HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il) Reynolds number: 200,000 Max Cl/Cd: 75.1 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3012-il-200000-n5.txt Download as CSV file: xf-hq3012-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/12 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3985 0.08905 0.08550 -0.0484 1.0000 0.0141
-10.000 -0.4076 0.08405 0.08056 -0.0501 1.0000 0.0139
-9.750 -0.4242 0.07790 0.07452 -0.0524 1.0000 0.0140
-9.500 -0.4492 0.07083 0.06756 -0.0551 1.0000 0.0143
-9.250 -0.5221 0.04788 0.04428 -0.0767 0.9832 0.0129
-9.000 -0.5279 0.03838 0.03406 -0.0845 0.9710 0.0130
-8.750 -0.5156 0.03411 0.02931 -0.0868 0.9615 0.0135
-8.500 -0.4954 0.03047 0.02513 -0.0889 0.9554 0.0145
-8.250 -0.4763 0.02734 0.02146 -0.0895 0.9474 0.0150
-8.000 -0.4498 0.02479 0.01846 -0.0907 0.9430 0.0154
-7.750 -0.4280 0.02297 0.01638 -0.0905 0.9351 0.0159
-7.500 -0.4001 0.02165 0.01491 -0.0913 0.9301 0.0165
-7.250 -0.3742 0.02066 0.01377 -0.0915 0.9238 0.0173
-7.000 -0.3474 0.01965 0.01261 -0.0918 0.9178 0.0185
-6.750 -0.3192 0.01863 0.01142 -0.0921 0.9130 0.0198
-6.500 -0.2946 0.01783 0.01052 -0.0918 0.9058 0.0217
-6.250 -0.2660 0.01731 0.00994 -0.0922 0.9008 0.0245
-6.000 -0.2408 0.01663 0.00911 -0.0918 0.8941 0.0279
-5.750 -0.2146 0.01600 0.00847 -0.0918 0.8880 0.0323
-5.500 -0.1879 0.01551 0.00786 -0.0916 0.8822 0.0372
-5.250 -0.1620 0.01514 0.00747 -0.0915 0.8755 0.0429
-5.000 -0.1340 0.01480 0.00707 -0.0916 0.8706 0.0503
-4.750 -0.1083 0.01458 0.00680 -0.0913 0.8635 0.0577
-4.500 -0.0817 0.01412 0.00628 -0.0912 0.8580 0.0631
-4.250 -0.0554 0.01375 0.00587 -0.0910 0.8520 0.0688
-4.000 -0.0291 0.01341 0.00548 -0.0907 0.8457 0.0765
-3.750 -0.0014 0.01309 0.00509 -0.0907 0.8410 0.0869
-3.500 0.0242 0.01277 0.00480 -0.0904 0.8339 0.1022
-3.250 0.0510 0.01239 0.00450 -0.0904 0.8285 0.1323
-3.000 0.0767 0.01191 0.00426 -0.0903 0.8225 0.2005
-2.750 0.1014 0.01126 0.00401 -0.0902 0.8162 0.3140
-2.500 0.1256 0.01065 0.00399 -0.0897 0.8111 0.4858
-2.250 0.1511 0.01055 0.00403 -0.0892 0.8041 0.5462
-2.000 0.1784 0.01051 0.00399 -0.0888 0.7986 0.5816
-1.750 0.2049 0.01051 0.00400 -0.0884 0.7918 0.6103
-1.500 0.2316 0.01052 0.00402 -0.0878 0.7852 0.6410
-1.250 0.2578 0.01056 0.00407 -0.0872 0.7783 0.6681
-1.000 0.2847 0.01057 0.00405 -0.0868 0.7713 0.6835
-0.750 0.3120 0.01058 0.00403 -0.0865 0.7649 0.6966
-0.500 0.3390 0.01061 0.00401 -0.0862 0.7579 0.7088
-0.250 0.3666 0.01060 0.00397 -0.0859 0.7521 0.7166
0.000 0.3939 0.01062 0.00396 -0.0858 0.7447 0.7240
0.250 0.4216 0.01061 0.00391 -0.0856 0.7380 0.7304
0.500 0.4484 0.01062 0.00389 -0.0853 0.7278 0.7385
0.750 0.4749 0.01061 0.00386 -0.0849 0.7171 0.7451
1.000 0.5023 0.01062 0.00382 -0.0846 0.7078 0.7534
1.250 0.5288 0.01063 0.00385 -0.0843 0.6987 0.7607
1.500 0.5557 0.01066 0.00387 -0.0840 0.6900 0.7691
1.750 0.5824 0.01068 0.00388 -0.0836 0.6809 0.7774
2.000 0.6086 0.01070 0.00393 -0.0832 0.6703 0.7862
2.250 0.6350 0.01074 0.00397 -0.0828 0.6590 0.7959
2.500 0.6606 0.01076 0.00401 -0.0823 0.6459 0.8056
2.750 0.6859 0.01080 0.00405 -0.0816 0.6312 0.8165
3.000 0.7110 0.01085 0.00411 -0.0810 0.6163 0.8285
3.250 0.7359 0.01089 0.00417 -0.0803 0.6009 0.8424
3.500 0.7606 0.01094 0.00426 -0.0796 0.5840 0.8588
3.750 0.7851 0.01100 0.00432 -0.0787 0.5649 0.8810
4.000 0.8134 0.01107 0.00442 -0.0788 0.5420 0.9186
4.250 0.8447 0.01126 0.00455 -0.0796 0.5152 1.0000
4.500 0.8681 0.01156 0.00472 -0.0789 0.4873 1.0000
4.750 0.8907 0.01192 0.00494 -0.0781 0.4591 1.0000
5.000 0.9125 0.01232 0.00520 -0.0772 0.4307 1.0000
5.500 0.9553 0.01318 0.00585 -0.0752 0.3771 1.0000
5.750 0.9764 0.01363 0.00621 -0.0742 0.3522 1.0000
6.000 0.9968 0.01412 0.00659 -0.0731 0.3280 1.0000
6.250 1.0171 0.01461 0.00701 -0.0720 0.3060 1.0000
6.750 1.0567 0.01562 0.00790 -0.0697 0.2692 1.0000
7.000 1.0764 0.01613 0.00837 -0.0685 0.2523 1.0000
7.250 1.0956 0.01665 0.00887 -0.0673 0.2357 1.0000
7.500 1.1141 0.01719 0.00938 -0.0660 0.2195 1.0000
7.750 1.1320 0.01775 0.00990 -0.0646 0.2040 1.0000
8.000 1.1490 0.01832 0.01044 -0.0631 0.1896 1.0000
8.250 1.1648 0.01888 0.01100 -0.0613 0.1767 1.0000
8.500 1.1801 0.01948 0.01159 -0.0596 0.1648 1.0000
8.750 1.1948 0.02013 0.01225 -0.0578 0.1526 1.0000
9.000 1.2088 0.02083 0.01292 -0.0560 0.1387 1.0000
9.250 1.2225 0.02157 0.01364 -0.0542 0.1252 1.0000
9.500 1.2359 0.02235 0.01440 -0.0525 0.1129 1.0000
9.750 1.2487 0.02318 0.01523 -0.0507 0.1019 1.0000
10.000 1.2605 0.02410 0.01612 -0.0490 0.0900 1.0000
10.250 1.2716 0.02511 0.01712 -0.0473 0.0777 1.0000
10.500 1.2823 0.02617 0.01817 -0.0456 0.0675 1.0000
10.750 1.2927 0.02726 0.01928 -0.0440 0.0587 1.0000
11.000 1.3028 0.02842 0.02047 -0.0424 0.0530 1.0000
11.250 1.3133 0.02957 0.02169 -0.0410 0.0482 1.0000
11.500 1.3217 0.03091 0.02307 -0.0395 0.0438 1.0000
11.750 1.3315 0.03216 0.02443 -0.0381 0.0400 1.0000
12.000 1.3382 0.03372 0.02601 -0.0368 0.0352 1.0000
12.250 1.3462 0.03521 0.02762 -0.0355 0.0311 1.0000
12.500 1.3515 0.03697 0.02943 -0.0343 0.0269 1.0000
12.750 1.3568 0.03879 0.03133 -0.0332 0.0220 1.0000
13.000 1.3604 0.04082 0.03343 -0.0322 0.0189 1.0000
13.250 1.3624 0.04306 0.03574 -0.0313 0.0152 1.0000
13.500 1.3632 0.04553 0.03830 -0.0305 0.0123 1.0000
13.750 1.3620 0.04827 0.04112 -0.0299 0.0102 1.0000
14.000 1.3614 0.05106 0.04404 -0.0295 0.0090 1.0000
14.250 1.3593 0.05413 0.04724 -0.0293 0.0083 1.0000
14.500 1.3562 0.05745 0.05070 -0.0294 0.0078 1.0000
14.750 1.3512 0.06116 0.05455 -0.0297 0.0074 1.0000
15.000 1.3460 0.06508 0.05862 -0.0304 0.0072 1.0000
15.250 1.3393 0.06942 0.06313 -0.0314 0.0069 1.0000
15.500 1.3322 0.07398 0.06786 -0.0327 0.0068 1.0000
15.750 1.3235 0.07902 0.07311 -0.0344 0.0066 1.0000
16.000 1.3134 0.08452 0.07878 -0.0366 0.0065 1.0000
16.250 1.3021 0.09043 0.08487 -0.0391 0.0064 1.0000
16.500 1.2900 0.09672 0.09134 -0.0420 0.0064 1.0000
16.750 1.2766 0.10349 0.09829 -0.0453 0.0064 1.0000
17.000 1.2616 0.11078 0.10575 -0.0490 0.0063 1.0000
17.250 1.2470 0.11817 0.11332 -0.0529 0.0063 1.0000
17.500 1.2315 0.12595 0.12126 -0.0571 0.0063 1.0000
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