HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 500,000 Max Cl/Cd: 90.54 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq258-il-500000-n5.txt Download as CSV file: xf-hq258-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3916 0.08390 0.08172 -0.0312 1.0000 0.0079
-7.750 -0.3927 0.08067 0.07854 -0.0320 1.0000 0.0079
-7.500 -0.3978 0.07766 0.07557 -0.0322 1.0000 0.0079
-7.000 -0.3822 0.06825 0.06621 -0.0431 0.9915 0.0079
-6.750 -0.3571 0.06110 0.05898 -0.0542 0.9850 0.0079
-6.500 -0.3335 0.05475 0.05251 -0.0621 0.9778 0.0079
-6.250 -0.3179 0.04555 0.04308 -0.0714 0.9687 0.0062
-6.000 -0.2914 0.03945 0.03672 -0.0764 0.9614 0.0055
-5.750 -0.2671 0.03267 0.02954 -0.0793 0.9516 0.0048
-5.500 -0.2426 0.02337 0.01953 -0.0800 0.9419 0.0038
-5.250 -0.2163 0.02028 0.01601 -0.0803 0.9346 0.0037
-5.000 -0.1909 0.01793 0.01328 -0.0801 0.9265 0.0036
-4.750 -0.1646 0.01587 0.01083 -0.0800 0.9197 0.0036
-4.500 -0.1390 0.01374 0.00832 -0.0795 0.9119 0.0037
-4.250 -0.1130 0.01216 0.00645 -0.0790 0.9052 0.0038
-4.000 -0.0872 0.01096 0.00505 -0.0786 0.8977 0.0042
-3.750 -0.0606 0.01030 0.00428 -0.0783 0.8910 0.0048
-3.500 -0.0337 0.00980 0.00364 -0.0781 0.8836 0.0057
-3.250 -0.0066 0.00943 0.00317 -0.0779 0.8768 0.0072
-3.000 0.0205 0.00903 0.00266 -0.0777 0.8697 0.0101
-2.750 0.0480 0.00868 0.00224 -0.0775 0.8627 0.0154
-2.500 0.0753 0.00840 0.00200 -0.0774 0.8554 0.0367
-2.250 0.1027 0.00823 0.00181 -0.0773 0.8480 0.0528
-2.000 0.1299 0.00803 0.00165 -0.0772 0.8400 0.0822
-1.750 0.1565 0.00755 0.00146 -0.0773 0.8301 0.1880
-1.500 0.1830 0.00706 0.00131 -0.0773 0.8204 0.3175
-1.250 0.2093 0.00662 0.00122 -0.0773 0.8114 0.4574
-1.000 0.2361 0.00640 0.00119 -0.0771 0.8022 0.5364
-0.750 0.2624 0.00622 0.00119 -0.0768 0.7923 0.6188
-0.500 0.2879 0.00608 0.00123 -0.0761 0.7796 0.6960
-0.250 0.3138 0.00604 0.00123 -0.0756 0.7641 0.7344
0.000 0.3406 0.00607 0.00121 -0.0752 0.7485 0.7480
0.250 0.3677 0.00610 0.00119 -0.0750 0.7344 0.7590
0.500 0.3947 0.00613 0.00119 -0.0748 0.7202 0.7704
0.750 0.4215 0.00617 0.00119 -0.0745 0.7044 0.7822
1.000 0.4481 0.00622 0.00121 -0.0741 0.6864 0.7949
1.250 0.4744 0.00627 0.00124 -0.0738 0.6682 0.8090
1.500 0.5005 0.00633 0.00129 -0.0734 0.6497 0.8252
1.750 0.5261 0.00638 0.00133 -0.0728 0.6287 0.8447
2.000 0.5505 0.00643 0.00138 -0.0720 0.6023 0.8717
2.250 0.5774 0.00648 0.00143 -0.0717 0.5663 0.9375
2.500 0.6084 0.00672 0.00152 -0.0725 0.5257 1.0000
2.750 0.6336 0.00703 0.00168 -0.0721 0.4844 1.0000
3.000 0.6587 0.00737 0.00185 -0.0718 0.4420 1.0000
3.250 0.6840 0.00771 0.00203 -0.0714 0.4040 1.0000
3.500 0.7088 0.00811 0.00225 -0.0710 0.3593 1.0000
3.750 0.7328 0.00860 0.00250 -0.0706 0.3046 1.0000
4.000 0.7544 0.00940 0.00285 -0.0699 0.2197 1.0000
4.250 0.7785 0.00991 0.00318 -0.0694 0.1718 1.0000
4.500 0.8032 0.01034 0.00347 -0.0691 0.1408 1.0000
4.750 0.8265 0.01097 0.00386 -0.0685 0.0924 1.0000
5.000 0.8452 0.01224 0.00463 -0.0674 0.0089 1.0000
5.250 0.8701 0.01267 0.00507 -0.0669 0.0041 1.0000
5.500 0.8952 0.01308 0.00556 -0.0665 0.0034 1.0000
5.750 0.9197 0.01356 0.00613 -0.0659 0.0029 1.0000
6.000 0.9437 0.01411 0.00684 -0.0653 0.0026 1.0000
6.250 0.9669 0.01480 0.00766 -0.0645 0.0023 1.0000
6.500 0.9889 0.01564 0.00863 -0.0635 0.0022 1.0000
6.750 1.0101 0.01657 0.00968 -0.0625 0.0021 1.0000
7.000 1.0300 0.01766 0.01090 -0.0612 0.0021 1.0000
7.250 1.0492 0.01882 0.01219 -0.0599 0.0021 1.0000
7.500 1.0678 0.02010 0.01360 -0.0585 0.0021 1.0000
7.750 1.0863 0.02145 0.01509 -0.0571 0.0021 1.0000
8.000 1.1042 0.02296 0.01676 -0.0556 0.0021 1.0000
8.250 1.1222 0.02446 0.01843 -0.0543 0.0021 1.0000
8.500 1.1393 0.02616 0.02033 -0.0528 0.0021 1.0000
8.750 1.1552 0.02802 0.02241 -0.0512 0.0022 1.0000
9.000 1.1692 0.03011 0.02481 -0.0494 0.0022 1.0000
9.250 1.1804 0.03251 0.02751 -0.0473 0.0023 1.0000
9.500 1.1876 0.03531 0.03065 -0.0448 0.0024 1.0000
9.750 1.1890 0.03865 0.03434 -0.0418 0.0025 1.0000
10.000 1.1824 0.04199 0.03802 -0.0380 0.0026 1.0000
10.250 1.1688 0.04537 0.04169 -0.0339 0.0027 1.0000
10.500 1.1536 0.04888 0.04547 -0.0307 0.0028 1.0000
10.750 1.1373 0.05274 0.04955 -0.0288 0.0029 1.0000
11.000 1.1208 0.05696 0.05398 -0.0280 0.0029 1.0000
11.250 1.1012 0.06214 0.05937 -0.0286 0.0030 1.0000
11.500 1.0833 0.06774 0.06514 -0.0306 0.0030 1.0000
11.750 1.0643 0.07441 0.07198 -0.0342 0.0030 1.0000
12.000 1.0495 0.08132 0.07902 -0.0388 0.0030 1.0000
12.250 1.0316 0.09032 0.08817 -0.0453 0.0030 1.0000
12.500 1.0144 0.10075 0.09871 -0.0526 0.0029 1.0000
12.750 0.9967 0.11243 0.11048 -0.0599 0.0029 1.0000
13.000 0.9777 0.12498 0.12308 -0.0666 0.0029 1.0000
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Polar data table (+)
Polar graphs
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