HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 200,000 Max Cl/Cd: 79.56 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq308-il-200000-n5.txt Download as CSV file: xf-hq308-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3681 0.08788 0.08458 -0.0349 1.0000 0.0188
-7.500 -0.3759 0.08567 0.08246 -0.0340 1.0000 0.0189
-7.250 -0.3848 0.08350 0.08036 -0.0330 1.0000 0.0189
-7.000 -0.3841 0.08030 0.07721 -0.0349 0.9987 0.0189
-6.750 -0.3587 0.07403 0.07090 -0.0452 0.9924 0.0190
-6.500 -0.3325 0.06796 0.06471 -0.0542 0.9868 0.0190
-6.000 -0.2929 0.05330 0.04983 -0.0672 0.9754 0.0097
-5.750 -0.2665 0.04749 0.04381 -0.0734 0.9692 0.0093
-5.500 -0.2364 0.04202 0.03808 -0.0788 0.9642 0.0090
-5.250 -0.2022 0.03656 0.03225 -0.0836 0.9610 0.0089
-5.000 -0.1734 0.03238 0.02770 -0.0854 0.9545 0.0097
-4.750 -0.1419 0.02775 0.02255 -0.0881 0.9501 0.0118
-4.500 -0.1083 0.02409 0.01839 -0.0899 0.9469 0.0117
-4.250 -0.0802 0.02126 0.01507 -0.0901 0.9405 0.0115
-4.000 -0.0481 0.01886 0.01222 -0.0909 0.9366 0.0115
-3.750 -0.0161 0.01695 0.00996 -0.0915 0.9330 0.0118
-3.500 0.0114 0.01554 0.00835 -0.0913 0.9269 0.0124
-3.250 0.0424 0.01441 0.00704 -0.0918 0.9226 0.0136
-3.000 0.0715 0.01382 0.00636 -0.0921 0.9173 0.0170
-2.750 0.1003 0.01304 0.00545 -0.0921 0.9115 0.0187
-2.500 0.1313 0.01225 0.00451 -0.0927 0.9073 0.0213
-2.250 0.1586 0.01182 0.00399 -0.0925 0.9001 0.0307
-2.000 0.1884 0.01137 0.00363 -0.0929 0.8949 0.0702
-1.750 0.2152 0.01066 0.00336 -0.0932 0.8879 0.2053
-1.500 0.2390 0.00946 0.00339 -0.0929 0.8817 0.5802
-1.250 0.2639 0.00928 0.00341 -0.0920 0.8743 0.6687
-1.000 0.2885 0.00912 0.00339 -0.0907 0.8675 0.7431
-0.750 0.3115 0.00898 0.00335 -0.0892 0.8584 0.7918
-0.500 0.3371 0.00886 0.00319 -0.0883 0.8500 0.8196
-0.250 0.3636 0.00878 0.00306 -0.0877 0.8411 0.8373
0.000 0.3897 0.00870 0.00297 -0.0871 0.8320 0.8582
0.250 0.4172 0.00859 0.00286 -0.0867 0.8235 0.8873
0.500 0.4525 0.00845 0.00271 -0.0880 0.8126 0.9472
0.750 0.4828 0.00845 0.00262 -0.0885 0.7994 1.0000
1.000 0.5103 0.00850 0.00259 -0.0884 0.7871 1.0000
1.250 0.5378 0.00856 0.00259 -0.0882 0.7753 1.0000
1.500 0.5652 0.00862 0.00261 -0.0881 0.7627 1.0000
1.750 0.5922 0.00869 0.00261 -0.0878 0.7472 1.0000
2.000 0.6188 0.00878 0.00262 -0.0874 0.7284 1.0000
2.250 0.6454 0.00888 0.00266 -0.0871 0.7088 1.0000
2.500 0.6720 0.00900 0.00275 -0.0867 0.6905 1.0000
2.750 0.6983 0.00914 0.00284 -0.0863 0.6696 1.0000
3.000 0.7244 0.00930 0.00294 -0.0859 0.6468 1.0000
3.250 0.7499 0.00950 0.00306 -0.0854 0.6188 1.0000
3.500 0.7749 0.00974 0.00320 -0.0847 0.5858 1.0000
3.750 0.7990 0.01005 0.00343 -0.0840 0.5464 1.0000
4.000 0.8222 0.01044 0.00365 -0.0831 0.5020 1.0000
4.250 0.8448 0.01091 0.00393 -0.0821 0.4555 1.0000
4.500 0.8672 0.01142 0.00427 -0.0813 0.4108 1.0000
4.750 0.8896 0.01195 0.00465 -0.0804 0.3693 1.0000
5.000 0.9120 0.01250 0.00506 -0.0796 0.3282 1.0000
5.250 0.9328 0.01320 0.00560 -0.0787 0.2780 1.0000
5.500 0.9515 0.01416 0.00614 -0.0775 0.2063 1.0000
5.750 0.9716 0.01500 0.00669 -0.0766 0.1546 1.0000
6.000 0.9936 0.01566 0.00724 -0.0759 0.1228 1.0000
6.250 1.0144 0.01647 0.00786 -0.0751 0.0847 1.0000
6.500 1.0336 0.01749 0.00864 -0.0740 0.0461 1.0000
6.750 1.0538 0.01840 0.00948 -0.0730 0.0254 1.0000
7.000 1.0730 0.01945 0.01047 -0.0718 0.0093 1.0000
7.250 1.0934 0.02035 0.01152 -0.0706 0.0069 1.0000
7.500 1.1135 0.02126 0.01261 -0.0694 0.0061 1.0000
7.750 1.1326 0.02227 0.01381 -0.0682 0.0056 1.0000
8.000 1.1507 0.02336 0.01509 -0.0667 0.0054 1.0000
8.250 1.1669 0.02463 0.01656 -0.0651 0.0051 1.0000
8.500 1.1814 0.02604 0.01815 -0.0633 0.0049 1.0000
8.750 1.1942 0.02759 0.01990 -0.0613 0.0048 1.0000
9.000 1.2056 0.02932 0.02182 -0.0591 0.0047 1.0000
9.250 1.2161 0.03117 0.02387 -0.0569 0.0047 1.0000
9.500 1.2247 0.03316 0.02606 -0.0545 0.0046 1.0000
9.750 1.2318 0.03534 0.02848 -0.0520 0.0046 1.0000
10.000 1.2371 0.03772 0.03111 -0.0495 0.0045 1.0000
10.250 1.2401 0.04025 0.03391 -0.0469 0.0045 1.0000
10.500 1.2398 0.04304 0.03707 -0.0443 0.0045 1.0000
10.750 1.2368 0.04597 0.04029 -0.0419 0.0045 1.0000
11.000 1.2307 0.04918 0.04378 -0.0397 0.0045 1.0000
11.250 1.2208 0.05280 0.04768 -0.0381 0.0044 1.0000
11.500 1.2081 0.05691 0.05206 -0.0371 0.0043 1.0000
11.750 1.1919 0.06173 0.05714 -0.0370 0.0043 1.0000
12.000 1.1780 0.06658 0.06223 -0.0377 0.0043 1.0000
12.250 1.1613 0.07232 0.06820 -0.0396 0.0042 1.0000
12.500 1.1467 0.07827 0.07436 -0.0422 0.0043 1.0000
12.750 1.1327 0.08480 0.08108 -0.0458 0.0043 1.0000
13.000 1.1168 0.09237 0.08884 -0.0505 0.0043 1.0000
13.250 1.1024 0.10053 0.09717 -0.0558 0.0044 1.0000
13.500 1.0843 0.11084 0.10769 -0.0625 0.0046 1.0000
13.750 1.0584 0.12455 0.12151 -0.0710 0.0049 1.0000
14.000 1.0348 0.13838 0.13544 -0.0789 0.0050 1.0000
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