HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 100,000 Max Cl/Cd: 58.62 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3512-il-100000.txt Download as CSV file: xf-hq3512-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3497 0.10542 0.10085 -0.0431 1.0000 0.0943
-9.000 -0.3762 0.10450 0.10010 -0.0427 1.0000 0.0949
-8.750 -0.4032 0.10355 0.09928 -0.0413 1.0000 0.0952
-8.500 -0.3805 0.09838 0.09409 -0.0374 1.0000 0.0975
-8.250 -0.3790 0.09640 0.09214 -0.0342 1.0000 0.0996
-8.000 -0.3888 0.09481 0.09063 -0.0316 1.0000 0.1019
-7.750 -0.4045 0.09333 0.08924 -0.0292 1.0000 0.1035
-7.500 -0.4248 0.09196 0.08797 -0.0269 1.0000 0.1050
-7.250 -0.4489 0.09069 0.08680 -0.0244 1.0000 0.1060
-7.000 -0.4750 0.08825 0.08446 -0.0257 1.0000 0.1078
-6.750 -0.5106 0.08368 0.07978 -0.0354 1.0000 0.1096
-6.500 -0.5091 0.07934 0.07553 -0.0337 0.9998 0.1112
-6.250 -0.4851 0.07710 0.07336 -0.0307 0.9967 0.1153
-6.000 -0.4694 0.06959 0.06556 -0.0440 0.9886 0.1263
-5.750 -0.4448 0.06670 0.06274 -0.0442 0.9844 0.1323
-5.500 -0.4261 0.06192 0.05780 -0.0496 0.9780 0.1442
-5.250 -0.4028 0.05837 0.05414 -0.0531 0.9725 0.1603
-5.000 -0.3258 0.03246 0.02712 -0.0665 0.9544 0.0980
-4.750 -0.3173 0.03854 0.03131 -0.0672 0.9637 0.0675
-4.500 -0.3129 0.04500 0.03968 -0.0677 0.9567 0.1857
-4.250 -0.2451 0.03173 0.02354 -0.0716 0.9564 0.0689
-4.000 -0.2184 0.03045 0.02217 -0.0721 0.9507 0.0764
-3.750 -0.1843 0.02860 0.01997 -0.0732 0.9459 0.0850
-3.500 -0.1458 0.02748 0.01876 -0.0755 0.9420 0.1017
-3.250 -0.1203 0.02662 0.01784 -0.0754 0.9358 0.1152
-3.000 -0.0870 0.02577 0.01695 -0.0764 0.9306 0.1281
-2.750 -0.0472 0.02506 0.01637 -0.0787 0.9268 0.1468
-2.500 -0.0271 0.02456 0.01595 -0.0776 0.9190 0.1656
-2.250 0.0084 0.02318 0.01536 -0.0798 0.9145 0.2802
-2.000 0.0214 0.02268 0.01636 -0.0759 0.9078 0.6689
-1.750 0.0433 0.02312 0.01680 -0.0736 0.9009 0.7306
-1.500 0.0637 0.02345 0.01710 -0.0712 0.8940 0.7716
-1.250 0.0838 0.02361 0.01722 -0.0690 0.8866 0.8055
-1.000 0.1040 0.02369 0.01727 -0.0666 0.8800 0.8409
-0.750 0.1151 0.02358 0.01722 -0.0622 0.8720 0.8873
-0.500 0.1705 0.02344 0.01710 -0.0655 0.8688 0.9616
-0.250 0.2190 0.02365 0.01717 -0.0708 0.8607 1.0000
0.000 0.2603 0.02366 0.01702 -0.0742 0.8550 1.0000
0.250 0.2813 0.02395 0.01719 -0.0745 0.8450 1.0000
0.500 0.3295 0.02392 0.01702 -0.0786 0.8401 1.0000
0.750 0.3560 0.02416 0.01715 -0.0793 0.8292 1.0000
1.000 0.4170 0.02358 0.01646 -0.0845 0.8245 1.0000
1.250 0.4483 0.02350 0.01630 -0.0853 0.8125 1.0000
1.500 0.4873 0.02320 0.01593 -0.0870 0.8023 1.0000
1.750 0.5397 0.02245 0.01512 -0.0904 0.7968 1.0000
2.000 0.5675 0.02251 0.01513 -0.0905 0.7861 1.0000
2.250 0.6155 0.02183 0.01443 -0.0931 0.7816 1.0000
2.500 0.6416 0.02189 0.01447 -0.0928 0.7704 1.0000
2.750 0.6876 0.02116 0.01371 -0.0949 0.7654 1.0000
3.000 0.7150 0.02107 0.01364 -0.0946 0.7539 1.0000
3.250 0.7444 0.02090 0.01347 -0.0944 0.7428 1.0000
3.500 0.7832 0.02030 0.01286 -0.0953 0.7344 1.0000
3.750 0.8173 0.01984 0.01244 -0.0955 0.7235 1.0000
4.000 0.8467 0.01955 0.01217 -0.0951 0.7103 1.0000
4.250 0.8771 0.01922 0.01184 -0.0948 0.6964 1.0000
4.500 0.9081 0.01884 0.01150 -0.0945 0.6814 1.0000
4.750 0.9395 0.01844 0.01109 -0.0942 0.6649 1.0000
5.000 0.9648 0.01827 0.01094 -0.0931 0.6440 1.0000
5.250 0.9931 0.01799 0.01064 -0.0924 0.6214 1.0000
5.500 1.0171 0.01791 0.01052 -0.0911 0.5936 1.0000
5.750 1.0414 0.01790 0.01041 -0.0898 0.5627 1.0000
6.000 1.0628 0.01813 0.01050 -0.0882 0.5279 1.0000
6.250 1.0840 0.01854 0.01075 -0.0867 0.4944 1.0000
6.500 1.1053 0.01912 0.01114 -0.0855 0.4647 1.0000
6.750 1.1269 0.01980 0.01165 -0.0844 0.4395 1.0000
7.000 1.1490 0.02051 0.01223 -0.0835 0.4179 1.0000
7.250 1.1714 0.02127 0.01292 -0.0827 0.3989 1.0000
7.500 1.1928 0.02203 0.01366 -0.0817 0.3813 1.0000
7.750 1.2142 0.02279 0.01441 -0.0808 0.3650 1.0000
8.000 1.2352 0.02357 0.01518 -0.0799 0.3496 1.0000
8.250 1.2557 0.02435 0.01600 -0.0788 0.3345 1.0000
8.500 1.2760 0.02517 0.01684 -0.0778 0.3202 1.0000
8.750 1.2957 0.02603 0.01772 -0.0767 0.3060 1.0000
9.000 1.3151 0.02694 0.01867 -0.0756 0.2920 1.0000
9.250 1.3337 0.02790 0.01967 -0.0744 0.2778 1.0000
9.500 1.3514 0.02890 0.02075 -0.0731 0.2637 1.0000
9.750 1.3673 0.02990 0.02181 -0.0715 0.2495 1.0000
10.000 1.3809 0.03088 0.02285 -0.0696 0.2353 1.0000
10.250 1.3924 0.03182 0.02387 -0.0674 0.2216 1.0000
10.500 1.4008 0.03270 0.02481 -0.0648 0.2082 1.0000
10.750 1.4066 0.03353 0.02568 -0.0618 0.1958 1.0000
11.000 1.4064 0.03432 0.02655 -0.0581 0.1841 1.0000
11.250 1.4030 0.03531 0.02770 -0.0542 0.1725 1.0000
11.500 1.3995 0.03646 0.02898 -0.0507 0.1610 1.0000
11.750 1.3954 0.03779 0.03038 -0.0476 0.1495 1.0000
12.000 1.3903 0.03936 0.03200 -0.0449 0.1379 1.0000
12.250 1.3839 0.04123 0.03391 -0.0425 0.1262 1.0000
12.500 1.3768 0.04347 0.03616 -0.0405 0.1143 1.0000
12.750 1.3691 0.04608 0.03877 -0.0388 0.1027 1.0000
13.000 1.3602 0.04912 0.04190 -0.0375 0.0910 1.0000
13.250 1.3500 0.05260 0.04546 -0.0364 0.0798 1.0000
13.500 1.3381 0.05655 0.04948 -0.0357 0.0692 1.0000
13.750 1.3254 0.06087 0.05386 -0.0353 0.0601 1.0000
14.000 1.3151 0.06513 0.05807 -0.0350 0.0538 1.0000
14.250 1.3082 0.06926 0.06238 -0.0350 0.0485 1.0000
14.500 1.3052 0.07305 0.06606 -0.0346 0.0442 1.0000
14.750 1.3017 0.07718 0.07048 -0.0348 0.0415 1.0000
15.000 1.2997 0.08112 0.07459 -0.0351 0.0393 1.0000
15.250 1.2987 0.08493 0.07850 -0.0354 0.0375 1.0000
15.500 1.3043 0.08828 0.08183 -0.0350 0.0354 1.0000
15.750 1.2954 0.09351 0.08731 -0.0363 0.0347 1.0000
16.000 1.2836 0.09920 0.09332 -0.0384 0.0343 1.0000
16.250 1.2702 0.10538 0.09977 -0.0410 0.0339 1.0000
16.500 1.2552 0.11211 0.10676 -0.0443 0.0337 1.0000
16.750 1.2386 0.11942 0.11431 -0.0483 0.0337 1.0000
17.000 1.2201 0.12749 0.12258 -0.0531 0.0339 1.0000
17.250 1.2000 0.13634 0.13163 -0.0586 0.0341 1.0000
17.500 1.1796 0.14574 0.14120 -0.0647 0.0346 1.0000
17.750 1.1588 0.15575 0.15134 -0.0712 0.0351 1.0000
18.000 1.0578 0.19629 0.19194 -0.0968 0.0441 1.0000
18.250 1.0547 0.20418 0.19979 -0.1007 0.0444 1.0000
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