HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il) Reynolds number: 50,000 Max Cl/Cd: 30.24 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3513-il-50000.txt Download as CSV file: xf-hq3513-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/13 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3301 0.11952 0.11294 -0.0357 1.0000 0.2395
-9.500 -0.3078 0.11450 0.10793 -0.0336 1.0000 0.2498
-9.250 -0.3441 0.11581 0.10946 -0.0327 1.0000 0.2553
-9.000 -0.3205 0.11090 0.10454 -0.0304 1.0000 0.2680
-8.750 -0.3187 0.10819 0.10189 -0.0282 1.0000 0.2774
-8.500 -0.3501 0.10886 0.10276 -0.0257 1.0000 0.2855
-8.250 -0.3452 0.10608 0.10002 -0.0230 1.0000 0.2999
-8.000 -0.3423 0.10361 0.09760 -0.0202 1.0000 0.3136
-7.750 -0.3450 0.10162 0.09570 -0.0173 1.0000 0.3274
-7.500 -0.3496 0.09976 0.09392 -0.0143 1.0000 0.3410
-7.250 -0.3562 0.09803 0.09227 -0.0113 1.0000 0.3544
-6.750 -0.3746 0.09496 0.08939 -0.0049 1.0000 0.3818
-6.500 -0.3764 0.09305 0.08754 -0.0017 1.0000 0.3993
-6.250 -0.3850 0.09174 0.08631 0.0020 1.0000 0.4193
-6.000 -0.4035 0.09109 0.08578 0.0063 1.0000 0.4371
-5.750 -0.4244 0.09048 0.08528 0.0111 1.0000 0.4535
-5.500 -0.5154 0.06287 0.05666 -0.0392 1.0000 0.1634
-5.250 -0.4998 0.05697 0.05052 -0.0409 1.0000 0.1512
-5.000 -0.4804 0.05226 0.04536 -0.0428 1.0000 0.1439
-4.750 -0.4565 0.04712 0.03949 -0.0454 1.0000 0.1375
-4.500 -0.4344 0.04404 0.03600 -0.0461 1.0000 0.1410
-4.250 -0.4097 0.04114 0.03251 -0.0469 1.0000 0.1445
-4.000 -0.3854 0.03866 0.02953 -0.0472 1.0000 0.1516
-3.750 -0.3620 0.03683 0.02741 -0.0471 1.0000 0.1596
-3.500 -0.3388 0.03518 0.02550 -0.0468 1.0000 0.1692
-3.250 -0.3144 0.03394 0.02383 -0.0464 1.0000 0.1784
-3.000 -0.2928 0.03283 0.02272 -0.0458 1.0000 0.1911
-2.750 -0.2707 0.03185 0.02169 -0.0449 1.0000 0.2028
-2.500 -0.2494 0.03114 0.02096 -0.0441 1.0000 0.2222
-2.250 -0.2278 0.03037 0.02032 -0.0433 1.0000 0.2469
-2.000 -0.2027 0.02941 0.01973 -0.0433 1.0000 0.3020
-1.750 -0.1956 0.02834 0.02096 -0.0370 1.0000 0.6697
-1.500 -0.2020 0.02877 0.02152 -0.0277 1.0000 0.7780
-1.250 -0.2043 0.02870 0.02147 -0.0203 1.0000 0.8464
-1.000 -0.1902 0.02842 0.02125 -0.0164 1.0000 0.9315
-0.750 -0.1582 0.02832 0.02089 -0.0196 1.0000 1.0000
-0.500 -0.1349 0.02870 0.02095 -0.0215 1.0000 1.0000
-0.250 -0.1106 0.02924 0.02117 -0.0234 1.0000 1.0000
0.000 -0.0863 0.02988 0.02153 -0.0251 1.0000 1.0000
0.250 -0.0624 0.03060 0.02200 -0.0268 1.0000 1.0000
0.500 -0.0107 0.03248 0.02354 -0.0334 0.9863 1.0000
0.750 0.0423 0.03440 0.02517 -0.0400 0.9706 1.0000
1.000 0.0829 0.03579 0.02632 -0.0442 0.9572 1.0000
1.250 0.1209 0.03709 0.02743 -0.0479 0.9435 1.0000
1.500 0.1577 0.03836 0.02854 -0.0511 0.9294 1.0000
1.750 0.1942 0.03962 0.02966 -0.0542 0.9146 1.0000
2.000 0.2422 0.04109 0.03098 -0.0587 0.8963 1.0000
2.250 0.2738 0.04190 0.03169 -0.0604 0.8753 1.0000
2.500 0.3186 0.04287 0.03256 -0.0637 0.8540 1.0000
2.750 0.3634 0.04376 0.03337 -0.0667 0.8345 1.0000
3.000 0.3920 0.04452 0.03409 -0.0676 0.8158 1.0000
3.250 0.4256 0.04528 0.03482 -0.0690 0.7977 1.0000
3.500 0.4625 0.04595 0.03548 -0.0706 0.7801 1.0000
3.750 0.5024 0.04647 0.03600 -0.0723 0.7629 1.0000
4.000 0.5448 0.04679 0.03634 -0.0741 0.7461 1.0000
4.250 0.5648 0.04751 0.03709 -0.0734 0.7259 1.0000
4.500 0.5974 0.04787 0.03749 -0.0738 0.7072 1.0000
4.750 0.6373 0.04781 0.03749 -0.0747 0.6894 1.0000
5.000 0.6802 0.04745 0.03722 -0.0755 0.6725 1.0000
5.250 0.7241 0.04680 0.03665 -0.0762 0.6563 1.0000
5.500 0.7361 0.04780 0.03770 -0.0744 0.6335 1.0000
5.750 0.7729 0.04733 0.03734 -0.0742 0.6165 1.0000
6.000 0.8133 0.04642 0.03653 -0.0740 0.6007 1.0000
6.250 0.8541 0.04529 0.03553 -0.0736 0.5857 1.0000
6.500 0.8962 0.04411 0.03447 -0.0734 0.5709 1.0000
6.750 0.9445 0.04258 0.03309 -0.0738 0.5560 1.0000
7.000 0.9940 0.04119 0.03182 -0.0746 0.5409 1.0000
7.250 1.0416 0.03992 0.03065 -0.0752 0.5252 1.0000
7.500 1.0868 0.03901 0.02984 -0.0758 0.5092 1.0000
7.750 1.1312 0.03832 0.02919 -0.0766 0.4928 1.0000
8.000 1.1639 0.03849 0.02940 -0.0764 0.4766 1.0000
8.250 1.1867 0.03932 0.03033 -0.0755 0.4609 1.0000
8.500 1.2097 0.04019 0.03128 -0.0745 0.4455 1.0000
8.750 1.2324 0.04116 0.03233 -0.0736 0.4303 1.0000
9.000 1.2543 0.04221 0.03347 -0.0726 0.4153 1.0000
9.250 1.2754 0.04337 0.03474 -0.0715 0.4004 1.0000
9.500 1.2951 0.04462 0.03608 -0.0703 0.3855 1.0000
9.750 1.3136 0.04594 0.03750 -0.0690 0.3707 1.0000
10.000 1.3314 0.04736 0.03901 -0.0676 0.3559 1.0000
10.250 1.3480 0.04883 0.04058 -0.0662 0.3413 1.0000
10.500 1.3646 0.05040 0.04227 -0.0647 0.3268 1.0000
10.750 1.3312 0.05441 0.04664 -0.0592 0.3205 1.0000
11.000 1.3407 0.05640 0.04874 -0.0573 0.3079 1.0000
11.250 1.3551 0.05821 0.05064 -0.0558 0.2949 1.0000
11.500 1.3039 0.06353 0.05618 -0.0501 0.2934 1.0000
11.750 1.2280 0.07275 0.06549 -0.0470 0.2954 1.0000
12.250 1.3585 0.06838 0.06129 -0.0465 0.2532 1.0000
12.500 1.3104 0.07467 0.06774 -0.0433 0.2529 1.0000
12.750 0.8162 0.15578 0.14758 -0.0874 0.4203 1.0000
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