HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il) Reynolds number: 100,000 Max Cl/Cd: 58.41 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq259b-il-100000.txt Download as CSV file: xf-hq259b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9 B 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4225 0.09200 0.08709 -0.0335 1.0000 0.1006
-8.250 -0.4439 0.08966 0.08491 -0.0370 1.0000 0.1022
-8.000 -0.4686 0.08617 0.08153 -0.0441 1.0000 0.1029
-7.750 -0.4381 0.08262 0.07800 -0.0341 1.0000 0.1071
-7.500 -0.4393 0.07999 0.07543 -0.0334 1.0000 0.1109
-7.250 -0.4510 0.07654 0.07208 -0.0366 1.0000 0.1145
-7.000 -0.4849 0.07359 0.06893 -0.0447 1.0000 0.1175
-6.750 -0.4719 0.06928 0.06488 -0.0394 1.0000 0.1204
-6.500 -0.4684 0.06729 0.06294 -0.0363 1.0000 0.1256
-6.250 -0.4837 0.06357 0.05890 -0.0418 1.0000 0.1332
-6.000 -0.4737 0.06125 0.05685 -0.0362 1.0000 0.1388
-5.750 -0.4733 0.05776 0.05321 -0.0381 1.0000 0.1498
-5.500 -0.4675 0.05498 0.05028 -0.0384 1.0000 0.1639
-5.250 -0.4587 0.05228 0.04750 -0.0382 1.0000 0.1785
-5.000 -0.4483 0.04961 0.04482 -0.0374 1.0000 0.1938
-4.750 -0.4372 0.04715 0.04240 -0.0359 1.0000 0.2107
-4.250 -0.3479 0.03271 0.02523 -0.0458 1.0000 0.0900
-4.000 -0.3228 0.03028 0.02252 -0.0456 1.0000 0.0866
-3.750 -0.2959 0.02756 0.01946 -0.0456 1.0000 0.0822
-3.500 -0.2682 0.02544 0.01683 -0.0453 1.0000 0.0791
-3.250 -0.2425 0.02395 0.01503 -0.0448 1.0000 0.0792
-3.000 -0.2185 0.02294 0.01387 -0.0443 1.0000 0.0835
-2.750 -0.1939 0.02197 0.01269 -0.0436 1.0000 0.0865
-2.500 -0.1696 0.02106 0.01165 -0.0428 1.0000 0.0892
-2.250 -0.1459 0.02001 0.01073 -0.0424 1.0000 0.0955
-2.000 -0.1225 0.01933 0.01012 -0.0419 1.0000 0.1074
-1.750 -0.0982 0.01866 0.00955 -0.0415 1.0000 0.1248
-1.500 -0.0717 0.01601 0.00928 -0.0416 1.0000 0.6239
-1.250 -0.0667 0.01598 0.00970 -0.0354 1.0000 0.7910
-1.000 -0.0613 0.01588 0.00978 -0.0299 1.0000 0.8797
-0.750 -0.0100 0.01590 0.00970 -0.0349 0.9900 1.0000
-0.500 0.0437 0.01644 0.00994 -0.0409 0.9794 1.0000
-0.250 0.0978 0.01697 0.01023 -0.0467 0.9698 1.0000
0.000 0.1372 0.01723 0.01032 -0.0497 0.9599 1.0000
0.250 0.1795 0.01757 0.01052 -0.0530 0.9512 1.0000
0.500 0.2241 0.01789 0.01072 -0.0567 0.9429 1.0000
0.750 0.2603 0.01814 0.01089 -0.0588 0.9329 1.0000
1.000 0.3054 0.01838 0.01107 -0.0623 0.9246 1.0000
1.250 0.3454 0.01853 0.01119 -0.0647 0.9144 1.0000
1.500 0.3827 0.01866 0.01132 -0.0666 0.9035 1.0000
1.750 0.4271 0.01867 0.01134 -0.0695 0.8936 1.0000
2.000 0.4759 0.01851 0.01123 -0.0731 0.8840 1.0000
2.250 0.5159 0.01839 0.01117 -0.0749 0.8717 1.0000
2.500 0.5571 0.01813 0.01099 -0.0767 0.8593 1.0000
2.750 0.5980 0.01776 0.01071 -0.0781 0.8465 1.0000
3.000 0.6369 0.01732 0.01038 -0.0789 0.8322 1.0000
3.250 0.6732 0.01682 0.00998 -0.0791 0.8159 1.0000
3.500 0.7085 0.01625 0.00950 -0.0788 0.7977 1.0000
3.750 0.7390 0.01575 0.00910 -0.0777 0.7745 1.0000
4.000 0.7681 0.01521 0.00860 -0.0762 0.7454 1.0000
4.250 0.7952 0.01472 0.00809 -0.0743 0.7078 1.0000
4.500 0.8185 0.01450 0.00785 -0.0722 0.6573 1.0000
4.750 0.8419 0.01449 0.00767 -0.0704 0.5993 1.0000
5.000 0.8650 0.01481 0.00768 -0.0687 0.5439 1.0000
5.250 0.8872 0.01543 0.00802 -0.0673 0.4971 1.0000
5.500 0.9090 0.01615 0.00856 -0.0661 0.4565 1.0000
5.750 0.9299 0.01688 0.00913 -0.0647 0.4169 1.0000
6.000 0.9497 0.01760 0.00975 -0.0633 0.3745 1.0000
6.250 0.9667 0.01836 0.01037 -0.0615 0.3204 1.0000
6.500 0.9804 0.01939 0.01105 -0.0593 0.2464 1.0000
6.750 0.9934 0.02089 0.01204 -0.0572 0.1824 1.0000
7.000 1.0086 0.02250 0.01334 -0.0555 0.1444 1.0000
7.250 1.0253 0.02422 0.01488 -0.0538 0.1190 1.0000
7.500 1.0440 0.02627 0.01669 -0.0526 0.1018 1.0000
7.750 1.0657 0.02810 0.01846 -0.0518 0.0889 1.0000
8.000 1.0906 0.03003 0.02062 -0.0510 0.0811 1.0000
8.250 1.1172 0.03272 0.02321 -0.0510 0.0748 1.0000
8.500 1.1386 0.03448 0.02535 -0.0498 0.0696 1.0000
8.750 1.1614 0.03690 0.02797 -0.0491 0.0661 1.0000
9.000 1.1840 0.04088 0.03203 -0.0489 0.0631 1.0000
9.250 1.1956 0.04324 0.03501 -0.0465 0.0610 1.0000
9.500 1.2053 0.04629 0.03860 -0.0443 0.0591 1.0000
9.750 1.2115 0.05011 0.04293 -0.0420 0.0586 1.0000
10.000 1.2122 0.05427 0.04757 -0.0394 0.0585 1.0000
10.250 1.2072 0.05851 0.05225 -0.0367 0.0586 1.0000
10.500 1.1969 0.06271 0.05684 -0.0339 0.0586 1.0000
10.750 1.1808 0.06673 0.06116 -0.0309 0.0588 1.0000
11.000 1.1601 0.07069 0.06536 -0.0282 0.0592 1.0000
11.250 1.1378 0.07511 0.06998 -0.0267 0.0598 1.0000
11.500 1.1146 0.08010 0.07515 -0.0265 0.0604 1.0000
11.750 1.0921 0.08582 0.08101 -0.0277 0.0611 1.0000
12.000 1.0718 0.09219 0.08749 -0.0299 0.0618 1.0000
12.250 1.0574 0.09918 0.09453 -0.0324 0.0626 1.0000
12.500 0.8397 0.12135 0.11722 -0.0458 0.0747 1.0000
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Polar data table (+)
Polar graphs
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