HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 100,000 Max Cl/Cd: 51.33 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1510-il-100000.txt Download as CSV file: xf-hq1510-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4013 0.09800 0.09338 -0.0221 1.0000 0.1175
-9.500 -0.4309 0.09378 0.08930 -0.0279 1.0000 0.1200
-9.250 -0.4045 0.08930 0.08476 -0.0243 1.0000 0.1244
-9.000 -0.4036 0.08549 0.08099 -0.0251 1.0000 0.1299
-8.750 -0.4405 0.08075 0.07638 -0.0317 1.0000 0.1338
-8.500 -0.4155 0.07650 0.07212 -0.0281 1.0000 0.1380
-8.250 -0.4167 0.07261 0.06826 -0.0287 1.0000 0.1439
-8.000 -0.4663 0.06735 0.06317 -0.0360 1.0000 0.1474
-7.750 -0.4365 0.06371 0.05952 -0.0314 1.0000 0.1530
-7.500 -0.4538 0.05946 0.05536 -0.0331 1.0000 0.1575
-6.750 -0.5618 0.04404 0.03777 -0.0407 1.0000 0.0651
-6.500 -0.5535 0.03975 0.03336 -0.0390 1.0000 0.0624
-6.250 -0.5446 0.03602 0.02924 -0.0369 1.0000 0.0599
-6.000 -0.5332 0.03259 0.02530 -0.0347 1.0000 0.0584
-5.750 -0.5187 0.02983 0.02208 -0.0326 1.0000 0.0587
-5.500 -0.5024 0.02797 0.01984 -0.0308 1.0000 0.0628
-5.250 -0.4844 0.02617 0.01749 -0.0289 1.0000 0.0666
-5.000 -0.4655 0.02396 0.01525 -0.0276 1.0000 0.0717
-4.750 -0.4454 0.02250 0.01354 -0.0261 1.0000 0.0807
-4.500 -0.4255 0.02132 0.01226 -0.0248 1.0000 0.0924
-4.250 -0.4059 0.02000 0.01102 -0.0236 1.0000 0.1083
-4.000 -0.3863 0.01899 0.01014 -0.0226 1.0000 0.1259
-3.750 -0.3664 0.01806 0.00930 -0.0213 1.0000 0.1445
-3.500 -0.3471 0.01719 0.00859 -0.0202 1.0000 0.1765
-3.250 -0.3291 0.01551 0.00776 -0.0193 1.0000 0.2890
-3.000 -0.3198 0.01434 0.00816 -0.0156 1.0000 0.6149
-2.750 -0.3067 0.01454 0.00848 -0.0122 1.0000 0.6918
-2.500 -0.2933 0.01476 0.00869 -0.0089 1.0000 0.7414
-2.250 -0.2809 0.01492 0.00884 -0.0056 1.0000 0.7797
-2.000 -0.2571 0.01519 0.00907 -0.0043 0.9950 0.8190
-1.750 -0.2293 0.01541 0.00926 -0.0036 0.9870 0.8600
-1.500 -0.1981 0.01566 0.00950 -0.0031 0.9799 0.9069
-1.250 -0.1423 0.01600 0.00971 -0.0078 0.9750 0.9492
-1.000 -0.0641 0.01641 0.00991 -0.0177 0.9728 0.9756
-0.750 0.0146 0.01668 0.00998 -0.0281 0.9708 0.9945
-0.500 0.0585 0.01671 0.00990 -0.0329 0.9620 1.0000
-0.250 0.0975 0.01676 0.00987 -0.0366 0.9526 1.0000
0.000 0.1330 0.01680 0.00983 -0.0395 0.9425 1.0000
0.250 0.1621 0.01685 0.00982 -0.0410 0.9310 1.0000
0.500 0.1958 0.01694 0.00987 -0.0432 0.9208 1.0000
0.750 0.2505 0.01694 0.00984 -0.0485 0.9134 1.0000
1.000 0.2954 0.01681 0.00970 -0.0519 0.9012 1.0000
1.250 0.3422 0.01652 0.00943 -0.0550 0.8880 1.0000
1.500 0.3800 0.01630 0.00922 -0.0564 0.8748 1.0000
1.750 0.4112 0.01622 0.00915 -0.0568 0.8622 1.0000
2.000 0.4411 0.01617 0.00911 -0.0569 0.8500 1.0000
2.250 0.4704 0.01609 0.00908 -0.0567 0.8374 1.0000
2.500 0.4984 0.01602 0.00903 -0.0561 0.8242 1.0000
2.750 0.5250 0.01594 0.00899 -0.0552 0.8100 1.0000
3.000 0.5507 0.01586 0.00895 -0.0540 0.7947 1.0000
3.250 0.5764 0.01575 0.00891 -0.0528 0.7783 1.0000
3.500 0.6025 0.01558 0.00878 -0.0515 0.7612 1.0000
3.750 0.6294 0.01534 0.00857 -0.0501 0.7433 1.0000
4.000 0.6527 0.01522 0.00851 -0.0484 0.7198 1.0000
4.250 0.6772 0.01501 0.00837 -0.0467 0.6939 1.0000
4.500 0.7012 0.01480 0.00815 -0.0448 0.6625 1.0000
4.750 0.7239 0.01467 0.00799 -0.0428 0.6224 1.0000
5.000 0.7457 0.01467 0.00786 -0.0408 0.5724 1.0000
5.250 0.7659 0.01492 0.00793 -0.0387 0.5122 1.0000
5.500 0.7853 0.01545 0.00817 -0.0368 0.4516 1.0000
5.750 0.8043 0.01616 0.00860 -0.0352 0.3969 1.0000
6.000 0.8231 0.01696 0.00914 -0.0336 0.3477 1.0000
6.250 0.8410 0.01784 0.00981 -0.0321 0.2982 1.0000
6.500 0.8572 0.01900 0.01073 -0.0304 0.2464 1.0000
6.750 0.8718 0.02039 0.01180 -0.0285 0.1889 1.0000
7.000 0.8881 0.02176 0.01286 -0.0269 0.1513 1.0000
7.250 0.9073 0.02317 0.01414 -0.0256 0.1302 1.0000
7.500 0.9282 0.02465 0.01553 -0.0246 0.1160 1.0000
7.750 0.9501 0.02613 0.01702 -0.0237 0.1043 1.0000
8.000 0.9748 0.02807 0.01900 -0.0232 0.0966 1.0000
8.250 0.9993 0.02992 0.02098 -0.0226 0.0897 1.0000
8.500 1.0212 0.03207 0.02335 -0.0217 0.0822 1.0000
8.750 1.0436 0.03441 0.02574 -0.0212 0.0755 1.0000
9.000 1.0577 0.03617 0.02787 -0.0195 0.0666 1.0000
9.250 1.0705 0.03861 0.03052 -0.0180 0.0586 1.0000
9.500 1.0842 0.04056 0.03254 -0.0168 0.0510 1.0000
9.750 1.0888 0.04458 0.03711 -0.0143 0.0476 1.0000
10.000 1.0896 0.04829 0.04139 -0.0116 0.0457 1.0000
10.250 1.0857 0.05221 0.04578 -0.0089 0.0446 1.0000
10.500 1.0763 0.05621 0.05018 -0.0062 0.0442 1.0000
10.750 1.0604 0.05997 0.05426 -0.0033 0.0443 1.0000
11.000 1.0403 0.06378 0.05833 -0.0009 0.0446 1.0000
11.250 1.0173 0.06808 0.06287 0.0001 0.0448 1.0000
11.500 0.9946 0.07294 0.06792 -0.0005 0.0455 1.0000
11.750 0.9698 0.07870 0.07385 -0.0026 0.0460 1.0000
12.000 0.9451 0.08538 0.08066 -0.0062 0.0467 1.0000
12.250 0.9221 0.09296 0.08833 -0.0110 0.0476 1.0000
12.500 0.9037 0.10088 0.09629 -0.0158 0.0485 1.0000
12.750 0.8867 0.10963 0.10505 -0.0207 0.0492 1.0000
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