HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 50,000 Max Cl/Cd: 41.07 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq309-il-50000-n5.txt Download as CSV file: xf-hq309-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3750 0.09883 0.09220 -0.0338 1.0000 0.1056
-8.000 -0.3986 0.09803 0.09163 -0.0359 1.0000 0.1106
-7.750 -0.4159 0.09609 0.08990 -0.0387 1.0000 0.1112
-7.250 -0.3937 0.08529 0.07906 -0.0363 1.0000 0.0634
-7.000 -0.3993 0.08092 0.07476 -0.0388 1.0000 0.0522
-6.750 -0.4026 0.07752 0.07143 -0.0394 1.0000 0.0500
-6.500 -0.4065 0.07373 0.06767 -0.0408 1.0000 0.0477
-6.250 -0.4087 0.06830 0.06193 -0.0464 1.0000 0.0425
-6.000 -0.4053 0.06497 0.05864 -0.0454 1.0000 0.0417
-5.750 -0.4006 0.06146 0.05507 -0.0455 1.0000 0.0409
-5.500 -0.3930 0.05779 0.05127 -0.0461 1.0000 0.0402
-5.250 -0.3822 0.05399 0.04727 -0.0470 1.0000 0.0395
-5.000 -0.3678 0.05012 0.04311 -0.0482 1.0000 0.0389
-4.750 -0.3502 0.04639 0.03903 -0.0493 1.0000 0.0385
-4.500 -0.3295 0.04276 0.03496 -0.0503 1.0000 0.0382
-4.250 -0.3066 0.03944 0.03115 -0.0511 1.0000 0.0383
-4.000 -0.2819 0.03659 0.02776 -0.0517 1.0000 0.0400
-3.750 -0.2553 0.03432 0.02473 -0.0518 1.0000 0.0427
-3.500 -0.2260 0.03175 0.02195 -0.0531 0.9977 0.0457
-3.250 -0.1905 0.02967 0.01941 -0.0547 0.9937 0.0483
-3.000 -0.1561 0.02790 0.01725 -0.0555 0.9893 0.0522
-2.750 -0.1220 0.02656 0.01572 -0.0567 0.9851 0.0625
-2.500 -0.0908 0.02539 0.01438 -0.0572 0.9796 0.0758
-2.250 -0.0556 0.02431 0.01318 -0.0588 0.9749 0.1031
-2.000 -0.0205 0.02322 0.01213 -0.0608 0.9697 0.1465
-1.750 0.0086 0.02088 0.01183 -0.0619 0.9656 0.5616
-1.500 0.0264 0.02066 0.01203 -0.0580 0.9589 0.7738
-1.250 0.0561 0.02004 0.01157 -0.0567 0.9505 1.0000
-1.000 0.0943 0.02031 0.01137 -0.0595 0.9439 1.0000
-0.750 0.1288 0.02056 0.01121 -0.0616 0.9360 1.0000
-0.500 0.1641 0.02084 0.01116 -0.0637 0.9285 1.0000
-0.250 0.2004 0.02111 0.01116 -0.0658 0.9210 1.0000
0.000 0.2327 0.02139 0.01121 -0.0673 0.9122 1.0000
0.250 0.2723 0.02165 0.01125 -0.0699 0.9053 1.0000
0.500 0.3024 0.02192 0.01136 -0.0708 0.8952 1.0000
0.750 0.3361 0.02217 0.01149 -0.0723 0.8862 1.0000
1.000 0.3746 0.02238 0.01158 -0.0745 0.8783 1.0000
1.250 0.4045 0.02263 0.01176 -0.0751 0.8676 1.0000
1.500 0.4370 0.02285 0.01194 -0.0762 0.8576 1.0000
1.750 0.4761 0.02295 0.01203 -0.0782 0.8497 1.0000
2.000 0.5054 0.02315 0.01223 -0.0785 0.8381 1.0000
2.250 0.5356 0.02330 0.01239 -0.0789 0.8260 1.0000
2.500 0.5672 0.02335 0.01247 -0.0792 0.8132 1.0000
2.750 0.5992 0.02331 0.01254 -0.0795 0.7995 1.0000
3.000 0.6307 0.02325 0.01254 -0.0796 0.7855 1.0000
3.250 0.6617 0.02317 0.01254 -0.0795 0.7711 1.0000
3.500 0.6925 0.02307 0.01253 -0.0794 0.7563 1.0000
3.750 0.7237 0.02289 0.01254 -0.0791 0.7407 1.0000
4.000 0.7493 0.02289 0.01265 -0.0781 0.7211 1.0000
4.250 0.7783 0.02271 0.01259 -0.0774 0.7015 1.0000
4.500 0.8049 0.02263 0.01264 -0.0763 0.6790 1.0000
4.750 0.8327 0.02249 0.01262 -0.0754 0.6551 1.0000
5.000 0.8588 0.02246 0.01278 -0.0742 0.6278 1.0000
5.250 0.8836 0.02252 0.01295 -0.0729 0.5965 1.0000
5.500 0.9092 0.02259 0.01307 -0.0716 0.5621 1.0000
5.750 0.9326 0.02284 0.01334 -0.0701 0.5233 1.0000
6.000 0.9549 0.02325 0.01370 -0.0686 0.4825 1.0000
6.250 0.9757 0.02386 0.01430 -0.0670 0.4412 1.0000
6.500 0.9949 0.02464 0.01500 -0.0654 0.4018 1.0000
6.750 1.0131 0.02556 0.01584 -0.0637 0.3649 1.0000
7.000 1.0301 0.02657 0.01681 -0.0621 0.3296 1.0000
7.250 1.0459 0.02767 0.01784 -0.0604 0.2964 1.0000
7.500 1.0607 0.02883 0.01899 -0.0587 0.2638 1.0000
7.750 1.0744 0.03007 0.02022 -0.0570 0.2330 1.0000
8.000 1.0872 0.03137 0.02162 -0.0552 0.2041 1.0000
8.250 1.0990 0.03279 0.02305 -0.0534 0.1767 1.0000
8.500 1.1101 0.03434 0.02463 -0.0516 0.1507 1.0000
8.750 1.1224 0.03611 0.02647 -0.0498 0.1287 1.0000
9.000 1.1297 0.03789 0.02822 -0.0477 0.1097 1.0000
9.250 1.1389 0.03992 0.03034 -0.0457 0.0927 1.0000
9.500 1.1443 0.04205 0.03256 -0.0436 0.0769 1.0000
9.750 1.1443 0.04419 0.03472 -0.0416 0.0620 1.0000
10.000 1.1462 0.04681 0.03745 -0.0398 0.0509 1.0000
10.250 1.1464 0.04962 0.04039 -0.0382 0.0423 1.0000
10.500 1.1463 0.05250 0.04338 -0.0368 0.0371 1.0000
10.750 1.1473 0.05578 0.04688 -0.0355 0.0333 1.0000
11.000 1.1486 0.05915 0.05060 -0.0343 0.0301 1.0000
11.250 1.1467 0.06274 0.05443 -0.0336 0.0281 1.0000
11.500 1.1432 0.06655 0.05846 -0.0332 0.0269 1.0000
11.750 1.1379 0.07069 0.06280 -0.0331 0.0261 1.0000
12.000 1.1298 0.07535 0.06766 -0.0336 0.0254 1.0000
12.250 1.1205 0.08041 0.07306 -0.0346 0.0251 1.0000
12.500 1.1080 0.08614 0.07899 -0.0363 0.0249 1.0000
12.750 1.0942 0.09232 0.08542 -0.0390 0.0248 1.0000
13.000 1.0792 0.09911 0.09231 -0.0424 0.0249 1.0000
13.500 1.0465 0.11515 0.10886 -0.0520 0.0254 1.0000
13.750 1.0182 0.12862 0.12263 -0.0609 0.0268 1.0000
14.000 0.9902 0.14392 0.13797 -0.0699 0.0294 1.0000
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Polar data table (+)
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