5.500 1.0150 0.01153 0.00488 -0.0895 0.2598 0.8697
5.750 1.0446 0.01164 0.00512 -0.0901 0.2509 1.0000
6.000 1.0683 0.01192 0.00539 -0.0895 0.2438 1.0000
6.250 1.0915 0.01222 0.00567 -0.0889 0.2349 1.0000
6.500 1.1148 0.01250 0.00595 -0.0882 0.2266 1.0000
6.750 1.1369 0.01284 0.00625 -0.0874 0.2172 1.0000
7.000 1.1596 0.01313 0.00653 -0.0866 0.2076 1.0000
7.250 1.1816 0.01344 0.00685 -0.0858 0.1983 1.0000
7.500 1.2024 0.01381 0.00718 -0.0848 0.1863 1.0000
7.750 1.2223 0.01421 0.00753 -0.0836 0.1722 1.0000
8.000 1.2402 0.01463 0.00790 -0.0821 0.1573 1.0000
8.250 1.2566 0.01512 0.00833 -0.0803 0.1421 1.0000
8.500 1.2698 0.01578 0.00888 -0.0781 0.1220 1.0000
8.750 1.2838 0.01642 0.00944 -0.0760 0.1054 1.0000
9.000 1.2949 0.01724 0.01014 -0.0737 0.0850 1.0000
9.250 1.3070 0.01804 0.01084 -0.0715 0.0693 1.0000
9.500 1.3192 0.01883 0.01158 -0.0695 0.0566 1.0000
9.750 1.3299 0.01975 0.01242 -0.0673 0.0425 1.0000
10.000 1.3381 0.02085 0.01343 -0.0649 0.0278 1.0000
10.250 1.3449 0.02208 0.01461 -0.0625 0.0154 1.0000
10.500 1.3545 0.02315 0.01568 -0.0605 0.0094 1.0000
10.750 1.3645 0.02422 0.01678 -0.0586 0.0062 1.0000
11.000 1.3747 0.02530 0.01790 -0.0569 0.0051 1.0000
11.250 1.3857 0.02635 0.01902 -0.0553 0.0047 1.0000
11.500 1.3949 0.02756 0.02030 -0.0537 0.0043 1.0000
11.750 1.4045 0.02878 0.02160 -0.0521 0.0040 1.0000
12.000 1.4130 0.03010 0.02302 -0.0506 0.0038 1.0000
12.250 1.4217 0.03146 0.02449 -0.0492 0.0038 1.0000
12.500 1.4288 0.03298 0.02612 -0.0479 0.0036 1.0000
12.750 1.4351 0.03461 0.02785 -0.0466 0.0035 1.0000
13.000 1.4406 0.03637 0.02972 -0.0454 0.0035 1.0000
13.250 1.4441 0.03837 0.03183 -0.0442 0.0033 1.0000
13.500 1.4477 0.04042 0.03399 -0.0432 0.0033 1.0000
13.750 1.4492 0.04277 0.03645 -0.0423 0.0032 1.0000
14.000 1.4504 0.04523 0.03902 -0.0416 0.0031 1.0000
14.250 1.4494 0.04803 0.04194 -0.0411 0.0030 1.0000
14.500 1.4460 0.05124 0.04527 -0.0407 0.0029 1.0000
14.750 1.4421 0.05466 0.04882 -0.0407 0.0028 1.0000
15.000 1.4355 0.05858 0.05288 -0.0409 0.0027 1.0000
15.250 1.4293 0.06266 0.05709 -0.0415 0.0027 1.0000
15.500 1.4216 0.06715 0.06173 -0.0424 0.0027 1.0000
15.750 1.4106 0.07234 0.06707 -0.0438 0.0026 1.0000
16.000 1.3972 0.07819 0.07307 -0.0457 0.0026 1.0000
16.250 1.3848 0.08413 0.07916 -0.0478 0.0026 1.0000
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