HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/8 AIRFOIL (hq208-il) Reynolds number: 100,000 Max Cl/Cd: 55.88 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq208-il-100000.txt Download as CSV file: xf-hq208-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/8 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4588 0.09217 0.08743 -0.0253 1.0000 0.0804
-8.000 -0.4726 0.08919 0.08458 -0.0304 1.0000 0.0816
-7.750 -0.4815 0.08508 0.08048 -0.0385 1.0000 0.0820
-7.500 -0.4582 0.08187 0.07734 -0.0275 1.0000 0.0890
-7.250 -0.4616 0.07792 0.07346 -0.0322 1.0000 0.0928
-7.000 -0.4673 0.07351 0.06899 -0.0397 1.0000 0.0948
-6.750 -0.4594 0.07001 0.06562 -0.0363 1.0000 0.1007
-6.500 -0.4102 0.05592 0.05193 -0.0338 1.0000 0.1155
-6.250 -0.4252 0.05209 0.04796 -0.0384 1.0000 0.1220
-5.750 -0.4442 0.05621 0.05171 -0.0395 1.0000 0.1292
-5.500 -0.4387 0.05286 0.04826 -0.0397 1.0000 0.1405
-5.250 -0.4311 0.04993 0.04519 -0.0393 1.0000 0.1537
-5.000 -0.4220 0.04722 0.04244 -0.0382 1.0000 0.1688
-4.750 -0.4124 0.04469 0.03977 -0.0378 1.0000 0.1929
-4.250 -0.3413 0.03116 0.02405 -0.0407 1.0000 0.0658
-4.000 -0.3149 0.02853 0.02056 -0.0392 1.0000 0.0554
-3.750 -0.2920 0.02539 0.01714 -0.0386 1.0000 0.0537
-3.500 -0.2678 0.02331 0.01469 -0.0376 1.0000 0.0537
-3.250 -0.2440 0.02150 0.01263 -0.0369 1.0000 0.0586
-3.000 -0.2200 0.02012 0.01114 -0.0360 1.0000 0.0634
-2.750 -0.1954 0.01894 0.00975 -0.0349 1.0000 0.0689
-2.500 -0.1723 0.01738 0.00841 -0.0341 1.0000 0.0866
-2.250 -0.1490 0.01599 0.00728 -0.0335 1.0000 0.1411
-2.000 -0.1396 0.01321 0.00725 -0.0292 1.0000 0.7375
-1.750 -0.1314 0.01307 0.00725 -0.0241 1.0000 0.8356
-1.500 -0.0986 0.01270 0.00690 -0.0243 1.0000 1.0000
-1.250 -0.0744 0.01285 0.00675 -0.0249 1.0000 1.0000
-1.000 -0.0506 0.01306 0.00669 -0.0253 1.0000 1.0000
-0.750 -0.0275 0.01331 0.00668 -0.0255 1.0000 1.0000
-0.500 -0.0030 0.01361 0.00679 -0.0260 0.9993 1.0000
-0.250 0.0416 0.01411 0.00708 -0.0302 0.9911 1.0000
0.000 0.0869 0.01462 0.00742 -0.0345 0.9829 1.0000
0.250 0.1285 0.01502 0.00767 -0.0379 0.9734 1.0000
0.500 0.1717 0.01543 0.00799 -0.0416 0.9643 1.0000
0.750 0.2171 0.01581 0.00830 -0.0456 0.9556 1.0000
1.000 0.2577 0.01607 0.00853 -0.0486 0.9443 1.0000
1.250 0.3054 0.01620 0.00864 -0.0525 0.9312 1.0000
1.500 0.3597 0.01608 0.00855 -0.0572 0.9169 1.0000
1.750 0.4086 0.01595 0.00848 -0.0609 0.9041 1.0000
2.000 0.4508 0.01589 0.00850 -0.0633 0.8923 1.0000
2.250 0.4907 0.01579 0.00848 -0.0651 0.8801 1.0000
2.500 0.5283 0.01565 0.00843 -0.0663 0.8671 1.0000
2.750 0.5631 0.01549 0.00842 -0.0668 0.8530 1.0000
3.000 0.5956 0.01529 0.00834 -0.0667 0.8374 1.0000
3.250 0.6268 0.01505 0.00820 -0.0661 0.8209 1.0000
3.500 0.6534 0.01487 0.00814 -0.0648 0.8005 1.0000
3.750 0.6814 0.01457 0.00793 -0.0634 0.7792 1.0000
4.000 0.7067 0.01432 0.00783 -0.0615 0.7524 1.0000
4.250 0.7303 0.01409 0.00768 -0.0593 0.7173 1.0000
4.500 0.7536 0.01384 0.00739 -0.0568 0.6700 1.0000
4.750 0.7745 0.01386 0.00726 -0.0543 0.6032 1.0000
5.000 0.7939 0.01424 0.00733 -0.0518 0.5207 1.0000
5.250 0.8124 0.01499 0.00767 -0.0497 0.4371 1.0000
5.500 0.8310 0.01589 0.00832 -0.0481 0.3672 1.0000
5.750 0.8484 0.01696 0.00906 -0.0464 0.2938 1.0000
6.000 0.8617 0.01864 0.01013 -0.0443 0.1913 1.0000
6.250 0.8774 0.02050 0.01151 -0.0424 0.1338 1.0000
6.500 0.8965 0.02225 0.01308 -0.0409 0.1128 1.0000
6.750 0.9176 0.02379 0.01461 -0.0398 0.0955 1.0000
7.000 0.9398 0.02572 0.01654 -0.0387 0.0815 1.0000
7.250 0.9580 0.02770 0.01853 -0.0377 0.0615 1.0000
7.500 0.9787 0.03042 0.02149 -0.0363 0.0475 1.0000
7.750 0.9989 0.03394 0.02505 -0.0356 0.0398 1.0000
8.000 1.0191 0.03692 0.02860 -0.0338 0.0378 1.0000
8.250 1.0349 0.04063 0.03289 -0.0319 0.0367 1.0000
8.500 1.0459 0.04471 0.03753 -0.0299 0.0366 1.0000
8.750 1.0519 0.04915 0.04249 -0.0276 0.0369 1.0000
9.000 1.0532 0.05375 0.04756 -0.0255 0.0376 1.0000
9.250 1.0506 0.05850 0.05267 -0.0235 0.0383 1.0000
9.500 1.0452 0.06350 0.05793 -0.0219 0.0391 1.0000
9.750 1.0481 0.06770 0.06238 -0.0204 0.0412 1.0000
10.000 1.0078 0.07173 0.06694 -0.0173 0.0432 1.0000
10.250 0.9781 0.07691 0.07233 -0.0175 0.0443 1.0000
10.500 0.9520 0.08292 0.07849 -0.0202 0.0451 1.0000
10.750 0.9252 0.09072 0.08640 -0.0258 0.0458 1.0000
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Polar data table (+)
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