HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/9 AIRFOIL (hq159-il) Reynolds number: 500,000 Max Cl/Cd: 72.05 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq159-il-500000-n5.txt Download as CSV file: xf-hq159-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/9 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5385 0.08581 0.08357 -0.0213 1.0000 0.0046
-9.500 -0.5455 0.07999 0.07778 -0.0246 1.0000 0.0046
-9.250 -0.5534 0.07406 0.07189 -0.0284 1.0000 0.0045
-9.000 -0.5700 0.06553 0.06342 -0.0356 1.0000 0.0044
-8.750 -0.5908 0.05828 0.05615 -0.0421 1.0000 0.0043
-8.500 -0.6065 0.05097 0.04867 -0.0450 1.0000 0.0043
-8.250 -0.6248 0.04177 0.03914 -0.0458 1.0000 0.0041
-8.000 -0.6501 0.02970 0.02624 -0.0435 1.0000 0.0040
-7.750 -0.6460 0.02508 0.02107 -0.0413 1.0000 0.0040
-7.500 -0.6203 0.02136 0.01679 -0.0426 0.9941 0.0042
-7.250 -0.5925 0.01899 0.01402 -0.0436 0.9885 0.0045
-7.000 -0.5616 0.01733 0.01204 -0.0448 0.9845 0.0048
-6.750 -0.5323 0.01616 0.01065 -0.0455 0.9783 0.0051
-6.500 -0.5018 0.01464 0.00890 -0.0466 0.9730 0.0055
-6.250 -0.4727 0.01361 0.00775 -0.0473 0.9657 0.0061
-6.000 -0.4412 0.01297 0.00703 -0.0483 0.9592 0.0067
-5.750 -0.4116 0.01253 0.00654 -0.0489 0.9504 0.0078
-5.500 -0.3820 0.01203 0.00593 -0.0494 0.9416 0.0087
-5.000 -0.3273 0.01076 0.00440 -0.0493 0.9205 0.0108
-4.750 -0.3004 0.01039 0.00396 -0.0492 0.9104 0.0125
-4.500 -0.2735 0.01011 0.00360 -0.0489 0.9010 0.0148
-4.250 -0.2473 0.00973 0.00321 -0.0486 0.8913 0.0224
-4.000 -0.2207 0.00947 0.00294 -0.0484 0.8821 0.0326
-3.750 -0.1939 0.00926 0.00268 -0.0481 0.8734 0.0414
-3.500 -0.1672 0.00906 0.00247 -0.0479 0.8647 0.0530
-3.250 -0.1406 0.00879 0.00226 -0.0477 0.8562 0.0779
-3.000 -0.1142 0.00851 0.00206 -0.0476 0.8483 0.1122
-2.750 -0.0877 0.00819 0.00188 -0.0474 0.8395 0.1604
-2.500 -0.0615 0.00785 0.00169 -0.0473 0.8310 0.2247
-2.250 -0.0360 0.00738 0.00151 -0.0471 0.8216 0.3207
-2.000 -0.0103 0.00695 0.00139 -0.0469 0.8116 0.4231
-1.750 0.0159 0.00668 0.00131 -0.0466 0.8022 0.4967
-1.500 0.0421 0.00649 0.00127 -0.0463 0.7936 0.5609
-1.250 0.0689 0.00638 0.00125 -0.0460 0.7833 0.6041
-1.000 0.0954 0.00631 0.00124 -0.0456 0.7712 0.6447
-0.750 0.1222 0.00629 0.00122 -0.0452 0.7577 0.6698
-0.500 0.1493 0.00628 0.00120 -0.0449 0.7450 0.6876
-0.250 0.1764 0.00628 0.00119 -0.0447 0.7325 0.7037
0.000 0.2035 0.00629 0.00119 -0.0444 0.7195 0.7204
0.250 0.2305 0.00631 0.00119 -0.0441 0.7051 0.7356
0.500 0.2577 0.00633 0.00120 -0.0439 0.6906 0.7464
0.750 0.2849 0.00637 0.00121 -0.0437 0.6766 0.7558
1.000 0.3122 0.00641 0.00123 -0.0435 0.6629 0.7658
1.250 0.3393 0.00646 0.00127 -0.0433 0.6477 0.7760
1.500 0.3662 0.00651 0.00131 -0.0430 0.6307 0.7864
1.750 0.3929 0.00658 0.00136 -0.0427 0.6117 0.7976
2.000 0.4194 0.00666 0.00142 -0.0424 0.5893 0.8097
2.250 0.4454 0.00677 0.00148 -0.0420 0.5628 0.8226
2.500 0.4708 0.00692 0.00158 -0.0415 0.5284 0.8365
2.750 0.4951 0.00716 0.00169 -0.0408 0.4803 0.8520
3.000 0.5188 0.00744 0.00183 -0.0400 0.4290 0.8710
3.250 0.5420 0.00775 0.00201 -0.0391 0.3734 0.8978
3.500 0.5711 0.00825 0.00226 -0.0397 0.2963 0.9445
3.750 0.6065 0.00865 0.00249 -0.0417 0.2547 1.0000
4.000 0.6325 0.00890 0.00269 -0.0415 0.2357 1.0000
4.250 0.6584 0.00916 0.00289 -0.0412 0.2171 1.0000
4.500 0.6838 0.00949 0.00312 -0.0409 0.1893 1.0000
4.750 0.7082 0.00993 0.00340 -0.0405 0.1497 1.0000
5.000 0.7318 0.01047 0.00373 -0.0401 0.1075 1.0000
5.250 0.7557 0.01100 0.00410 -0.0396 0.0750 1.0000
5.500 0.7799 0.01147 0.00446 -0.0391 0.0552 1.0000
5.750 0.8050 0.01183 0.00480 -0.0388 0.0453 1.0000
6.000 0.8300 0.01219 0.00517 -0.0384 0.0373 1.0000
6.250 0.8545 0.01260 0.00556 -0.0380 0.0286 1.0000
6.500 0.8791 0.01301 0.00596 -0.0376 0.0227 1.0000
6.750 0.9031 0.01348 0.00640 -0.0371 0.0154 1.0000
7.000 0.9262 0.01407 0.00696 -0.0365 0.0075 1.0000
7.250 0.9493 0.01466 0.00757 -0.0358 0.0052 1.0000
7.500 0.9725 0.01524 0.00822 -0.0351 0.0045 1.0000
7.750 0.9955 0.01582 0.00890 -0.0344 0.0042 1.0000
8.000 1.0180 0.01647 0.00968 -0.0336 0.0040 1.0000
8.250 1.0398 0.01716 0.01047 -0.0328 0.0037 1.0000
8.500 1.0610 0.01791 0.01133 -0.0320 0.0034 1.0000
8.750 1.0814 0.01873 0.01224 -0.0311 0.0030 1.0000
9.000 1.0999 0.01977 0.01341 -0.0299 0.0027 1.0000
9.250 1.1162 0.02105 0.01485 -0.0284 0.0026 1.0000
9.500 1.1309 0.02244 0.01641 -0.0267 0.0025 1.0000
9.750 1.1489 0.02337 0.01746 -0.0256 0.0024 1.0000
10.000 1.1631 0.02467 0.01893 -0.0239 0.0024 1.0000
10.250 1.1773 0.02588 0.02032 -0.0224 0.0023 1.0000
10.500 1.1890 0.02725 0.02187 -0.0205 0.0022 1.0000
10.750 1.1985 0.02865 0.02345 -0.0184 0.0021 1.0000
11.000 1.2017 0.03028 0.02526 -0.0155 0.0021 1.0000
11.250 1.2035 0.03198 0.02715 -0.0128 0.0021 1.0000
11.500 1.2033 0.03389 0.02925 -0.0103 0.0020 1.0000
11.750 1.2002 0.03615 0.03171 -0.0080 0.0020 1.0000
12.000 1.1957 0.03866 0.03442 -0.0063 0.0019 1.0000
12.250 1.1889 0.04161 0.03758 -0.0051 0.0019 1.0000
12.500 1.1795 0.04510 0.04128 -0.0046 0.0018 1.0000
12.750 1.1682 0.04916 0.04554 -0.0049 0.0019 1.0000
13.000 1.1557 0.05379 0.05036 -0.0062 0.0018 1.0000
13.250 1.1413 0.05924 0.05601 -0.0085 0.0018 1.0000
13.500 1.1244 0.06580 0.06275 -0.0120 0.0019 1.0000
13.750 1.1070 0.07332 0.07045 -0.0167 0.0019 1.0000
14.000 1.0853 0.08273 0.08003 -0.0228 0.0018 1.0000
14.250 1.0639 0.09284 0.09030 -0.0292 0.0019 1.0000
14.500 1.0404 0.10372 0.10131 -0.0355 0.0019 1.0000
14.750 1.0174 0.11456 0.11225 -0.0416 0.0020 1.0000
15.000 0.9910 0.12673 0.12451 -0.0481 0.0021 1.0000
15.250 0.9620 0.14022 0.13807 -0.0550 0.0022 1.0000
15.500 0.9255 0.15728 0.15516 -0.0633 0.0023 1.0000
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