HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 200,000 Max Cl/Cd: 79.55 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2590sm-il-200000.txt Download as CSV file: xf-hq2590sm-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9.0 smoothed by Eppler
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4170 0.09572 0.09207 -0.0319 1.0000 0.0435
-9.000 -0.4172 0.09223 0.08862 -0.0336 1.0000 0.0451
-8.750 -0.4242 0.08836 0.08482 -0.0376 1.0000 0.0471
-8.500 -0.3536 0.07307 0.06984 -0.0394 1.0000 0.0506
-8.250 -0.3507 0.07038 0.06718 -0.0383 1.0000 0.0521
-8.000 -0.3553 0.06721 0.06406 -0.0380 1.0000 0.0534
-7.750 -0.3663 0.06415 0.06107 -0.0373 1.0000 0.0545
-7.500 -0.3867 0.06192 0.05895 -0.0350 1.0000 0.0546
-7.250 -0.4955 0.06516 0.06167 -0.0470 1.0000 0.0489
-7.000 -0.4940 0.06229 0.05893 -0.0442 1.0000 0.0499
-6.750 -0.4934 0.06072 0.05743 -0.0414 1.0000 0.0512
-6.500 -0.4938 0.05875 0.05546 -0.0396 1.0000 0.0527
-6.250 -0.4735 0.05459 0.05111 -0.0439 0.9970 0.0570
-6.000 -0.3882 0.03316 0.02954 -0.0565 0.9836 0.0648
-5.750 -0.3664 0.02985 0.02607 -0.0587 0.9785 0.0690
-5.500 -0.3401 0.02498 0.02067 -0.0629 0.9740 0.0772
-5.250 -0.3103 0.02193 0.01757 -0.0652 0.9714 0.0822
-5.000 -0.2841 0.01911 0.01449 -0.0673 0.9669 0.0938
-4.750 -0.2572 0.01673 0.01185 -0.0690 0.9623 0.1072
-4.500 -0.2409 0.02409 0.01731 -0.0672 0.9707 0.0475
-4.250 -0.2109 0.02184 0.01473 -0.0679 0.9666 0.0472
-4.000 -0.1791 0.02041 0.01299 -0.0687 0.9626 0.0489
-3.750 -0.1457 0.01857 0.01097 -0.0698 0.9600 0.0497
-3.500 -0.1110 0.01726 0.00963 -0.0713 0.9578 0.0516
-3.250 -0.0740 0.01642 0.00878 -0.0732 0.9559 0.0552
-3.000 -0.0489 0.01598 0.00828 -0.0727 0.9498 0.0599
-2.750 -0.0168 0.01503 0.00738 -0.0738 0.9465 0.0659
-2.500 0.0189 0.01439 0.00676 -0.0756 0.9439 0.0788
-2.250 0.0560 0.01313 0.00605 -0.0781 0.9420 0.1955
-2.000 0.0742 0.01183 0.00634 -0.0769 0.9364 0.6247
-1.750 0.1083 0.01173 0.00637 -0.0775 0.9313 0.6999
-1.500 0.1509 0.01149 0.00623 -0.0793 0.9274 0.7564
-1.250 0.1771 0.01139 0.00617 -0.0781 0.9183 0.7887
-1.000 0.2108 0.01119 0.00601 -0.0781 0.9133 0.8241
-0.750 0.2318 0.01110 0.00597 -0.0758 0.9045 0.8529
-0.500 0.2625 0.01091 0.00575 -0.0758 0.8995 0.8708
-0.250 0.2877 0.01080 0.00564 -0.0749 0.8931 0.8868
0.000 0.3139 0.01064 0.00549 -0.0741 0.8868 0.9044
0.250 0.3460 0.01041 0.00525 -0.0744 0.8825 0.9232
0.500 0.3767 0.01031 0.00517 -0.0748 0.8746 0.9468
0.750 0.4222 0.01008 0.00493 -0.0781 0.8696 0.9700
1.000 0.4615 0.01000 0.00484 -0.0807 0.8617 1.0000
1.250 0.4917 0.00993 0.00471 -0.0812 0.8543 1.0000
1.500 0.5187 0.00996 0.00472 -0.0812 0.8444 1.0000
1.750 0.5477 0.00992 0.00466 -0.0812 0.8354 1.0000
2.000 0.5762 0.00988 0.00459 -0.0811 0.8253 1.0000
2.250 0.6030 0.00987 0.00458 -0.0806 0.8133 1.0000
2.500 0.6301 0.00985 0.00454 -0.0801 0.8005 1.0000
2.750 0.6570 0.00981 0.00451 -0.0795 0.7861 1.0000
3.000 0.6836 0.00976 0.00445 -0.0788 0.7693 1.0000
3.250 0.7096 0.00970 0.00437 -0.0779 0.7474 1.0000
3.500 0.7341 0.00965 0.00427 -0.0767 0.7144 1.0000
3.750 0.7580 0.00967 0.00419 -0.0754 0.6710 1.0000
4.000 0.7812 0.00982 0.00415 -0.0740 0.6090 1.0000
4.250 0.8019 0.01028 0.00421 -0.0723 0.5350 1.0000
4.500 0.8227 0.01091 0.00453 -0.0710 0.4808 1.0000
4.750 0.8447 0.01150 0.00491 -0.0700 0.4413 1.0000
5.000 0.8676 0.01202 0.00530 -0.0692 0.4094 1.0000
5.250 0.8908 0.01251 0.00570 -0.0684 0.3803 1.0000
5.500 0.9131 0.01302 0.00611 -0.0675 0.3453 1.0000
5.750 0.9349 0.01354 0.00650 -0.0666 0.3035 1.0000
6.000 0.9559 0.01415 0.00693 -0.0657 0.2536 1.0000
6.250 0.9748 0.01504 0.00748 -0.0645 0.1858 1.0000
6.500 0.9923 0.01620 0.00830 -0.0631 0.1330 1.0000
6.750 1.0106 0.01730 0.00921 -0.0618 0.1041 1.0000
7.000 1.0290 0.01840 0.01023 -0.0605 0.0829 1.0000
7.250 1.0466 0.01962 0.01140 -0.0589 0.0683 1.0000
7.500 1.0636 0.02096 0.01272 -0.0573 0.0595 1.0000
7.750 1.0824 0.02205 0.01382 -0.0561 0.0531 1.0000
8.000 1.1009 0.02357 0.01540 -0.0547 0.0492 1.0000
8.250 1.1218 0.02474 0.01668 -0.0537 0.0459 1.0000
8.500 1.1416 0.02595 0.01789 -0.0527 0.0425 1.0000
8.750 1.1626 0.02820 0.02022 -0.0519 0.0399 1.0000
9.000 1.1842 0.02972 0.02197 -0.0510 0.0381 1.0000
9.250 1.2044 0.03126 0.02370 -0.0499 0.0360 1.0000
9.500 1.2225 0.03262 0.02517 -0.0488 0.0338 1.0000
9.750 1.2412 0.03521 0.02783 -0.0481 0.0321 1.0000
10.000 1.2549 0.03915 0.03216 -0.0467 0.0311 1.0000
10.250 1.2649 0.04161 0.03501 -0.0446 0.0306 1.0000
10.500 1.2705 0.04429 0.03809 -0.0421 0.0299 1.0000
10.750 1.2717 0.04708 0.04128 -0.0393 0.0290 1.0000
11.000 1.2681 0.04990 0.04443 -0.0362 0.0282 1.0000
11.250 1.2586 0.05277 0.04758 -0.0327 0.0278 1.0000
11.500 1.2428 0.05638 0.05148 -0.0294 0.0278 1.0000
11.750 1.2239 0.06032 0.05571 -0.0269 0.0279 1.0000
12.000 1.2023 0.06478 0.06044 -0.0255 0.0281 1.0000
12.250 1.1787 0.06988 0.06578 -0.0254 0.0283 1.0000
12.500 1.1538 0.07570 0.07182 -0.0266 0.0286 1.0000
12.750 1.1276 0.08245 0.07877 -0.0295 0.0289 1.0000
13.000 1.1013 0.09022 0.08669 -0.0339 0.0293 1.0000
13.250 1.0735 0.09963 0.09626 -0.0404 0.0297 1.0000
13.500 1.0464 0.11036 0.10708 -0.0477 0.0305 1.0000
13.750 1.0244 0.12085 0.11760 -0.0538 0.0312 1.0000
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Polar data table (+)
Polar graphs
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