HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il) Reynolds number: 200,000 Max Cl/Cd: 67.32 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq159b-il-200000.txt Download as CSV file: xf-hq159b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4229 0.10563 0.10227 -0.0147 1.0000 0.0442
-10.250 -0.4209 0.10170 0.09834 -0.0158 1.0000 0.0455
-10.000 -0.5198 0.10282 0.09926 -0.0164 1.0000 0.0425
-9.750 -0.5147 0.09946 0.09591 -0.0171 1.0000 0.0434
-9.500 -0.5114 0.09586 0.09234 -0.0183 1.0000 0.0446
-9.250 -0.5102 0.09200 0.08850 -0.0201 1.0000 0.0458
-9.000 -0.5110 0.08778 0.08432 -0.0224 1.0000 0.0473
-8.750 -0.5139 0.08324 0.07983 -0.0254 1.0000 0.0485
-8.500 -0.5209 0.07799 0.07464 -0.0299 1.0000 0.0497
-8.250 -0.5331 0.07233 0.06904 -0.0355 1.0000 0.0499
-8.000 -0.5459 0.06665 0.06323 -0.0411 1.0000 0.0512
-7.750 -0.5576 0.06346 0.05962 -0.0437 1.0000 0.0524
-7.500 -0.5566 0.06027 0.05614 -0.0436 1.0000 0.0526
-7.250 -0.5555 0.05212 0.04816 -0.0442 1.0000 0.0543
-7.000 -0.5457 0.04901 0.04505 -0.0434 1.0000 0.0555
-6.750 -0.5368 0.04611 0.04206 -0.0424 1.0000 0.0572
-6.500 -0.5283 0.04315 0.03891 -0.0412 1.0000 0.0594
-6.250 -0.5201 0.04014 0.03562 -0.0396 1.0000 0.0619
-6.000 -0.5150 0.03475 0.02961 -0.0372 1.0000 0.0555
-5.500 -0.4861 0.02268 0.01588 -0.0312 1.0000 0.0319
-5.250 -0.4690 0.02174 0.01485 -0.0298 1.0000 0.0347
-5.000 -0.4497 0.02009 0.01292 -0.0282 1.0000 0.0368
-4.750 -0.4296 0.01892 0.01148 -0.0266 1.0000 0.0396
-4.500 -0.4101 0.01737 0.00989 -0.0255 1.0000 0.0454
-4.250 -0.3747 0.01657 0.00891 -0.0271 0.9965 0.0532
-4.000 -0.3383 0.01553 0.00787 -0.0293 0.9925 0.0635
-3.750 -0.3026 0.01457 0.00693 -0.0312 0.9876 0.0741
-3.500 -0.2649 0.01373 0.00610 -0.0336 0.9835 0.0867
-3.250 -0.2303 0.01294 0.00540 -0.0354 0.9778 0.1118
-3.000 -0.1985 0.01110 0.00477 -0.0376 0.9728 0.3569
-2.750 -0.1660 0.01032 0.00496 -0.0387 0.9686 0.6157
-2.500 -0.1348 0.01028 0.00503 -0.0391 0.9610 0.6819
-2.250 -0.0953 0.01027 0.00503 -0.0411 0.9566 0.7253
-2.000 -0.0621 0.01026 0.00503 -0.0417 0.9492 0.7589
-1.750 -0.0248 0.01021 0.00500 -0.0431 0.9438 0.7885
-1.500 0.0063 0.01017 0.00498 -0.0431 0.9364 0.8153
-1.250 0.0379 0.01009 0.00491 -0.0433 0.9300 0.8369
-1.000 0.0666 0.01004 0.00485 -0.0430 0.9230 0.8565
-0.750 0.0945 0.00995 0.00479 -0.0424 0.9161 0.8753
-0.500 0.1218 0.00987 0.00471 -0.0418 0.9082 0.8920
-0.250 0.1513 0.00974 0.00457 -0.0415 0.9004 0.9087
0.000 0.1792 0.00963 0.00445 -0.0409 0.8901 0.9260
0.250 0.2124 0.00950 0.00430 -0.0415 0.8805 0.9407
0.500 0.2502 0.00935 0.00412 -0.0430 0.8713 0.9533
0.750 0.2896 0.00924 0.00399 -0.0451 0.8593 0.9656
1.000 0.3308 0.00915 0.00388 -0.0477 0.8473 0.9776
1.250 0.3737 0.00908 0.00381 -0.0509 0.8370 0.9896
1.500 0.4088 0.00902 0.00374 -0.0526 0.8261 1.0000
1.750 0.4261 0.00903 0.00371 -0.0508 0.8135 1.0000
2.000 0.4474 0.00907 0.00374 -0.0496 0.8008 1.0000
2.250 0.4712 0.00912 0.00377 -0.0487 0.7876 1.0000
2.500 0.4960 0.00917 0.00382 -0.0480 0.7741 1.0000
2.750 0.5213 0.00922 0.00386 -0.0473 0.7593 1.0000
3.000 0.5462 0.00925 0.00390 -0.0464 0.7406 1.0000
3.250 0.5709 0.00927 0.00389 -0.0454 0.7169 1.0000
3.500 0.5953 0.00932 0.00388 -0.0443 0.6874 1.0000
3.750 0.6192 0.00940 0.00389 -0.0431 0.6486 1.0000
4.000 0.6426 0.00957 0.00395 -0.0419 0.5993 1.0000
4.250 0.6651 0.00988 0.00404 -0.0407 0.5343 1.0000
4.500 0.6858 0.01045 0.00425 -0.0393 0.4592 1.0000
4.750 0.7065 0.01113 0.00460 -0.0381 0.3842 1.0000
5.000 0.7271 0.01187 0.00500 -0.0371 0.3144 1.0000
5.250 0.7487 0.01258 0.00550 -0.0363 0.2650 1.0000
5.500 0.7706 0.01329 0.00603 -0.0355 0.2104 1.0000
5.750 0.7850 0.01512 0.00704 -0.0339 0.0871 1.0000
6.000 0.8053 0.01624 0.00808 -0.0327 0.0651 1.0000
6.250 0.8262 0.01724 0.00911 -0.0316 0.0569 1.0000
6.500 0.8464 0.01834 0.01019 -0.0305 0.0507 1.0000
6.750 0.8674 0.01944 0.01140 -0.0294 0.0461 1.0000
7.000 0.8889 0.02056 0.01257 -0.0284 0.0419 1.0000
7.250 0.9085 0.02257 0.01457 -0.0273 0.0375 1.0000
7.500 0.9318 0.02398 0.01617 -0.0264 0.0350 1.0000
7.750 0.9548 0.02580 0.01815 -0.0255 0.0326 1.0000
8.000 0.9757 0.02753 0.01994 -0.0248 0.0295 1.0000
8.250 0.9934 0.03207 0.02486 -0.0237 0.0277 1.0000
8.500 1.0111 0.03423 0.02741 -0.0222 0.0271 1.0000
8.750 1.0249 0.03748 0.03110 -0.0204 0.0268 1.0000
9.000 1.0334 0.04149 0.03555 -0.0184 0.0270 1.0000
9.250 1.0401 0.04715 0.04154 -0.0168 0.0281 1.0000
9.500 1.0509 0.04906 0.04376 -0.0148 0.0287 1.0000
13.250 0.6647 0.15000 0.14698 -0.0497 0.0557 1.0000
13.500 0.6658 0.15324 0.15024 -0.0513 0.0535 1.0000
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Polar data table (+)
Polar graphs
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