HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 500,000 Max Cl/Cd: 113.58 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3010-il-500000.txt Download as CSV file: xf-hq3010-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.4372 0.15884 0.15632 -0.0164 1.0000 0.0101
-13.750 -0.4311 0.15554 0.15302 -0.0176 1.0000 0.0103
-8.000 -0.3741 0.07653 0.07452 -0.0460 0.9961 0.0190
-7.750 -0.3560 0.06832 0.06631 -0.0595 0.9880 0.0191
-7.500 -0.3319 0.05922 0.05704 -0.0745 0.9829 0.0192
-7.250 -0.3144 0.05267 0.05028 -0.0821 0.9759 0.0192
-6.250 -0.2438 0.02280 0.01849 -0.0975 0.9501 0.0134
-6.000 -0.2194 0.02015 0.01546 -0.0975 0.9440 0.0133
-5.750 -0.1959 0.01750 0.01241 -0.0972 0.9380 0.0133
-5.500 -0.1724 0.01530 0.00988 -0.0965 0.9314 0.0135
-5.250 -0.1473 0.01383 0.00825 -0.0962 0.9262 0.0147
-5.000 -0.1221 0.01321 0.00755 -0.0957 0.9194 0.0157
-4.750 -0.0963 0.01224 0.00643 -0.0952 0.9141 0.0161
-4.500 -0.0711 0.01150 0.00560 -0.0946 0.9075 0.0170
-4.250 -0.0449 0.01091 0.00491 -0.0941 0.9017 0.0184
-4.000 -0.0192 0.01023 0.00412 -0.0937 0.8957 0.0212
-3.750 0.0076 0.00991 0.00378 -0.0933 0.8894 0.0274
-3.500 0.0345 0.00952 0.00341 -0.0931 0.8839 0.0466
-3.250 0.0613 0.00931 0.00317 -0.0929 0.8771 0.0558
-3.000 0.0888 0.00914 0.00295 -0.0927 0.8717 0.0654
-2.750 0.1154 0.00884 0.00273 -0.0926 0.8646 0.0873
-2.500 0.1416 0.00823 0.00245 -0.0925 0.8584 0.1888
-2.250 0.1653 0.00715 0.00226 -0.0924 0.8506 0.4606
-2.000 0.1916 0.00689 0.00220 -0.0921 0.8440 0.5553
-1.750 0.2184 0.00680 0.00218 -0.0917 0.8362 0.5992
-1.500 0.2460 0.00676 0.00212 -0.0915 0.8300 0.6281
-1.250 0.2732 0.00672 0.00211 -0.0912 0.8226 0.6516
-1.000 0.3005 0.00670 0.00209 -0.0909 0.8163 0.6773
-0.750 0.3274 0.00669 0.00208 -0.0905 0.8078 0.6995
-0.500 0.3539 0.00667 0.00208 -0.0899 0.7988 0.7246
-0.250 0.3805 0.00667 0.00207 -0.0894 0.7890 0.7454
0.000 0.4076 0.00667 0.00206 -0.0891 0.7801 0.7586
0.250 0.4350 0.00667 0.00203 -0.0889 0.7725 0.7687
0.500 0.4622 0.00666 0.00203 -0.0887 0.7634 0.7778
0.750 0.4896 0.00667 0.00202 -0.0885 0.7544 0.7880
1.000 0.5167 0.00668 0.00201 -0.0882 0.7447 0.7985
1.250 0.5433 0.00667 0.00200 -0.0879 0.7330 0.8092
1.500 0.5699 0.00667 0.00201 -0.0875 0.7211 0.8211
1.750 0.5964 0.00667 0.00203 -0.0871 0.7100 0.8345
2.000 0.6225 0.00666 0.00206 -0.0867 0.6985 0.8502
2.250 0.6479 0.00665 0.00208 -0.0860 0.6862 0.8703
2.500 0.6720 0.00658 0.00210 -0.0850 0.6730 0.9035
2.750 0.7087 0.00654 0.00211 -0.0869 0.6569 1.0000
3.000 0.7359 0.00667 0.00219 -0.0868 0.6399 1.0000
3.250 0.7626 0.00681 0.00226 -0.0866 0.6211 1.0000
3.500 0.7888 0.00697 0.00236 -0.0864 0.5981 1.0000
3.750 0.8144 0.00717 0.00247 -0.0860 0.5724 1.0000
4.000 0.8391 0.00743 0.00262 -0.0854 0.5407 1.0000
4.250 0.8631 0.00775 0.00279 -0.0847 0.5051 1.0000
4.500 0.8864 0.00813 0.00300 -0.0840 0.4670 1.0000
4.750 0.9094 0.00855 0.00326 -0.0832 0.4270 1.0000
5.000 0.9323 0.00899 0.00355 -0.0825 0.3891 1.0000
5.250 0.9549 0.00946 0.00385 -0.0817 0.3509 1.0000
5.500 0.9772 0.00996 0.00417 -0.0809 0.3124 1.0000
5.750 0.9997 0.01044 0.00451 -0.0802 0.2803 1.0000
6.000 1.0222 0.01092 0.00486 -0.0794 0.2502 1.0000
6.250 1.0444 0.01143 0.00524 -0.0787 0.2186 1.0000
6.500 1.0662 0.01196 0.00561 -0.0779 0.1891 1.0000
6.750 1.0882 0.01247 0.00600 -0.0771 0.1641 1.0000
7.000 1.1102 0.01296 0.00641 -0.0763 0.1438 1.0000
7.250 1.1323 0.01344 0.00682 -0.0755 0.1246 1.0000
7.500 1.1533 0.01400 0.00730 -0.0746 0.1039 1.0000
7.750 1.1732 0.01464 0.00782 -0.0735 0.0811 1.0000
8.000 1.1911 0.01544 0.00844 -0.0722 0.0562 1.0000
8.250 1.2105 0.01609 0.00903 -0.0710 0.0423 1.0000
8.500 1.2293 0.01676 0.00966 -0.0698 0.0313 1.0000
8.750 1.2452 0.01767 0.01047 -0.0681 0.0172 1.0000
9.000 1.2611 0.01853 0.01132 -0.0663 0.0101 1.0000
9.250 1.2766 0.01938 0.01220 -0.0645 0.0078 1.0000
9.500 1.2903 0.02022 0.01317 -0.0623 0.0071 1.0000
9.750 1.3032 0.02104 0.01409 -0.0601 0.0067 1.0000
10.000 1.3143 0.02196 0.01513 -0.0576 0.0064 1.0000
10.250 1.3244 0.02295 0.01623 -0.0552 0.0062 1.0000
10.500 1.3327 0.02407 0.01747 -0.0526 0.0060 1.0000
10.750 1.3402 0.02527 0.01879 -0.0501 0.0060 1.0000
11.000 1.3457 0.02665 0.02029 -0.0476 0.0058 1.0000
11.250 1.3501 0.02815 0.02192 -0.0452 0.0058 1.0000
11.500 1.3532 0.02984 0.02373 -0.0428 0.0058 1.0000
11.750 1.3551 0.03170 0.02574 -0.0406 0.0057 1.0000
12.000 1.3569 0.03366 0.02782 -0.0386 0.0056 1.0000
12.250 1.3574 0.03585 0.03017 -0.0368 0.0056 1.0000
12.500 1.3591 0.03797 0.03241 -0.0354 0.0054 1.0000
12.750 1.3588 0.04042 0.03499 -0.0341 0.0053 1.0000
13.000 1.3563 0.04322 0.03793 -0.0330 0.0052 1.0000
13.250 1.3521 0.04632 0.04116 -0.0322 0.0050 1.0000
13.500 1.3478 0.04962 0.04462 -0.0317 0.0050 1.0000
13.750 1.3414 0.05334 0.04850 -0.0315 0.0049 1.0000
14.000 1.3367 0.05701 0.05233 -0.0316 0.0050 1.0000
14.250 1.3270 0.06156 0.05706 -0.0322 0.0049 1.0000
14.500 1.3203 0.06592 0.06158 -0.0331 0.0049 1.0000
14.750 1.3093 0.07115 0.06699 -0.0347 0.0049 1.0000
15.000 1.2977 0.07680 0.07282 -0.0367 0.0048 1.0000
15.250 1.2891 0.08227 0.07846 -0.0390 0.0049 1.0000
15.500 1.2779 0.08842 0.08478 -0.0419 0.0049 1.0000
15.750 1.2657 0.09512 0.09164 -0.0452 0.0049 1.0000
16.000 1.2531 0.10216 0.09885 -0.0490 0.0049 1.0000
16.250 1.2393 0.10971 0.10656 -0.0533 0.0049 1.0000
16.500 1.2269 0.11729 0.11429 -0.0577 0.0050 1.0000
16.750 1.2131 0.12542 0.12258 -0.0626 0.0050 1.0000
17.000 1.1986 0.13407 0.13140 -0.0678 0.0051 1.0000
17.250 1.1836 0.14300 0.14048 -0.0733 0.0051 1.0000
17.500 1.1655 0.15325 0.15089 -0.0797 0.0052 1.0000
17.750 1.1430 0.16533 0.16316 -0.0872 0.0053 1.0000
18.000 1.0270 0.21869 0.21668 -0.1137 0.0083 1.0000
18.250 1.0356 0.22062 0.21863 -0.1154 0.0079 1.0000
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