HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 500,000 Max Cl/Cd: 116.5 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq308-il-500000.txt Download as CSV file: xf-hq308-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3687 0.08456 0.08245 -0.0335 1.0000 0.0104
-7.500 -0.3809 0.08276 0.08072 -0.0311 1.0000 0.0104
-7.250 -0.4022 0.08197 0.08000 -0.0267 1.0000 0.0104
-7.000 -0.3770 0.07589 0.07391 -0.0364 0.9963 0.0105
-6.750 -0.3487 0.06906 0.06705 -0.0483 0.9920 0.0105
-6.500 -0.3276 0.05825 0.05614 -0.0623 0.9861 0.0110
-6.250 -0.3004 0.05235 0.05013 -0.0703 0.9832 0.0115
-6.000 -0.2737 0.04807 0.04572 -0.0757 0.9792 0.0121
-5.750 -0.2447 0.04372 0.04122 -0.0808 0.9748 0.0130
-5.500 -0.2106 0.03907 0.03635 -0.0861 0.9721 0.0141
-5.250 -0.1724 0.03453 0.03151 -0.0906 0.9702 0.0165
-5.000 -0.1319 0.03277 0.02941 -0.0924 0.9677 0.0183
-3.500 0.0365 0.01350 0.00813 -0.0966 0.9361 0.0162
-3.250 0.0642 0.01168 0.00607 -0.0961 0.9307 0.0147
-3.000 0.0905 0.01048 0.00473 -0.0954 0.9246 0.0142
-2.750 0.1172 0.00967 0.00381 -0.0949 0.9182 0.0147
-2.500 0.1444 0.00911 0.00313 -0.0946 0.9121 0.0167
-2.250 0.1715 0.00862 0.00254 -0.0942 0.9050 0.0229
-2.000 0.1986 0.00814 0.00220 -0.0939 0.8980 0.0790
-1.750 0.2242 0.00732 0.00197 -0.0939 0.8899 0.2756
-1.500 0.2481 0.00641 0.00195 -0.0936 0.8812 0.5777
-1.250 0.2740 0.00623 0.00195 -0.0929 0.8743 0.6637
-1.000 0.3004 0.00618 0.00192 -0.0924 0.8660 0.6955
-0.750 0.3270 0.00613 0.00186 -0.0919 0.8580 0.7243
-0.500 0.3523 0.00606 0.00185 -0.0911 0.8483 0.7658
-0.250 0.3768 0.00598 0.00184 -0.0900 0.8377 0.8051
0.000 0.4022 0.00590 0.00181 -0.0893 0.8286 0.8314
0.250 0.4285 0.00585 0.00174 -0.0887 0.8202 0.8491
0.500 0.4539 0.00576 0.00170 -0.0880 0.8102 0.8729
0.750 0.4787 0.00561 0.00165 -0.0871 0.7992 0.9166
1.000 0.5155 0.00554 0.00156 -0.0889 0.7855 1.0000
1.250 0.5432 0.00560 0.00155 -0.0889 0.7727 1.0000
1.500 0.5708 0.00567 0.00156 -0.0888 0.7607 1.0000
1.750 0.5982 0.00575 0.00158 -0.0887 0.7477 1.0000
2.000 0.6254 0.00584 0.00161 -0.0886 0.7337 1.0000
2.250 0.6523 0.00593 0.00165 -0.0884 0.7178 1.0000
2.500 0.6790 0.00605 0.00171 -0.0881 0.7003 1.0000
2.750 0.7056 0.00617 0.00180 -0.0878 0.6804 1.0000
3.000 0.7317 0.00633 0.00188 -0.0874 0.6580 1.0000
3.250 0.7575 0.00651 0.00198 -0.0870 0.6315 1.0000
3.500 0.7829 0.00672 0.00210 -0.0865 0.5992 1.0000
3.750 0.8075 0.00701 0.00225 -0.0859 0.5601 1.0000
4.000 0.8303 0.00745 0.00248 -0.0850 0.5023 1.0000
4.250 0.8520 0.00804 0.00275 -0.0840 0.4337 1.0000
4.500 0.8736 0.00868 0.00308 -0.0831 0.3657 1.0000
4.750 0.8956 0.00933 0.00342 -0.0823 0.3035 1.0000
5.000 0.9175 0.01001 0.00379 -0.0815 0.2423 1.0000
5.250 0.9408 0.01053 0.00416 -0.0809 0.2027 1.0000
5.750 0.9881 0.01150 0.00489 -0.0798 0.1443 1.0000
6.000 1.0088 0.01233 0.00539 -0.0790 0.0890 1.0000
6.250 1.0290 0.01323 0.00600 -0.0780 0.0440 1.0000
6.500 1.0502 0.01404 0.00668 -0.0770 0.0186 1.0000
6.750 1.0713 0.01490 0.00750 -0.0759 0.0074 1.0000
7.000 1.0939 0.01555 0.00831 -0.0749 0.0066 1.0000
7.250 1.1155 0.01632 0.00922 -0.0738 0.0062 1.0000
7.500 1.1356 0.01725 0.01030 -0.0725 0.0059 1.0000
7.750 1.1543 0.01831 0.01151 -0.0710 0.0059 1.0000
8.000 1.1712 0.01958 0.01294 -0.0692 0.0059 1.0000
8.250 1.1863 0.02109 0.01463 -0.0672 0.0059 1.0000
8.500 1.2005 0.02286 0.01658 -0.0651 0.0060 1.0000
8.750 1.2147 0.02495 0.01889 -0.0630 0.0062 1.0000
9.000 1.2286 0.02756 0.02175 -0.0609 0.0064 1.0000
9.250 1.2406 0.03088 0.02539 -0.0587 0.0068 1.0000
9.500 1.2462 0.03538 0.03029 -0.0561 0.0072 1.0000
9.750 1.2581 0.03819 0.03327 -0.0542 0.0077 1.0000
10.000 1.2636 0.04074 0.03612 -0.0517 0.0078 1.0000
10.250 1.2674 0.04289 0.03850 -0.0489 0.0080 1.0000
10.500 1.2600 0.04567 0.04152 -0.0450 0.0079 1.0000
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