HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 500,000 Max Cl/Cd: 123.58 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq358-il-500000.txt Download as CSV file: xf-hq358-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3433 0.09366 0.09149 -0.0324 1.0000 0.0096
-8.000 -0.3506 0.09191 0.08980 -0.0308 1.0000 0.0097
-7.750 -0.3623 0.09049 0.08842 -0.0277 1.0000 0.0096
-7.500 -0.3502 0.08697 0.08492 -0.0319 0.9976 0.0099
-7.250 -0.3309 0.08253 0.08048 -0.0384 0.9938 0.0100
-7.000 -0.3090 0.07741 0.07537 -0.0461 0.9884 0.0100
-6.750 -0.2815 0.07171 0.06966 -0.0559 0.9846 0.0101
-6.500 -0.2481 0.06513 0.06303 -0.0682 0.9821 0.0101
-6.250 -0.2220 0.05936 0.05719 -0.0766 0.9758 0.0101
-6.000 -0.1973 0.04944 0.04713 -0.0886 0.9717 0.0109
-5.750 -0.1668 0.04539 0.04298 -0.0945 0.9700 0.0117
-5.500 -0.1368 0.04145 0.03890 -0.0993 0.9662 0.0127
-5.250 -0.1063 0.03741 0.03466 -0.1032 0.9612 0.0150
-5.000 -0.0647 0.03549 0.03245 -0.1055 0.9583 0.0178
-3.000 0.1550 0.01282 0.00742 -0.1103 0.9169 0.0159
-2.750 0.1816 0.01113 0.00552 -0.1095 0.9110 0.0142
-2.500 0.2086 0.01003 0.00428 -0.1090 0.9051 0.0138
-2.250 0.2359 0.00932 0.00346 -0.1086 0.8996 0.0148
-2.000 0.2630 0.00886 0.00288 -0.1082 0.8920 0.0171
-1.750 0.2899 0.00846 0.00240 -0.1078 0.8834 0.0238
-1.500 0.3173 0.00799 0.00203 -0.1075 0.8749 0.0876
-1.250 0.3424 0.00681 0.00187 -0.1077 0.8655 0.4460
-1.000 0.3677 0.00638 0.00192 -0.1072 0.8574 0.6277
-0.750 0.3929 0.00623 0.00194 -0.1064 0.8494 0.7139
-0.500 0.4188 0.00617 0.00193 -0.1057 0.8405 0.7525
-0.250 0.4449 0.00611 0.00188 -0.1051 0.8318 0.7812
0.000 0.4696 0.00602 0.00185 -0.1041 0.8222 0.8201
0.250 0.4940 0.00590 0.00180 -0.1032 0.8124 0.8535
0.500 0.5189 0.00579 0.00174 -0.1023 0.8035 0.8835
0.750 0.5525 0.00561 0.00163 -0.1033 0.7944 1.0000
1.000 0.5806 0.00566 0.00162 -0.1034 0.7837 1.0000
1.250 0.6085 0.00572 0.00163 -0.1035 0.7729 1.0000
1.500 0.6360 0.00579 0.00164 -0.1034 0.7612 1.0000
1.750 0.6634 0.00586 0.00165 -0.1033 0.7487 1.0000
2.000 0.6906 0.00595 0.00169 -0.1031 0.7353 1.0000
2.250 0.7175 0.00605 0.00173 -0.1029 0.7200 1.0000
2.500 0.7442 0.00616 0.00181 -0.1027 0.7034 1.0000
2.750 0.7705 0.00629 0.00188 -0.1023 0.6845 1.0000
3.000 0.7965 0.00645 0.00196 -0.1019 0.6616 1.0000
3.250 0.8218 0.00665 0.00206 -0.1014 0.6334 1.0000
3.500 0.8466 0.00689 0.00218 -0.1008 0.5981 1.0000
3.750 0.8704 0.00722 0.00234 -0.1000 0.5549 1.0000
4.000 0.8931 0.00765 0.00259 -0.0991 0.5033 1.0000
4.250 0.9151 0.00818 0.00287 -0.0982 0.4467 1.0000
4.500 0.9370 0.00876 0.00319 -0.0973 0.3911 1.0000
4.750 0.9596 0.00929 0.00352 -0.0965 0.3446 1.0000
5.000 0.9811 0.00994 0.00388 -0.0956 0.2911 1.0000
5.250 1.0042 0.01043 0.00426 -0.0950 0.2593 1.0000
5.500 1.0281 0.01085 0.00460 -0.0945 0.2346 1.0000
5.750 1.0510 0.01136 0.00494 -0.0938 0.1969 1.0000
6.000 1.0707 0.01224 0.00542 -0.0928 0.1281 1.0000
6.250 1.0845 0.01384 0.00642 -0.0909 0.0357 1.0000
6.500 1.1029 0.01503 0.00750 -0.0892 0.0082 1.0000
6.750 1.1251 0.01570 0.00830 -0.0882 0.0073 1.0000
7.000 1.1462 0.01648 0.00926 -0.0870 0.0068 1.0000
7.250 1.1657 0.01743 0.01035 -0.0856 0.0067 1.0000
7.500 1.1834 0.01854 0.01161 -0.0838 0.0066 1.0000
7.750 1.1991 0.01985 0.01308 -0.0818 0.0066 1.0000
8.000 1.2132 0.02139 0.01477 -0.0795 0.0067 1.0000
8.250 1.2269 0.02316 0.01671 -0.0772 0.0069 1.0000
8.500 1.2413 0.02533 0.01906 -0.0751 0.0072 1.0000
8.750 1.2579 0.02729 0.02120 -0.0734 0.0071 1.0000
9.000 1.2745 0.02890 0.02297 -0.0719 0.0067 1.0000
9.250 1.2896 0.03047 0.02468 -0.0702 0.0062 1.0000
9.500 1.3026 0.03353 0.02804 -0.0682 0.0064 1.0000
9.750 1.3108 0.03697 0.03183 -0.0656 0.0066 1.0000
10.000 1.3105 0.04130 0.03660 -0.0621 0.0070 1.0000
10.250 1.2978 0.04583 0.04151 -0.0574 0.0076 1.0000
10.750 1.1940 0.04612 0.04251 -0.0443 0.0078 1.0000
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