HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 100,000 Max Cl/Cd: 48.38 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1512-il-100000-n5.txt Download as CSV file: xf-hq1512-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/12 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5690 0.08512 0.08004 -0.0379 1.0000 0.0277
-11.000 -0.6059 0.07205 0.06692 -0.0476 1.0000 0.0268
-10.750 -0.6393 0.06347 0.05821 -0.0540 1.0000 0.0264
-10.500 -0.6672 0.05762 0.05218 -0.0571 1.0000 0.0259
-10.250 -0.6898 0.05355 0.04793 -0.0574 1.0000 0.0259
-10.000 -0.7088 0.05029 0.04446 -0.0556 1.0000 0.0260
-9.750 -0.7198 0.04698 0.04089 -0.0538 1.0000 0.0261
-9.500 -0.7251 0.04387 0.03747 -0.0519 1.0000 0.0265
-9.250 -0.7260 0.04098 0.03426 -0.0498 1.0000 0.0270
-9.000 -0.7233 0.03829 0.03123 -0.0475 1.0000 0.0276
-8.750 -0.7174 0.03594 0.02854 -0.0453 1.0000 0.0285
-8.500 -0.7090 0.03402 0.02623 -0.0430 1.0000 0.0299
-8.250 -0.6996 0.03216 0.02423 -0.0409 1.0000 0.0313
-8.000 -0.6889 0.03082 0.02283 -0.0389 1.0000 0.0326
-7.750 -0.6778 0.02949 0.02133 -0.0366 1.0000 0.0338
-7.500 -0.6665 0.02820 0.01989 -0.0343 1.0000 0.0351
-7.250 -0.6537 0.02698 0.01850 -0.0321 0.9997 0.0368
-7.000 -0.6212 0.02550 0.01680 -0.0337 0.9936 0.0404
-6.750 -0.5905 0.02426 0.01555 -0.0353 0.9869 0.0443
-6.500 -0.5585 0.02307 0.01418 -0.0366 0.9807 0.0486
-6.250 -0.5280 0.02195 0.01304 -0.0379 0.9738 0.0550
-6.000 -0.4961 0.02102 0.01203 -0.0393 0.9676 0.0640
-5.750 -0.4654 0.02017 0.01115 -0.0405 0.9605 0.0761
-5.500 -0.4318 0.01929 0.01036 -0.0423 0.9553 0.0953
-5.250 -0.4033 0.01855 0.00967 -0.0430 0.9474 0.1197
-5.000 -0.3704 0.01778 0.00905 -0.0446 0.9421 0.1563
-4.750 -0.3437 0.01713 0.00856 -0.0450 0.9337 0.2008
-4.500 -0.3126 0.01640 0.00806 -0.0462 0.9280 0.2615
-4.250 -0.2881 0.01568 0.00767 -0.0461 0.9196 0.3356
-4.000 -0.2598 0.01506 0.00751 -0.0464 0.9138 0.4423
-3.750 -0.2346 0.01487 0.00754 -0.0456 0.9059 0.5183
-3.500 -0.2044 0.01481 0.00751 -0.0457 0.8999 0.5704
-3.250 -0.1774 0.01484 0.00750 -0.0452 0.8924 0.6044
-3.000 -0.1480 0.01486 0.00745 -0.0452 0.8860 0.6326
-2.750 -0.1211 0.01491 0.00746 -0.0446 0.8787 0.6558
-2.500 -0.0930 0.01494 0.00741 -0.0443 0.8719 0.6770
-2.250 -0.0658 0.01498 0.00740 -0.0438 0.8650 0.6939
-2.000 -0.0386 0.01501 0.00736 -0.0433 0.8579 0.7092
-1.750 -0.0112 0.01502 0.00731 -0.0429 0.8513 0.7238
-1.500 0.0144 0.01506 0.00732 -0.0421 0.8437 0.7393
-1.250 0.0409 0.01508 0.00732 -0.0413 0.8371 0.7551
-1.000 0.0660 0.01510 0.00731 -0.0405 0.8292 0.7686
-0.750 0.0934 0.01507 0.00722 -0.0402 0.8227 0.7800
-0.500 0.1192 0.01506 0.00720 -0.0395 0.8145 0.7883
-0.250 0.1470 0.01501 0.00710 -0.0394 0.8079 0.7976
0.000 0.1729 0.01500 0.00708 -0.0389 0.7996 0.8068
0.250 0.2005 0.01496 0.00703 -0.0386 0.7928 0.8157
0.500 0.2263 0.01494 0.00700 -0.0380 0.7841 0.8259
0.750 0.2526 0.01489 0.00695 -0.0374 0.7748 0.8354
1.000 0.2806 0.01476 0.00680 -0.0370 0.7656 0.8450
1.250 0.3057 0.01468 0.00674 -0.0361 0.7532 0.8559
1.500 0.3317 0.01459 0.00665 -0.0354 0.7406 0.8668
1.750 0.3587 0.01449 0.00657 -0.0348 0.7280 0.8779
2.000 0.3869 0.01442 0.00653 -0.0346 0.7163 0.8897
2.250 0.4171 0.01435 0.00648 -0.0347 0.7062 0.9022
2.500 0.4482 0.01433 0.00653 -0.0352 0.6939 0.9154
2.750 0.4820 0.01432 0.00659 -0.0363 0.6812 0.9294
3.000 0.5175 0.01431 0.00662 -0.0378 0.6672 0.9448
3.250 0.5545 0.01431 0.00666 -0.0396 0.6520 0.9616
3.500 0.5919 0.01430 0.00671 -0.0416 0.6351 0.9810
3.750 0.6250 0.01434 0.00677 -0.0428 0.6166 1.0000
4.000 0.6448 0.01445 0.00686 -0.0415 0.5969 1.0000
4.250 0.6667 0.01456 0.00693 -0.0403 0.5751 1.0000
4.500 0.6888 0.01471 0.00707 -0.0393 0.5492 1.0000
4.750 0.7110 0.01491 0.00719 -0.0381 0.5185 1.0000
5.000 0.7327 0.01518 0.00734 -0.0369 0.4829 1.0000
5.250 0.7533 0.01557 0.00756 -0.0356 0.4434 1.0000
5.500 0.7731 0.01606 0.00786 -0.0343 0.4024 1.0000
5.750 0.7923 0.01663 0.00824 -0.0329 0.3635 1.0000
6.000 0.8113 0.01725 0.00867 -0.0316 0.3286 1.0000
6.250 0.8304 0.01790 0.00916 -0.0304 0.2992 1.0000
6.500 0.8498 0.01853 0.00971 -0.0293 0.2746 1.0000
6.750 0.8691 0.01919 0.01028 -0.0282 0.2529 1.0000
7.000 0.8891 0.01978 0.01088 -0.0272 0.2312 1.0000
7.250 0.9081 0.02043 0.01148 -0.0260 0.2089 1.0000
7.500 0.9274 0.02106 0.01214 -0.0250 0.1843 1.0000
7.750 0.9455 0.02178 0.01282 -0.0237 0.1599 1.0000
8.000 0.9616 0.02265 0.01359 -0.0223 0.1361 1.0000
8.250 0.9767 0.02362 0.01447 -0.0208 0.1164 1.0000
8.500 0.9909 0.02466 0.01544 -0.0192 0.1021 1.0000
8.750 1.0047 0.02572 0.01649 -0.0176 0.0923 1.0000
9.000 1.0167 0.02686 0.01764 -0.0157 0.0856 1.0000
9.250 1.0291 0.02791 0.01877 -0.0138 0.0801 1.0000
9.500 1.0402 0.02900 0.01992 -0.0119 0.0751 1.0000
9.750 1.0492 0.03030 0.02120 -0.0099 0.0712 1.0000
10.000 1.0621 0.03143 0.02250 -0.0084 0.0676 1.0000
10.250 1.0739 0.03271 0.02388 -0.0068 0.0647 1.0000
10.500 1.0846 0.03406 0.02529 -0.0053 0.0621 1.0000
10.750 1.0949 0.03569 0.02690 -0.0039 0.0597 1.0000
11.000 1.1078 0.03708 0.02854 -0.0027 0.0575 1.0000
11.250 1.1191 0.03859 0.03024 -0.0014 0.0549 1.0000
11.500 1.1299 0.04020 0.03200 -0.0003 0.0529 1.0000
11.750 1.1398 0.04191 0.03382 0.0008 0.0511 1.0000
12.000 1.1482 0.04370 0.03567 0.0018 0.0492 1.0000
12.250 1.1555 0.04584 0.03793 0.0028 0.0472 1.0000
12.500 1.1569 0.04798 0.04039 0.0039 0.0453 1.0000
12.750 1.1568 0.05024 0.04289 0.0047 0.0430 1.0000
13.000 1.1562 0.05251 0.04530 0.0052 0.0410 1.0000
13.250 1.1547 0.05475 0.04758 0.0053 0.0389 1.0000
13.500 1.1541 0.05764 0.05056 0.0055 0.0374 1.0000
13.750 1.1457 0.06124 0.05451 0.0051 0.0360 1.0000
14.000 1.1365 0.06517 0.05873 0.0041 0.0344 1.0000
14.250 1.1275 0.06929 0.06306 0.0028 0.0329 1.0000
14.500 1.1185 0.07356 0.06749 0.0011 0.0316 1.0000
14.750 1.1095 0.07807 0.07213 -0.0010 0.0305 1.0000
15.000 1.1006 0.08285 0.07699 -0.0034 0.0296 1.0000
15.250 1.0911 0.08798 0.08220 -0.0059 0.0287 1.0000
15.500 1.0735 0.09519 0.08964 -0.0099 0.0285 1.0000
15.750 1.0521 0.10369 0.09838 -0.0149 0.0282 1.0000
16.000 1.0299 0.11286 0.10775 -0.0204 0.0282 1.0000
16.250 1.0060 0.12297 0.11802 -0.0266 0.0284 1.0000
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