HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il) Reynolds number: 500,000 Max Cl/Cd: 84 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3015-il-500000-n5.txt Download as CSV file: xf-hq3015-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/15 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6994 0.10462 0.10151 -0.0540 1.0000 0.0096
-16.500 -0.7504 0.09126 0.08798 -0.0611 1.0000 0.0095
-16.250 -0.7954 0.07924 0.07579 -0.0679 1.0000 0.0093
-16.000 -0.8296 0.06921 0.06557 -0.0739 1.0000 0.0093
-15.750 -0.8564 0.06091 0.05709 -0.0791 1.0000 0.0092
-15.500 -0.8762 0.05457 0.05059 -0.0829 1.0000 0.0092
-15.250 -0.8899 0.04964 0.04553 -0.0855 1.0000 0.0092
-15.000 -0.8995 0.04561 0.04137 -0.0874 1.0000 0.0093
-14.750 -0.9077 0.04201 0.03766 -0.0887 1.0000 0.0094
-14.500 -0.9125 0.03906 0.03459 -0.0894 1.0000 0.0094
-14.250 -0.9161 0.03644 0.03187 -0.0897 1.0000 0.0095
-14.000 -0.9190 0.03410 0.02944 -0.0896 1.0000 0.0096
-13.750 -0.9210 0.03210 0.02735 -0.0889 1.0000 0.0097
-13.500 -0.9232 0.03038 0.02554 -0.0877 1.0000 0.0099
-13.250 -0.9135 0.02856 0.02362 -0.0885 0.9919 0.0100
-13.000 -0.8927 0.02683 0.02176 -0.0910 0.9835 0.0102
-12.750 -0.8712 0.02500 0.01982 -0.0939 0.9746 0.0105
-12.500 -0.8460 0.02352 0.01823 -0.0966 0.9658 0.0109
-12.250 -0.8201 0.02227 0.01687 -0.0988 0.9555 0.0112
-12.000 -0.7969 0.02127 0.01576 -0.0998 0.9423 0.0117
-11.750 -0.7754 0.02044 0.01482 -0.1000 0.9289 0.0122
-11.500 -0.7552 0.01972 0.01397 -0.0997 0.9168 0.0127
-11.250 -0.7372 0.01899 0.01316 -0.0989 0.9062 0.0135
-11.000 -0.7190 0.01837 0.01244 -0.0979 0.8961 0.0144
-10.750 -0.7002 0.01782 0.01181 -0.0969 0.8871 0.0153
-10.500 -0.6804 0.01729 0.01121 -0.0960 0.8790 0.0165
-10.250 -0.6599 0.01682 0.01070 -0.0952 0.8717 0.0182
-10.000 -0.6383 0.01640 0.01021 -0.0945 0.8647 0.0199
-9.750 -0.6161 0.01602 0.00978 -0.0938 0.8582 0.0219
-9.500 -0.5930 0.01568 0.00936 -0.0933 0.8517 0.0238
-9.250 -0.5700 0.01532 0.00894 -0.0927 0.8462 0.0255
-9.000 -0.5463 0.01500 0.00859 -0.0922 0.8401 0.0273
-8.750 -0.5221 0.01471 0.00821 -0.0917 0.8342 0.0289
-8.500 -0.4983 0.01436 0.00781 -0.0913 0.8289 0.0303
-8.250 -0.4740 0.01404 0.00747 -0.0909 0.8232 0.0319
-8.000 -0.4490 0.01378 0.00716 -0.0905 0.8176 0.0338
-7.750 -0.4237 0.01354 0.00684 -0.0902 0.8125 0.0353
-7.500 -0.3990 0.01320 0.00648 -0.0898 0.8068 0.0371
-7.250 -0.3736 0.01295 0.00621 -0.0895 0.8016 0.0394
-7.000 -0.3477 0.01273 0.00594 -0.0893 0.7966 0.0415
-6.750 -0.3219 0.01247 0.00565 -0.0890 0.7910 0.0439
-6.500 -0.2963 0.01220 0.00536 -0.0888 0.7859 0.0466
-6.250 -0.2702 0.01197 0.00509 -0.0885 0.7811 0.0491
-6.000 -0.2438 0.01175 0.00483 -0.0884 0.7757 0.0512
-5.750 -0.2177 0.01150 0.00454 -0.0881 0.7706 0.0543
-5.500 -0.1913 0.01127 0.00430 -0.0879 0.7661 0.0582
-5.250 -0.1644 0.01109 0.00408 -0.0878 0.7607 0.0618
-5.000 -0.1379 0.01087 0.00386 -0.0876 0.7556 0.0671
-4.750 -0.1109 0.01070 0.00365 -0.0875 0.7511 0.0730
-4.500 -0.0840 0.01049 0.00347 -0.0874 0.7459 0.0809
-4.250 -0.0570 0.01031 0.00329 -0.0873 0.7407 0.0907
-3.750 -0.0032 0.00991 0.00296 -0.0872 0.7308 0.1228
-3.500 0.0233 0.00965 0.00280 -0.0871 0.7253 0.1529
-3.250 0.0497 0.00940 0.00264 -0.0869 0.7200 0.1928
-3.000 0.0763 0.00911 0.00251 -0.0869 0.7141 0.2355
-2.750 0.1025 0.00881 0.00235 -0.0868 0.7083 0.2872
-2.500 0.1274 0.00831 0.00218 -0.0866 0.7033 0.3830
-2.250 0.1539 0.00805 0.00213 -0.0864 0.6980 0.4553
-2.000 0.1813 0.00796 0.00211 -0.0863 0.6928 0.4892
-1.750 0.2092 0.00794 0.00208 -0.0863 0.6880 0.5103
-1.500 0.2370 0.00788 0.00209 -0.0863 0.6828 0.5336
-1.250 0.2648 0.00787 0.00210 -0.0862 0.6770 0.5577
-1.000 0.2924 0.00788 0.00211 -0.0860 0.6707 0.5763
-0.750 0.3202 0.00789 0.00212 -0.0859 0.6630 0.5873
-0.500 0.3478 0.00792 0.00211 -0.0858 0.6555 0.5953
-0.250 0.3756 0.00794 0.00212 -0.0858 0.6469 0.6027
0.000 0.4032 0.00798 0.00212 -0.0857 0.6394 0.6099
0.250 0.4309 0.00801 0.00215 -0.0856 0.6313 0.6183
0.500 0.4584 0.00806 0.00218 -0.0854 0.6244 0.6269
0.750 0.4861 0.00809 0.00222 -0.0854 0.6168 0.6351
1.000 0.5135 0.00815 0.00225 -0.0852 0.6092 0.6413
1.250 0.5410 0.00819 0.00229 -0.0851 0.6003 0.6467
1.500 0.5681 0.00825 0.00233 -0.0850 0.5912 0.6520
1.750 0.5949 0.00833 0.00237 -0.0847 0.5803 0.6569
2.000 0.6211 0.00842 0.00243 -0.0844 0.5660 0.6618
2.250 0.6469 0.00853 0.00250 -0.0840 0.5506 0.6674
2.500 0.6728 0.00865 0.00257 -0.0836 0.5362 0.6730
2.750 0.6982 0.00877 0.00268 -0.0832 0.5211 0.6784
3.000 0.7232 0.00893 0.00278 -0.0826 0.5046 0.6842
3.250 0.7477 0.00911 0.00290 -0.0820 0.4871 0.6897
3.500 0.7717 0.00930 0.00305 -0.0813 0.4697 0.6956
3.750 0.7954 0.00951 0.00320 -0.0806 0.4504 0.7020
4.000 0.8183 0.00976 0.00338 -0.0797 0.4297 0.7078
4.250 0.8408 0.01001 0.00357 -0.0788 0.4103 0.7142
4.750 0.8847 0.01056 0.00401 -0.0768 0.3697 0.7275
5.000 0.9057 0.01088 0.00424 -0.0757 0.3484 0.7346
5.250 0.9260 0.01120 0.00450 -0.0744 0.3284 0.7413
5.500 0.9468 0.01149 0.00476 -0.0732 0.3128 0.7491
5.750 0.9669 0.01179 0.00502 -0.0720 0.2986 0.7567
6.000 0.9868 0.01209 0.00530 -0.0706 0.2848 0.7650
6.250 1.0066 0.01237 0.00557 -0.0693 0.2735 0.7729
6.500 1.0248 0.01263 0.00585 -0.0676 0.2641 0.7823
6.750 1.0420 0.01290 0.00612 -0.0658 0.2544 0.7919
7.000 1.0595 0.01318 0.00643 -0.0640 0.2449 0.8027
7.250 1.0755 0.01351 0.00677 -0.0620 0.2348 0.8148
7.500 1.0916 0.01382 0.00711 -0.0601 0.2242 0.8291
7.750 1.1074 0.01413 0.00746 -0.0581 0.2146 0.8474
8.250 1.1514 0.01481 0.00830 -0.0571 0.1931 1.0000
8.500 1.1683 0.01526 0.00873 -0.0556 0.1846 1.0000
8.750 1.1835 0.01579 0.00923 -0.0539 0.1758 1.0000
9.000 1.1987 0.01633 0.00975 -0.0523 0.1661 1.0000
9.250 1.2141 0.01689 0.01029 -0.0508 0.1588 1.0000
9.500 1.2269 0.01759 0.01094 -0.0490 0.1481 1.0000
9.750 1.2432 0.01814 0.01150 -0.0477 0.1421 1.0000
10.000 1.2563 0.01887 0.01220 -0.0461 0.1339 1.0000
10.250 1.2708 0.01955 0.01288 -0.0446 0.1260 1.0000
10.500 1.2838 0.02033 0.01364 -0.0431 0.1190 1.0000
10.750 1.2972 0.02111 0.01442 -0.0417 0.1116 1.0000
11.000 1.3092 0.02200 0.01528 -0.0403 0.1039 1.0000
11.250 1.3204 0.02296 0.01623 -0.0388 0.0961 1.0000
11.500 1.3313 0.02397 0.01722 -0.0374 0.0872 1.0000
11.750 1.3416 0.02505 0.01828 -0.0360 0.0804 1.0000
12.000 1.3522 0.02614 0.01937 -0.0347 0.0739 1.0000
12.250 1.3619 0.02731 0.02055 -0.0334 0.0684 1.0000
12.500 1.3713 0.02854 0.02178 -0.0321 0.0628 1.0000
12.750 1.3800 0.02985 0.02310 -0.0309 0.0579 1.0000
13.000 1.3877 0.03126 0.02453 -0.0298 0.0527 1.0000
13.250 1.3956 0.03271 0.02599 -0.0287 0.0486 1.0000
13.500 1.4035 0.03419 0.02751 -0.0277 0.0450 1.0000
13.750 1.4089 0.03591 0.02924 -0.0267 0.0409 1.0000
14.000 1.4160 0.03755 0.03092 -0.0258 0.0378 1.0000
14.250 1.4199 0.03953 0.03290 -0.0250 0.0342 1.0000
14.500 1.4256 0.04139 0.03483 -0.0243 0.0312 1.0000
14.750 1.4286 0.04356 0.03702 -0.0237 0.0281 1.0000
15.000 1.4342 0.04555 0.03907 -0.0232 0.0263 1.0000
15.250 1.4389 0.04769 0.04128 -0.0228 0.0248 1.0000
15.500 1.4396 0.05029 0.04392 -0.0225 0.0218 1.0000
15.750 1.4428 0.05270 0.04640 -0.0223 0.0202 1.0000
16.000 1.4422 0.05562 0.04937 -0.0223 0.0176 1.0000
16.250 1.4416 0.05864 0.05245 -0.0224 0.0154 1.0000
16.500 1.4372 0.06219 0.05605 -0.0227 0.0123 1.0000
16.750 1.4339 0.06572 0.05966 -0.0232 0.0102 1.0000
17.000 1.4222 0.07050 0.06448 -0.0241 0.0064 1.0000
17.250 1.4155 0.07476 0.06884 -0.0251 0.0055 1.0000
17.500 1.4101 0.07896 0.07314 -0.0262 0.0052 1.0000
17.750 1.4017 0.08373 0.07802 -0.0276 0.0048 1.0000
18.000 1.3951 0.08836 0.08276 -0.0292 0.0047 1.0000
18.250 1.3850 0.09363 0.08814 -0.0311 0.0044 1.0000
18.500 1.3791 0.09834 0.09297 -0.0330 0.0044 1.0000
18.750 1.3703 0.10360 0.09836 -0.0351 0.0043 1.0000
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