HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 50,000 Max Cl/Cd: 35.57 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1585-il-50000.txt Download as CSV file: xf-hq1585-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5009 0.11434 0.10734 0.0017 1.0000 0.2522
-9.250 -0.5025 0.11137 0.10444 0.0008 1.0000 0.2621
-9.000 -0.5148 0.11006 0.10324 -0.0007 1.0000 0.2734
-8.750 -0.5000 0.10558 0.09876 0.0000 1.0000 0.2868
-8.500 -0.4876 0.10145 0.09464 0.0005 1.0000 0.2994
-8.250 -0.4851 0.09839 0.09163 0.0006 1.0000 0.3144
-8.000 -0.4900 0.09605 0.08939 0.0006 1.0000 0.3301
-7.750 -0.4671 0.09132 0.08463 0.0021 1.0000 0.3497
-7.500 -0.4601 0.08811 0.08146 0.0028 1.0000 0.3676
-7.250 -0.4658 0.08601 0.07947 0.0035 1.0000 0.3864
-7.000 -0.4638 0.08292 0.07646 0.0043 1.0000 0.4025
-6.750 -0.4558 0.07953 0.07307 0.0051 1.0000 0.4172
-6.500 -0.5252 0.06135 0.05481 -0.0338 1.0000 0.1901
-6.250 -0.5165 0.05228 0.04504 -0.0400 1.0000 0.1445
-6.000 -0.5050 0.04678 0.03896 -0.0414 1.0000 0.1341
-5.750 -0.4884 0.04290 0.03467 -0.0411 1.0000 0.1308
-5.500 -0.4707 0.03910 0.03050 -0.0406 1.0000 0.1273
-5.250 -0.4511 0.03553 0.02637 -0.0399 1.0000 0.1240
-5.000 -0.4298 0.03257 0.02289 -0.0389 1.0000 0.1234
-4.750 -0.4084 0.03037 0.02031 -0.0378 1.0000 0.1292
-4.500 -0.3863 0.02822 0.01780 -0.0367 1.0000 0.1351
-4.250 -0.3635 0.02631 0.01571 -0.0353 1.0000 0.1413
-4.000 -0.3407 0.02459 0.01387 -0.0338 1.0000 0.1510
-3.750 -0.3193 0.02323 0.01251 -0.0323 1.0000 0.1720
-3.500 -0.2973 0.02168 0.01108 -0.0306 1.0000 0.2010
-3.250 -0.2783 0.01922 0.00963 -0.0293 1.0000 0.3171
-3.000 -0.2883 0.01767 0.01033 -0.0182 1.0000 0.7137
-2.750 -0.2907 0.01772 0.01045 -0.0090 1.0000 0.8156
-2.500 -0.0801 0.01802 0.00929 -0.0336 1.0000 1.0000
-2.250 -0.0886 0.01768 0.00892 -0.0298 1.0000 1.0000
-2.000 -0.1012 0.01738 0.00858 -0.0251 1.0000 1.0000
-1.750 -0.1131 0.01708 0.00822 -0.0205 1.0000 1.0000
-1.500 -0.1158 0.01687 0.00786 -0.0171 1.0000 1.0000
-1.250 -0.1053 0.01680 0.00758 -0.0157 1.0000 1.0000
-1.000 -0.0884 0.01684 0.00740 -0.0151 1.0000 1.0000
-0.750 -0.0690 0.01696 0.00727 -0.0148 1.0000 1.0000
-0.500 -0.0487 0.01713 0.00724 -0.0146 1.0000 1.0000
-0.250 -0.0279 0.01734 0.00729 -0.0145 1.0000 1.0000
0.000 -0.0070 0.01760 0.00740 -0.0144 1.0000 1.0000
0.250 0.0139 0.01790 0.00757 -0.0142 1.0000 1.0000
0.500 0.0348 0.01823 0.00778 -0.0141 1.0000 1.0000
0.750 0.0555 0.01860 0.00806 -0.0140 1.0000 1.0000
1.000 0.0760 0.01902 0.00840 -0.0140 1.0000 1.0000
1.250 0.0962 0.01948 0.00881 -0.0139 1.0000 1.0000
1.500 0.1162 0.01998 0.00928 -0.0138 1.0000 1.0000
1.750 0.1358 0.02054 0.00981 -0.0138 1.0000 1.0000
2.000 0.1550 0.02115 0.01042 -0.0139 1.0000 1.0000
2.250 0.1738 0.02182 0.01111 -0.0139 1.0000 1.0000
2.500 0.1984 0.02267 0.01201 -0.0153 0.9967 1.0000
2.750 0.2635 0.02420 0.01370 -0.0241 0.9725 1.0000
3.000 0.3282 0.02543 0.01513 -0.0320 0.9448 1.0000
3.250 0.3924 0.02634 0.01632 -0.0391 0.9154 1.0000
3.500 0.4552 0.02688 0.01718 -0.0451 0.8856 1.0000
3.750 0.5167 0.02702 0.01773 -0.0501 0.8541 1.0000
4.000 0.5737 0.02677 0.01787 -0.0532 0.8197 1.0000
4.250 0.6318 0.02580 0.01731 -0.0546 0.7844 1.0000
4.500 0.6720 0.02470 0.01656 -0.0525 0.7430 1.0000
4.750 0.7011 0.02372 0.01578 -0.0489 0.6952 1.0000
5.000 0.7305 0.02251 0.01465 -0.0447 0.6434 1.0000
5.250 0.7517 0.02166 0.01364 -0.0398 0.5745 1.0000
5.500 0.7668 0.02156 0.01313 -0.0350 0.4888 1.0000
5.750 0.7807 0.02254 0.01358 -0.0315 0.3992 1.0000
6.000 0.7927 0.02456 0.01486 -0.0284 0.2973 1.0000
6.250 0.8119 0.02730 0.01685 -0.0264 0.2210 1.0000
6.500 0.8365 0.02950 0.01899 -0.0253 0.1852 1.0000
6.750 0.8629 0.03174 0.02113 -0.0246 0.1645 1.0000
7.000 0.8904 0.03446 0.02396 -0.0240 0.1516 1.0000
7.250 0.9128 0.03700 0.02674 -0.0230 0.1375 1.0000
7.500 0.9337 0.04003 0.03026 -0.0217 0.1274 1.0000
7.750 0.9493 0.04342 0.03415 -0.0203 0.1175 1.0000
8.000 0.9671 0.04719 0.03804 -0.0193 0.1102 1.0000
8.250 0.9732 0.05133 0.04295 -0.0174 0.1060 1.0000
8.500 0.9780 0.05595 0.04810 -0.0160 0.1042 1.0000
8.750 0.9762 0.06124 0.05388 -0.0148 0.1052 1.0000
9.000 0.9699 0.06666 0.05969 -0.0139 0.1070 1.0000
9.250 0.9622 0.07204 0.06531 -0.0135 0.1087 1.0000
9.500 0.9561 0.07743 0.07085 -0.0133 0.1101 1.0000
9.750 0.9555 0.08301 0.07653 -0.0134 0.1114 1.0000
10.000 0.8759 0.09112 0.08481 -0.0196 0.1207 1.0000
10.250 0.8662 0.09834 0.09203 -0.0231 0.1261 1.0000
10.500 0.8344 0.11244 0.10603 -0.0346 0.1526 1.0000
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Polar data table (+)
Polar graphs
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