HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 AIRFOIL (hq259-il) Reynolds number: 50,000 Max Cl/Cd: 38.18 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259-il-50000.txt Download as CSV file: xf-hq259-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4114 0.10941 0.10264 -0.0216 1.0000 0.2017
-8.750 -0.4177 0.10768 0.10102 -0.0225 1.0000 0.2119
-8.500 -0.4143 0.10455 0.09796 -0.0221 1.0000 0.2256
-8.250 -0.4097 0.10142 0.09489 -0.0214 1.0000 0.2392
-8.000 -0.4127 0.09902 0.09260 -0.0209 1.0000 0.2535
-7.750 -0.3958 0.09461 0.08821 -0.0189 1.0000 0.2716
-7.500 -0.3900 0.09172 0.08538 -0.0175 1.0000 0.2885
-7.250 -0.3950 0.08964 0.08342 -0.0161 1.0000 0.3068
-7.000 -0.4087 0.08828 0.08222 -0.0141 1.0000 0.3224
-6.750 -0.3918 0.08446 0.07843 -0.0116 1.0000 0.3479
-6.500 -0.3823 0.08141 0.07538 -0.0091 1.0000 0.3715
-6.250 -0.3833 0.07925 0.07333 -0.0060 1.0000 0.3954
-6.000 -0.3754 0.07650 0.07065 -0.0028 1.0000 0.4258
-5.750 -0.3735 0.07426 0.06850 0.0009 1.0000 0.4562
-5.500 -0.3789 0.07275 0.06711 0.0055 1.0000 0.4864
-4.750 -0.4011 0.04923 0.04253 -0.0426 1.0000 0.1727
-4.500 -0.3693 0.04331 0.03566 -0.0457 1.0000 0.1288
-4.250 -0.3435 0.03927 0.03094 -0.0463 1.0000 0.1153
-4.000 -0.3200 0.03589 0.02720 -0.0462 1.0000 0.1107
-3.750 -0.2946 0.03316 0.02386 -0.0460 1.0000 0.1112
-3.500 -0.2680 0.03113 0.02110 -0.0456 1.0000 0.1166
-3.250 -0.2433 0.02860 0.01848 -0.0449 1.0000 0.1221
-3.000 -0.2169 0.02673 0.01622 -0.0440 1.0000 0.1320
-2.750 -0.1927 0.02511 0.01457 -0.0430 1.0000 0.1564
-2.500 -0.1697 0.02351 0.01313 -0.0417 1.0000 0.1918
-2.250 -0.1431 0.02174 0.01163 -0.0411 1.0000 0.2512
-2.000 -0.1428 0.01900 0.01177 -0.0328 1.0000 0.7637
-1.750 -0.1233 0.01828 0.01099 -0.0280 1.0000 1.0000
-1.500 -0.0997 0.01839 0.01049 -0.0286 1.0000 1.0000
-1.250 -0.0760 0.01858 0.01022 -0.0292 1.0000 1.0000
-1.000 -0.0525 0.01882 0.01007 -0.0296 1.0000 1.0000
-0.750 -0.0293 0.01911 0.01002 -0.0300 1.0000 1.0000
-0.500 -0.0066 0.01944 0.01006 -0.0303 1.0000 1.0000
-0.250 0.0157 0.01982 0.01014 -0.0305 1.0000 1.0000
0.000 0.0376 0.02023 0.01032 -0.0306 1.0000 1.0000
0.250 0.0590 0.02069 0.01059 -0.0307 1.0000 1.0000
0.500 0.0802 0.02119 0.01091 -0.0308 1.0000 1.0000
0.750 0.1009 0.02173 0.01128 -0.0309 1.0000 1.0000
1.000 0.1212 0.02232 0.01174 -0.0310 1.0000 1.0000
1.250 0.1412 0.02296 0.01227 -0.0311 1.0000 1.0000
1.500 0.1607 0.02364 0.01287 -0.0312 1.0000 1.0000
1.750 0.1798 0.02438 0.01354 -0.0313 1.0000 1.0000
2.000 0.1985 0.02518 0.01430 -0.0314 1.0000 1.0000
2.250 0.2440 0.02660 0.01569 -0.0367 0.9860 1.0000
2.500 0.2989 0.02813 0.01723 -0.0434 0.9664 1.0000
2.750 0.3502 0.02935 0.01850 -0.0490 0.9445 1.0000
3.000 0.3988 0.03038 0.01963 -0.0537 0.9221 1.0000
3.250 0.4544 0.03131 0.02068 -0.0592 0.9006 1.0000
3.500 0.4951 0.03196 0.02147 -0.0619 0.8768 1.0000
3.750 0.5400 0.03246 0.02220 -0.0648 0.8526 1.0000
4.000 0.5890 0.03267 0.02263 -0.0678 0.8278 1.0000
4.250 0.6423 0.03241 0.02265 -0.0706 0.8021 1.0000
4.500 0.6987 0.03159 0.02223 -0.0730 0.7752 1.0000
4.750 0.7480 0.03044 0.02141 -0.0734 0.7467 1.0000
5.000 0.7952 0.02892 0.02022 -0.0728 0.7155 1.0000
5.250 0.8419 0.02705 0.01870 -0.0714 0.6805 1.0000
5.500 0.8776 0.02573 0.01755 -0.0688 0.6371 1.0000
5.750 0.9110 0.02471 0.01652 -0.0661 0.5873 1.0000
6.000 0.9363 0.02461 0.01628 -0.0633 0.5324 1.0000
6.250 0.9594 0.02513 0.01657 -0.0607 0.4781 1.0000
6.500 0.9799 0.02618 0.01745 -0.0585 0.4275 1.0000
6.750 1.0019 0.02745 0.01856 -0.0567 0.3824 1.0000
7.000 1.0228 0.02895 0.01996 -0.0550 0.3415 1.0000
7.250 1.0423 0.03065 0.02168 -0.0533 0.3039 1.0000
7.500 1.0606 0.03245 0.02347 -0.0514 0.2664 1.0000
7.750 1.0750 0.03428 0.02523 -0.0491 0.2244 1.0000
8.000 1.0769 0.03551 0.02618 -0.0454 0.1725 1.0000
8.250 1.0764 0.03750 0.02772 -0.0418 0.1236 1.0000
8.500 1.0863 0.04037 0.03059 -0.0393 0.0946 1.0000
8.750 1.1075 0.04419 0.03462 -0.0379 0.0823 1.0000
9.000 1.1270 0.04780 0.03840 -0.0368 0.0752 1.0000
9.250 1.1368 0.05197 0.04308 -0.0348 0.0715 1.0000
9.500 1.1398 0.05595 0.04765 -0.0325 0.0689 1.0000
9.750 1.1400 0.05990 0.05213 -0.0303 0.0667 1.0000
10.000 1.1371 0.06388 0.05646 -0.0282 0.0653 1.0000
10.250 1.1276 0.06809 0.06100 -0.0261 0.0649 1.0000
10.500 1.1053 0.07247 0.06575 -0.0236 0.0660 1.0000
10.750 1.0804 0.07714 0.07068 -0.0222 0.0674 1.0000
11.000 1.0555 0.08243 0.07616 -0.0225 0.0688 1.0000
11.250 1.0337 0.08826 0.08204 -0.0241 0.0705 1.0000
11.500 1.0132 0.09466 0.08853 -0.0268 0.0717 1.0000
11.750 0.9990 0.10120 0.09510 -0.0296 0.0728 1.0000
12.000 0.9854 0.10824 0.10218 -0.0330 0.0735 1.0000
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Polar data table (+)
Polar graphs
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