HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il) Reynolds number: 100,000 Max Cl/Cd: 54.29 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2010-il-100000.txt Download as CSV file: xf-hq2010-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/10 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3545 0.09133 0.08677 -0.0297 1.0000 0.1127
-9.000 -0.3640 0.08760 0.08311 -0.0320 1.0000 0.1176
-8.750 -0.3974 0.08374 0.07938 -0.0380 1.0000 0.1193
-8.500 -0.3637 0.07936 0.07497 -0.0329 1.0000 0.1241
-8.250 -0.3668 0.07576 0.07142 -0.0336 1.0000 0.1296
-8.000 -0.4033 0.07180 0.06762 -0.0384 1.0000 0.1328
-7.750 -0.3854 0.06770 0.06353 -0.0352 1.0000 0.1373
-7.500 -0.3910 0.06455 0.06046 -0.0345 1.0000 0.1422
-7.250 -0.4207 0.06130 0.05736 -0.0354 1.0000 0.1447
-7.000 -0.4686 0.05834 0.05438 -0.0373 1.0000 0.1469
-6.750 -0.4584 0.05468 0.05085 -0.0335 1.0000 0.1507
-6.500 -0.5037 0.06100 0.05672 -0.0369 1.0000 0.1523
-6.250 -0.5154 0.05820 0.05376 -0.0367 1.0000 0.1632
-6.000 -0.5080 0.05568 0.05133 -0.0338 1.0000 0.1687
-5.750 -0.5000 0.03917 0.03283 -0.0391 1.0000 0.0672
-5.500 -0.4843 0.03568 0.02893 -0.0376 1.0000 0.0617
-5.250 -0.4677 0.03231 0.02512 -0.0365 1.0000 0.0595
-5.000 -0.4486 0.02965 0.02198 -0.0353 1.0000 0.0603
-4.750 -0.4278 0.02781 0.01961 -0.0341 1.0000 0.0635
-4.500 -0.4055 0.02561 0.01695 -0.0330 1.0000 0.0657
-4.250 -0.3830 0.02355 0.01481 -0.0323 1.0000 0.0700
-4.000 -0.3606 0.02245 0.01346 -0.0313 1.0000 0.0791
-3.750 -0.3386 0.02111 0.01211 -0.0304 1.0000 0.0907
-3.500 -0.3173 0.02000 0.01101 -0.0296 1.0000 0.1071
-3.250 -0.2967 0.01905 0.01024 -0.0287 1.0000 0.1276
-3.000 -0.2758 0.01816 0.00951 -0.0278 1.0000 0.1537
-2.750 -0.2548 0.01700 0.00885 -0.0273 1.0000 0.2250
-2.500 -0.2396 0.01537 0.00926 -0.0247 0.9982 0.6491
-2.250 -0.2116 0.01582 0.00977 -0.0237 0.9911 0.7383
-2.000 -0.1836 0.01621 0.01015 -0.0229 0.9838 0.7932
-1.750 -0.1590 0.01640 0.01030 -0.0215 0.9760 0.8377
-1.500 -0.1304 0.01660 0.01048 -0.0206 0.9694 0.8859
-1.250 -0.0901 0.01670 0.01055 -0.0221 0.9636 0.9427
-1.000 -0.0064 0.01704 0.01067 -0.0329 0.9621 0.9864
-0.750 0.0464 0.01723 0.01065 -0.0393 0.9564 1.0000
-0.500 0.0749 0.01725 0.01055 -0.0411 0.9450 1.0000
-0.250 0.1109 0.01735 0.01052 -0.0439 0.9345 1.0000
0.000 0.1588 0.01751 0.01055 -0.0486 0.9273 1.0000
0.250 0.1883 0.01767 0.01062 -0.0499 0.9167 1.0000
0.500 0.2249 0.01787 0.01073 -0.0523 0.9079 1.0000
0.750 0.2724 0.01793 0.01074 -0.0562 0.9001 1.0000
1.000 0.3130 0.01791 0.01068 -0.0587 0.8884 1.0000
1.250 0.3603 0.01766 0.01042 -0.0619 0.8763 1.0000
1.500 0.4034 0.01739 0.01015 -0.0641 0.8647 1.0000
1.750 0.4485 0.01708 0.00985 -0.0666 0.8566 1.0000
2.000 0.4772 0.01710 0.00987 -0.0665 0.8443 1.0000
2.250 0.5062 0.01708 0.00990 -0.0663 0.8320 1.0000
2.500 0.5356 0.01702 0.00986 -0.0661 0.8197 1.0000
2.750 0.5650 0.01690 0.00978 -0.0657 0.8069 1.0000
3.000 0.5938 0.01675 0.00967 -0.0651 0.7936 1.0000
3.250 0.6221 0.01656 0.00956 -0.0643 0.7792 1.0000
3.500 0.6499 0.01635 0.00940 -0.0633 0.7638 1.0000
3.750 0.6779 0.01608 0.00917 -0.0623 0.7471 1.0000
4.000 0.7059 0.01578 0.00891 -0.0611 0.7289 1.0000
4.250 0.7308 0.01558 0.00880 -0.0596 0.7054 1.0000
4.500 0.7561 0.01536 0.00861 -0.0581 0.6787 1.0000
4.750 0.7814 0.01516 0.00838 -0.0565 0.6468 1.0000
5.000 0.8043 0.01509 0.00826 -0.0546 0.6048 1.0000
5.250 0.8258 0.01521 0.00827 -0.0526 0.5528 1.0000
5.500 0.8460 0.01559 0.00839 -0.0507 0.4964 1.0000
5.750 0.8654 0.01616 0.00870 -0.0489 0.4428 1.0000
6.000 0.8847 0.01690 0.00917 -0.0473 0.3981 1.0000
6.250 0.9042 0.01767 0.00978 -0.0459 0.3587 1.0000
6.500 0.9230 0.01846 0.01044 -0.0445 0.3221 1.0000
6.750 0.9414 0.01932 0.01120 -0.0431 0.2848 1.0000
7.000 0.9574 0.02038 0.01210 -0.0414 0.2421 1.0000
7.250 0.9709 0.02163 0.01309 -0.0394 0.1929 1.0000
7.500 0.9853 0.02299 0.01419 -0.0375 0.1557 1.0000
7.750 1.0031 0.02445 0.01554 -0.0360 0.1330 1.0000
8.000 1.0220 0.02590 0.01689 -0.0348 0.1178 1.0000
8.250 1.0433 0.02748 0.01854 -0.0339 0.1065 1.0000
8.500 1.0677 0.02948 0.02054 -0.0334 0.0985 1.0000
8.750 1.0912 0.03130 0.02240 -0.0328 0.0907 1.0000
9.000 1.1121 0.03340 0.02477 -0.0318 0.0830 1.0000
9.250 1.1294 0.03544 0.02687 -0.0308 0.0737 1.0000
9.500 1.1402 0.03683 0.02827 -0.0293 0.0625 1.0000
9.750 1.1510 0.03864 0.03040 -0.0272 0.0542 1.0000
10.000 1.1605 0.04252 0.03468 -0.0251 0.0480 1.0000
10.250 1.1685 0.04497 0.03744 -0.0231 0.0434 1.0000
10.500 1.1755 0.04952 0.04204 -0.0221 0.0399 1.0000
10.750 1.1698 0.05189 0.04494 -0.0186 0.0387 1.0000
11.000 1.1603 0.05498 0.04844 -0.0153 0.0378 1.0000
11.250 1.1463 0.05832 0.05212 -0.0122 0.0374 1.0000
11.500 1.1302 0.06198 0.05608 -0.0099 0.0374 1.0000
11.750 1.1111 0.06604 0.06042 -0.0085 0.0374 1.0000
12.000 1.0900 0.07061 0.06524 -0.0083 0.0374 1.0000
12.250 1.0692 0.07568 0.07052 -0.0092 0.0377 1.0000
12.500 1.0472 0.08145 0.07647 -0.0112 0.0381 1.0000
12.750 1.0243 0.08798 0.08316 -0.0145 0.0384 1.0000
13.000 1.0013 0.09543 0.09075 -0.0189 0.0389 1.0000
13.250 0.9808 0.10348 0.09888 -0.0236 0.0395 1.0000
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Polar data table (+)
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