HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 0/9 AIRFOIL (hq09-il) Reynolds number: 50,000 Max Cl/Cd: 26 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq09-il-50000-n5.txt Download as CSV file: xf-hq09-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6749 0.09497 0.08827 -0.0004 1.0000 0.0413
-9.500 -0.6810 0.08836 0.08171 -0.0050 1.0000 0.0410
-9.250 -0.6895 0.08239 0.07576 -0.0092 1.0000 0.0403
-9.000 -0.7021 0.07702 0.07039 -0.0126 1.0000 0.0397
-8.750 -0.7163 0.07230 0.06561 -0.0142 1.0000 0.0394
-8.500 -0.7263 0.06757 0.06088 -0.0155 1.0000 0.0392
-8.250 -0.7327 0.06289 0.05597 -0.0161 1.0000 0.0393
-8.000 -0.7355 0.05816 0.05090 -0.0163 1.0000 0.0399
-7.750 -0.7335 0.05349 0.04569 -0.0160 1.0000 0.0403
-7.500 -0.7272 0.04894 0.04061 -0.0153 1.0000 0.0410
-7.250 -0.7167 0.04454 0.03558 -0.0143 1.0000 0.0422
-7.000 -0.7022 0.04066 0.03108 -0.0133 1.0000 0.0445
-6.750 -0.6848 0.03847 0.02879 -0.0128 1.0000 0.0512
-6.500 -0.6637 0.03536 0.02504 -0.0118 1.0000 0.0546
-6.250 -0.6397 0.03247 0.02170 -0.0108 1.0000 0.0570
-6.000 -0.6157 0.03019 0.01930 -0.0101 1.0000 0.0608
-5.750 -0.5906 0.02832 0.01717 -0.0091 1.0000 0.0661
-5.500 -0.5677 0.02684 0.01561 -0.0083 1.0000 0.0773
-5.250 -0.5447 0.02530 0.01397 -0.0073 1.0000 0.0873
-5.000 -0.5228 0.02379 0.01237 -0.0061 1.0000 0.0998
-4.750 -0.5024 0.02224 0.01082 -0.0051 1.0000 0.1259
-4.500 -0.4836 0.02051 0.00963 -0.0043 1.0000 0.2004
-4.250 -0.4698 0.01858 0.00870 -0.0027 1.0000 0.3515
-4.000 -0.4568 0.01757 0.00860 0.0009 1.0000 0.5281
-3.750 -0.4405 0.01738 0.00867 0.0046 1.0000 0.6410
-3.500 -0.4240 0.01743 0.00878 0.0086 1.0000 0.7183
-3.250 -0.4055 0.01752 0.00883 0.0123 1.0000 0.7732
-3.000 -0.3834 0.01746 0.00859 0.0146 1.0000 0.8076
-2.750 -0.3588 0.01731 0.00815 0.0158 1.0000 0.8331
-2.500 -0.3297 0.01718 0.00784 0.0161 1.0000 0.8557
-2.250 -0.2957 0.01713 0.00760 0.0157 1.0000 0.8824
-2.000 -0.2518 0.01716 0.00742 0.0134 1.0000 0.9121
-1.750 -0.2003 0.01709 0.00714 0.0090 1.0000 0.9345
-1.500 -0.1564 0.01688 0.00670 0.0054 1.0000 0.9489
-1.250 -0.1137 0.01665 0.00635 0.0018 1.0000 0.9626
-1.000 -0.0714 0.01641 0.00602 -0.0019 1.0000 0.9765
-0.750 -0.0290 0.01616 0.00571 -0.0057 1.0000 0.9910
-0.500 -0.0013 0.01597 0.00552 -0.0070 1.0000 1.0000
-0.250 0.0013 0.01587 0.00546 -0.0038 1.0000 1.0000
0.000 0.0000 0.01583 0.00545 0.0000 1.0000 1.0000
0.250 -0.0013 0.01587 0.00546 0.0038 1.0000 1.0000
0.500 0.0013 0.01597 0.00552 0.0070 1.0000 1.0000
0.750 0.0290 0.01616 0.00571 0.0057 0.9910 1.0000
1.000 0.0714 0.01641 0.00602 0.0019 0.9765 1.0000
1.250 0.1137 0.01665 0.00635 -0.0018 0.9626 1.0000
1.500 0.1563 0.01688 0.00670 -0.0054 0.9490 1.0000
1.750 0.2003 0.01709 0.00713 -0.0090 0.9345 1.0000
2.000 0.2519 0.01715 0.00742 -0.0134 0.9121 1.0000
2.250 0.2956 0.01713 0.00760 -0.0157 0.8825 1.0000
2.500 0.3296 0.01718 0.00784 -0.0161 0.8558 1.0000
2.750 0.3587 0.01730 0.00815 -0.0158 0.8332 1.0000
3.000 0.3833 0.01746 0.00859 -0.0145 0.8077 1.0000
3.250 0.4054 0.01752 0.00883 -0.0123 0.7733 1.0000
3.500 0.4239 0.01743 0.00878 -0.0086 0.7184 1.0000
3.750 0.4404 0.01738 0.00867 -0.0046 0.6409 1.0000
4.000 0.4568 0.01757 0.00861 -0.0009 0.5287 1.0000
4.250 0.4697 0.01858 0.00870 0.0027 0.3511 1.0000
4.500 0.4835 0.02051 0.00963 0.0043 0.2003 1.0000
4.750 0.5024 0.02225 0.01081 0.0051 0.1255 1.0000
5.000 0.5228 0.02379 0.01237 0.0061 0.0998 1.0000
5.250 0.5447 0.02530 0.01396 0.0073 0.0875 1.0000
5.500 0.5677 0.02683 0.01560 0.0083 0.0771 1.0000
5.750 0.5906 0.02832 0.01717 0.0091 0.0661 1.0000
6.000 0.6157 0.03019 0.01930 0.0100 0.0608 1.0000
6.250 0.6398 0.03249 0.02171 0.0108 0.0570 1.0000
6.500 0.6638 0.03536 0.02505 0.0118 0.0546 1.0000
6.750 0.6849 0.03848 0.02880 0.0128 0.0511 1.0000
7.000 0.7024 0.04066 0.03109 0.0133 0.0445 1.0000
7.250 0.7167 0.04458 0.03563 0.0143 0.0421 1.0000
7.500 0.7274 0.04894 0.04062 0.0153 0.0410 1.0000
7.750 0.7337 0.05349 0.04568 0.0159 0.0403 1.0000
8.000 0.7357 0.05817 0.05092 0.0162 0.0399 1.0000
8.250 0.7333 0.06287 0.05594 0.0161 0.0395 1.0000
8.500 0.7261 0.06765 0.06096 0.0154 0.0390 1.0000
8.750 0.7163 0.07237 0.06568 0.0141 0.0393 1.0000
9.000 0.7022 0.07711 0.07047 0.0124 0.0397 1.0000
9.250 0.6903 0.08238 0.07575 0.0092 0.0404 1.0000
9.500 0.6810 0.08857 0.08192 0.0047 0.0410 1.0000
9.750 0.6756 0.09497 0.08827 0.0003 0.0414 1.0000
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Polar data table (+)
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