HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 500,000 Max Cl/Cd: 114.78 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq309-il-500000.txt Download as CSV file: xf-hq309-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3758 0.08395 0.08182 -0.0366 1.0000 0.0133
-8.000 -0.3817 0.08167 0.07960 -0.0356 1.0000 0.0136
-7.750 -0.3976 0.08020 0.07820 -0.0325 1.0000 0.0137
-7.500 -0.3967 0.07708 0.07510 -0.0347 0.9975 0.0142
-7.250 -0.3744 0.07107 0.06910 -0.0447 0.9920 0.0150
-7.000 -0.3475 0.06343 0.06142 -0.0589 0.9861 0.0159
-6.750 -0.3078 0.05526 0.05305 -0.0734 0.9825 0.0182
-6.500 -0.2777 0.05054 0.04810 -0.0797 0.9763 0.0188
-6.250 -0.2580 0.03997 0.03715 -0.0888 0.9717 0.0197
-6.000 -0.2291 0.03640 0.03346 -0.0929 0.9696 0.0207
-5.750 -0.2046 0.03370 0.03061 -0.0947 0.9637 0.0216
-5.500 -0.1758 0.03073 0.02742 -0.0969 0.9591 0.0231
-5.250 -0.1446 0.02769 0.02407 -0.0988 0.9555 0.0254
-5.000 -0.1147 0.02792 0.02402 -0.0979 0.9486 0.0284
-4.750 -0.0936 0.01578 0.01067 -0.0975 0.9422 0.0135
-4.500 -0.0682 0.01379 0.00834 -0.0966 0.9354 0.0128
-4.250 -0.0415 0.01230 0.00665 -0.0962 0.9300 0.0132
-4.000 -0.0156 0.01143 0.00567 -0.0957 0.9238 0.0143
-3.750 0.0109 0.01079 0.00496 -0.0953 0.9175 0.0156
-3.500 0.0380 0.01042 0.00452 -0.0950 0.9117 0.0177
-3.250 0.0645 0.00998 0.00401 -0.0946 0.9049 0.0189
-3.000 0.0913 0.00920 0.00312 -0.0943 0.8991 0.0249
-2.750 0.1181 0.00879 0.00273 -0.0939 0.8918 0.0511
-2.500 0.1455 0.00859 0.00252 -0.0938 0.8859 0.0686
-2.250 0.1719 0.00822 0.00231 -0.0936 0.8778 0.1157
-2.000 0.1956 0.00689 0.00209 -0.0937 0.8703 0.4658
-1.750 0.2213 0.00658 0.00206 -0.0932 0.8623 0.5812
-1.500 0.2481 0.00650 0.00204 -0.0928 0.8550 0.6277
-1.250 0.2752 0.00645 0.00200 -0.0924 0.8478 0.6582
-1.000 0.3023 0.00643 0.00198 -0.0921 0.8406 0.6828
-0.750 0.3290 0.00640 0.00195 -0.0917 0.8332 0.7117
-0.500 0.3548 0.00637 0.00198 -0.0910 0.8235 0.7467
-0.250 0.3804 0.00634 0.00198 -0.0902 0.8133 0.7767
0.000 0.4070 0.00632 0.00193 -0.0897 0.8041 0.7918
0.250 0.4340 0.00629 0.00190 -0.0894 0.7945 0.8037
0.500 0.4610 0.00627 0.00188 -0.0891 0.7854 0.8159
0.750 0.4876 0.00625 0.00184 -0.0887 0.7754 0.8296
1.000 0.5138 0.00622 0.00181 -0.0882 0.7637 0.8449
1.250 0.5394 0.00617 0.00181 -0.0876 0.7515 0.8635
1.500 0.5642 0.00609 0.00180 -0.0867 0.7398 0.8917
1.750 0.5976 0.00597 0.00177 -0.0877 0.7274 0.9651
2.000 0.6279 0.00604 0.00178 -0.0883 0.7141 1.0000
2.250 0.6554 0.00613 0.00183 -0.0883 0.6998 1.0000
2.500 0.6824 0.00624 0.00187 -0.0881 0.6839 1.0000
2.750 0.7092 0.00637 0.00193 -0.0879 0.6667 1.0000
3.000 0.7358 0.00650 0.00201 -0.0877 0.6468 1.0000
3.250 0.7618 0.00667 0.00210 -0.0873 0.6246 1.0000
3.500 0.7874 0.00686 0.00223 -0.0869 0.5980 1.0000
3.750 0.8126 0.00710 0.00236 -0.0864 0.5657 1.0000
4.000 0.8368 0.00740 0.00252 -0.0857 0.5289 1.0000
4.250 0.8604 0.00778 0.00273 -0.0850 0.4862 1.0000
4.500 0.8836 0.00821 0.00299 -0.0842 0.4409 1.0000
4.750 0.9062 0.00871 0.00328 -0.0834 0.3941 1.0000
5.000 0.9282 0.00927 0.00360 -0.0826 0.3409 1.0000
5.250 0.9502 0.00986 0.00394 -0.0818 0.2920 1.0000
5.500 0.9725 0.01042 0.00430 -0.0810 0.2507 1.0000
5.750 0.9952 0.01094 0.00468 -0.0804 0.2152 1.0000
6.000 1.0185 0.01140 0.00503 -0.0798 0.1879 1.0000
6.250 1.0411 0.01193 0.00542 -0.0791 0.1589 1.0000
6.500 1.0637 0.01245 0.00582 -0.0784 0.1321 1.0000
6.750 1.0854 0.01306 0.00627 -0.0776 0.1006 1.0000
7.000 1.1052 0.01385 0.00684 -0.0765 0.0652 1.0000
7.250 1.1253 0.01461 0.00748 -0.0755 0.0412 1.0000
7.500 1.1450 0.01541 0.00817 -0.0743 0.0233 1.0000
7.750 1.1636 0.01634 0.00902 -0.0729 0.0095 1.0000
8.000 1.1840 0.01706 0.00980 -0.0717 0.0074 1.0000
8.250 1.2037 0.01782 0.01065 -0.0705 0.0066 1.0000
8.500 1.2214 0.01876 0.01173 -0.0689 0.0061 1.0000
8.750 1.2374 0.01981 0.01293 -0.0671 0.0059 1.0000
9.000 1.2495 0.02117 0.01445 -0.0647 0.0057 1.0000
9.250 1.2591 0.02265 0.01609 -0.0620 0.0056 1.0000
9.500 1.2657 0.02419 0.01782 -0.0589 0.0056 1.0000
9.750 1.2719 0.02572 0.01949 -0.0558 0.0056 1.0000
10.000 1.2790 0.02723 0.02114 -0.0530 0.0056 1.0000
10.250 1.2854 0.02897 0.02303 -0.0503 0.0057 1.0000
10.500 1.2918 0.03079 0.02501 -0.0478 0.0057 1.0000
10.750 1.2988 0.03253 0.02690 -0.0455 0.0058 1.0000
11.000 1.3032 0.03465 0.02920 -0.0432 0.0058 1.0000
11.250 1.3040 0.03733 0.03210 -0.0408 0.0057 1.0000
11.500 1.3001 0.04063 0.03566 -0.0384 0.0057 1.0000
11.750 1.2949 0.04388 0.03914 -0.0363 0.0056 1.0000
12.000 1.2900 0.04657 0.04204 -0.0346 0.0055 1.0000
12.250 1.2818 0.05008 0.04577 -0.0333 0.0055 1.0000
12.500 1.2734 0.05364 0.04953 -0.0325 0.0055 1.0000
12.750 1.2660 0.05715 0.05324 -0.0323 0.0054 1.0000
13.000 1.2447 0.06322 0.05955 -0.0328 0.0055 1.0000
13.250 1.2243 0.06962 0.06617 -0.0342 0.0056 1.0000
13.500 1.2090 0.07537 0.07211 -0.0364 0.0056 1.0000
13.750 1.1993 0.08061 0.07748 -0.0389 0.0057 1.0000
14.000 1.1839 0.08738 0.08443 -0.0425 0.0057 1.0000
14.250 1.1695 0.09455 0.09175 -0.0468 0.0057 1.0000
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Polar data table (+)
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