HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 500,000 Max Cl/Cd: 73.27 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1510-il-500000-n5.txt Download as CSV file: xf-hq1510-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7672 0.04764 0.04504 -0.0503 1.0000 0.0040
-11.000 -0.7886 0.04234 0.03958 -0.0535 1.0000 0.0039
-10.750 -0.8110 0.03850 0.03554 -0.0528 1.0000 0.0039
-10.500 -0.8214 0.03505 0.03179 -0.0513 1.0000 0.0040
-10.250 -0.8243 0.03182 0.02824 -0.0499 1.0000 0.0040
-10.000 -0.8192 0.02924 0.02535 -0.0485 1.0000 0.0041
-9.750 -0.8100 0.02706 0.02289 -0.0471 1.0000 0.0041
-9.500 -0.8022 0.02454 0.02004 -0.0453 1.0000 0.0043
-9.250 -0.7901 0.02269 0.01794 -0.0438 1.0000 0.0045
-9.000 -0.7744 0.02145 0.01654 -0.0424 1.0000 0.0046
-8.750 -0.7578 0.02040 0.01536 -0.0410 1.0000 0.0048
-8.500 -0.7292 0.01938 0.01421 -0.0420 0.9959 0.0051
-8.250 -0.7000 0.01828 0.01295 -0.0430 0.9904 0.0054
-8.000 -0.6692 0.01724 0.01175 -0.0443 0.9856 0.0057
-7.750 -0.6389 0.01634 0.01070 -0.0454 0.9800 0.0062
-7.500 -0.6074 0.01569 0.00994 -0.0466 0.9743 0.0067
-7.250 -0.5780 0.01463 0.00873 -0.0475 0.9672 0.0075
-7.000 -0.5473 0.01391 0.00792 -0.0485 0.9597 0.0081
-6.750 -0.5178 0.01328 0.00721 -0.0491 0.9506 0.0088
-6.500 -0.4884 0.01272 0.00655 -0.0497 0.9411 0.0095
-6.250 -0.4603 0.01225 0.00597 -0.0499 0.9302 0.0103
-6.000 -0.4337 0.01171 0.00535 -0.0497 0.9190 0.0120
-5.750 -0.4073 0.01132 0.00490 -0.0495 0.9087 0.0141
-5.500 -0.3811 0.01096 0.00446 -0.0492 0.8990 0.0172
-5.250 -0.3549 0.01065 0.00412 -0.0489 0.8894 0.0230
-5.000 -0.3288 0.01036 0.00382 -0.0486 0.8800 0.0298
-4.750 -0.3022 0.01016 0.00356 -0.0484 0.8715 0.0354
-4.500 -0.2757 0.00992 0.00332 -0.0482 0.8629 0.0429
-4.250 -0.2490 0.00972 0.00306 -0.0480 0.8549 0.0498
-4.000 -0.2224 0.00950 0.00285 -0.0477 0.8471 0.0617
-3.750 -0.1956 0.00928 0.00263 -0.0476 0.8394 0.0749
-3.250 -0.1420 0.00881 0.00223 -0.0473 0.8240 0.1176
-3.000 -0.1156 0.00853 0.00205 -0.0471 0.8165 0.1585
-2.750 -0.0892 0.00818 0.00188 -0.0470 0.8083 0.2162
-2.500 -0.0631 0.00780 0.00170 -0.0469 0.8004 0.2854
-2.250 -0.0375 0.00737 0.00154 -0.0467 0.7918 0.3783
-2.000 -0.0116 0.00700 0.00145 -0.0465 0.7833 0.4670
-1.750 0.0148 0.00681 0.00140 -0.0462 0.7751 0.5265
-1.500 0.0420 0.00670 0.00137 -0.0460 0.7662 0.5641
-1.250 0.0688 0.00662 0.00134 -0.0457 0.7556 0.6028
-1.000 0.0955 0.00657 0.00134 -0.0453 0.7430 0.6370
-0.750 0.1228 0.00656 0.00132 -0.0451 0.7311 0.6551
-0.500 0.1502 0.00656 0.00130 -0.0449 0.7200 0.6695
-0.250 0.1778 0.00656 0.00129 -0.0448 0.7087 0.6832
0.000 0.2052 0.00657 0.00130 -0.0446 0.6970 0.6974
0.250 0.2325 0.00659 0.00131 -0.0444 0.6853 0.7115
0.500 0.2599 0.00662 0.00132 -0.0442 0.6722 0.7221
0.750 0.2874 0.00666 0.00133 -0.0440 0.6586 0.7308
1.000 0.3148 0.00670 0.00136 -0.0439 0.6465 0.7389
1.250 0.3423 0.00675 0.00139 -0.0438 0.6333 0.7475
1.500 0.3695 0.00681 0.00143 -0.0436 0.6175 0.7562
1.750 0.3967 0.00687 0.00148 -0.0434 0.6008 0.7650
2.000 0.4235 0.00696 0.00154 -0.0431 0.5806 0.7747
2.250 0.4500 0.00706 0.00161 -0.0428 0.5569 0.7842
2.500 0.4761 0.00720 0.00170 -0.0424 0.5289 0.7941
2.750 0.5016 0.00740 0.00180 -0.0420 0.4941 0.8046
3.000 0.5264 0.00766 0.00193 -0.0414 0.4523 0.8157
3.250 0.5506 0.00798 0.00211 -0.0408 0.4033 0.8276
3.500 0.5739 0.00838 0.00232 -0.0401 0.3447 0.8409
3.750 0.5964 0.00886 0.00256 -0.0393 0.2835 0.8563
4.000 0.6202 0.00912 0.00277 -0.0386 0.2540 0.8753
4.250 0.6448 0.00926 0.00297 -0.0379 0.2378 0.9042
4.500 0.6781 0.00944 0.00318 -0.0391 0.2202 0.9533
4.750 0.7120 0.00973 0.00341 -0.0407 0.1996 1.0000
5.000 0.7371 0.01006 0.00364 -0.0404 0.1743 1.0000
5.250 0.7614 0.01047 0.00393 -0.0399 0.1438 1.0000
5.500 0.7849 0.01098 0.00427 -0.0394 0.1091 1.0000
5.750 0.8077 0.01157 0.00467 -0.0388 0.0767 1.0000
6.000 0.8316 0.01203 0.00504 -0.0383 0.0593 1.0000
6.250 0.8561 0.01241 0.00539 -0.0379 0.0501 1.0000
6.500 0.8804 0.01281 0.00579 -0.0374 0.0431 1.0000
6.750 0.9051 0.01315 0.00615 -0.0370 0.0383 1.0000
7.000 0.9289 0.01358 0.00656 -0.0365 0.0325 1.0000
7.250 0.9529 0.01397 0.00695 -0.0360 0.0265 1.0000
7.500 0.9764 0.01443 0.00738 -0.0355 0.0217 1.0000
7.750 1.0000 0.01484 0.00782 -0.0349 0.0178 1.0000
8.000 1.0227 0.01535 0.00832 -0.0343 0.0133 1.0000
8.250 1.0440 0.01600 0.00897 -0.0334 0.0070 1.0000
8.500 1.0650 0.01668 0.00966 -0.0325 0.0053 1.0000
8.750 1.0861 0.01732 0.01036 -0.0316 0.0047 1.0000
9.000 1.1065 0.01802 0.01114 -0.0306 0.0042 1.0000
9.250 1.1263 0.01876 0.01199 -0.0296 0.0039 1.0000
9.500 1.1458 0.01949 0.01283 -0.0285 0.0037 1.0000
9.750 1.1647 0.02023 0.01367 -0.0273 0.0035 1.0000
10.000 1.1824 0.02104 0.01459 -0.0261 0.0034 1.0000
10.250 1.1993 0.02188 0.01555 -0.0247 0.0032 1.0000
10.500 1.2150 0.02277 0.01655 -0.0233 0.0030 1.0000
10.750 1.2288 0.02373 0.01762 -0.0216 0.0029 1.0000
11.000 1.2388 0.02475 0.01876 -0.0193 0.0028 1.0000
11.250 1.2471 0.02582 0.01995 -0.0168 0.0027 1.0000
11.500 1.2538 0.02701 0.02127 -0.0144 0.0026 1.0000
11.750 1.2587 0.02838 0.02276 -0.0121 0.0026 1.0000
12.000 1.2626 0.02986 0.02438 -0.0100 0.0025 1.0000
12.250 1.2644 0.03160 0.02625 -0.0080 0.0025 1.0000
12.500 1.2655 0.03348 0.02827 -0.0063 0.0024 1.0000
12.750 1.2647 0.03565 0.03059 -0.0049 0.0024 1.0000
13.000 1.2611 0.03823 0.03333 -0.0038 0.0023 1.0000
13.250 1.2526 0.04153 0.03680 -0.0030 0.0023 1.0000
13.500 1.2472 0.04472 0.04017 -0.0029 0.0023 1.0000
13.750 1.2377 0.04866 0.04428 -0.0033 0.0022 1.0000
14.000 1.2294 0.05275 0.04853 -0.0043 0.0022 1.0000
14.500 1.1886 0.06576 0.06195 -0.0097 0.0021 1.0000
14.750 1.1826 0.07075 0.06707 -0.0124 0.0022 1.0000
15.000 1.1714 0.07705 0.07351 -0.0159 0.0022 1.0000
15.250 1.1551 0.08473 0.08136 -0.0204 0.0022 1.0000
15.500 1.1387 0.09284 0.08961 -0.0251 0.0022 1.0000
15.750 1.1155 0.10271 0.09965 -0.0308 0.0022 1.0000
16.000 1.1085 0.10918 0.10622 -0.0344 0.0023 1.0000
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