HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.01 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3512-il-1000000.txt Download as CSV file: xf-hq3512-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3229 0.09330 0.09174 -0.0514 0.9974 0.0127
-9.750 -0.4880 0.02950 0.02696 -0.1102 0.9615 0.0077
-9.500 -0.4848 0.02502 0.02199 -0.1112 0.9461 0.0077
-9.250 -0.4734 0.02254 0.01914 -0.1105 0.9344 0.0077
-9.000 -0.4560 0.02094 0.01727 -0.1099 0.9254 0.0078
-8.750 -0.4367 0.01973 0.01584 -0.1093 0.9166 0.0079
-8.500 -0.4247 0.01666 0.01231 -0.1081 0.9077 0.0082
-8.250 -0.4040 0.01532 0.01077 -0.1075 0.9005 0.0085
-8.000 -0.3809 0.01446 0.00979 -0.1071 0.8941 0.0088
-7.750 -0.3567 0.01377 0.00899 -0.1067 0.8874 0.0090
-7.500 -0.3320 0.01314 0.00824 -0.1063 0.8816 0.0092
-7.250 -0.3071 0.01252 0.00753 -0.1060 0.8753 0.0095
-7.000 -0.2817 0.01198 0.00687 -0.1057 0.8694 0.0097
-6.750 -0.2561 0.01145 0.00626 -0.1054 0.8636 0.0100
-6.500 -0.2302 0.01096 0.00568 -0.1051 0.8575 0.0103
-6.250 -0.2039 0.01058 0.00521 -0.1049 0.8520 0.0106
-6.000 -0.1772 0.01022 0.00479 -0.1048 0.8460 0.0110
-5.750 -0.1515 0.00962 0.00408 -0.1045 0.8403 0.0121
-5.500 -0.1245 0.00930 0.00372 -0.1044 0.8346 0.0131
-5.250 -0.0973 0.00903 0.00340 -0.1043 0.8287 0.0142
-5.000 -0.0701 0.00873 0.00306 -0.1041 0.8233 0.0171
-4.750 -0.0426 0.00848 0.00285 -0.1041 0.8173 0.0257
-4.500 -0.0149 0.00837 0.00273 -0.1041 0.8115 0.0326
-4.250 0.0128 0.00819 0.00256 -0.1041 0.8058 0.0376
-4.000 0.0407 0.00809 0.00244 -0.1041 0.7996 0.0413
-3.750 0.0685 0.00798 0.00228 -0.1041 0.7940 0.0454
-3.500 0.0964 0.00782 0.00214 -0.1041 0.7874 0.0512
-3.250 0.1241 0.00774 0.00199 -0.1040 0.7804 0.0556
-3.000 0.1518 0.00756 0.00185 -0.1040 0.7719 0.0667
-2.750 0.1792 0.00739 0.00171 -0.1039 0.7640 0.0883
-2.500 0.2065 0.00712 0.00157 -0.1039 0.7557 0.1355
-2.250 0.2332 0.00671 0.00144 -0.1040 0.7488 0.2343
-2.000 0.2594 0.00613 0.00131 -0.1041 0.7415 0.3865
-1.750 0.2863 0.00585 0.00126 -0.1041 0.7351 0.4819
-1.500 0.3140 0.00573 0.00124 -0.1041 0.7278 0.5314
-1.250 0.3417 0.00570 0.00124 -0.1040 0.7211 0.5632
-1.000 0.3699 0.00566 0.00124 -0.1040 0.7139 0.5891
-0.750 0.3976 0.00568 0.00125 -0.1039 0.7067 0.6100
-0.500 0.4258 0.00568 0.00126 -0.1039 0.6987 0.6280
-0.250 0.4535 0.00572 0.00128 -0.1038 0.6913 0.6441
0.000 0.4814 0.00574 0.00132 -0.1038 0.6833 0.6628
0.250 0.5091 0.00578 0.00135 -0.1037 0.6755 0.6771
0.500 0.5368 0.00582 0.00138 -0.1036 0.6669 0.6867
0.750 0.5647 0.00586 0.00141 -0.1036 0.6590 0.6946
1.000 0.5924 0.00591 0.00144 -0.1035 0.6505 0.7011
1.250 0.6204 0.00595 0.00147 -0.1035 0.6416 0.7073
1.500 0.6477 0.00601 0.00151 -0.1034 0.6315 0.7136
2.000 0.7023 0.00614 0.00160 -0.1031 0.6078 0.7262
2.250 0.7294 0.00623 0.00166 -0.1030 0.5943 0.7332
2.500 0.7558 0.00634 0.00173 -0.1027 0.5779 0.7397
2.750 0.7820 0.00647 0.00181 -0.1024 0.5588 0.7471
3.000 0.8077 0.00662 0.00191 -0.1020 0.5363 0.7543
3.250 0.8326 0.00683 0.00203 -0.1015 0.5090 0.7624
3.500 0.8566 0.00709 0.00218 -0.1008 0.4775 0.7704
3.750 0.8801 0.00741 0.00236 -0.1001 0.4439 0.7793
4.000 0.9033 0.00771 0.00256 -0.0993 0.4107 0.7886
4.250 0.9265 0.00803 0.00277 -0.0985 0.3786 0.7987
4.500 0.9492 0.00837 0.00299 -0.0977 0.3458 0.8102
5.000 0.9940 0.00898 0.00345 -0.0959 0.2927 0.8404
5.250 1.0164 0.00916 0.00366 -0.0950 0.2783 0.8664
5.500 1.0440 0.00922 0.00387 -0.0951 0.2653 1.0000
5.750 1.0682 0.00950 0.00410 -0.0946 0.2548 1.0000
6.000 1.0935 0.00970 0.00429 -0.0942 0.2480 1.0000
6.250 1.1175 0.00997 0.00453 -0.0937 0.2399 1.0000
6.500 1.1425 0.01016 0.00472 -0.0933 0.2332 1.0000
6.750 1.1661 0.01043 0.00496 -0.0927 0.2249 1.0000
7.000 1.1902 0.01066 0.00518 -0.0922 0.2160 1.0000
7.250 1.2136 0.01092 0.00542 -0.0915 0.2058 1.0000
7.500 1.2362 0.01122 0.00568 -0.0907 0.1953 1.0000
7.750 1.2580 0.01155 0.00595 -0.0899 0.1814 1.0000
8.000 1.2789 0.01192 0.00626 -0.0888 0.1658 1.0000
8.250 1.2980 0.01237 0.00662 -0.0875 0.1475 1.0000
8.500 1.3153 0.01290 0.00704 -0.0859 0.1299 1.0000
8.750 1.3308 0.01342 0.00747 -0.0839 0.1136 1.0000
9.000 1.3447 0.01396 0.00795 -0.0817 0.0984 1.0000
9.250 1.3577 0.01457 0.00848 -0.0793 0.0836 1.0000
9.500 1.3695 0.01526 0.00907 -0.0768 0.0687 1.0000
9.750 1.3812 0.01598 0.00971 -0.0745 0.0555 1.0000
10.000 1.3917 0.01678 0.01043 -0.0720 0.0410 1.0000
10.250 1.3973 0.01791 0.01143 -0.0689 0.0233 1.0000
10.500 1.4009 0.01921 0.01262 -0.0657 0.0096 1.0000
10.750 1.4114 0.02011 0.01354 -0.0636 0.0068 1.0000
11.000 1.4232 0.02096 0.01442 -0.0617 0.0058 1.0000
11.250 1.4351 0.02182 0.01535 -0.0598 0.0053 1.0000
11.500 1.4459 0.02277 0.01637 -0.0580 0.0048 1.0000
11.750 1.4564 0.02377 0.01743 -0.0562 0.0046 1.0000
12.000 1.4658 0.02487 0.01859 -0.0544 0.0044 1.0000
12.250 1.4717 0.02627 0.02008 -0.0524 0.0041 1.0000
12.500 1.4765 0.02782 0.02173 -0.0504 0.0039 1.0000
12.750 1.4846 0.02912 0.02312 -0.0489 0.0039 1.0000
13.000 1.4907 0.03064 0.02472 -0.0473 0.0038 1.0000
13.250 1.4969 0.03221 0.02638 -0.0459 0.0038 1.0000
13.500 1.5007 0.03402 0.02829 -0.0445 0.0037 1.0000
13.750 1.5031 0.03605 0.03041 -0.0431 0.0036 1.0000
14.000 1.5061 0.03807 0.03253 -0.0420 0.0036 1.0000
14.250 1.5080 0.04028 0.03483 -0.0410 0.0035 1.0000
14.500 1.5072 0.04287 0.03753 -0.0402 0.0035 1.0000
14.750 1.5051 0.04572 0.04049 -0.0395 0.0035 1.0000
15.000 1.5033 0.04867 0.04354 -0.0391 0.0034 1.0000
15.250 1.4999 0.05194 0.04693 -0.0389 0.0034 1.0000
15.500 1.4963 0.05541 0.05051 -0.0390 0.0033 1.0000
15.750 1.4907 0.05927 0.05447 -0.0394 0.0033 1.0000
16.000 1.4843 0.06343 0.05876 -0.0401 0.0032 1.0000
16.250 1.4752 0.06820 0.06365 -0.0411 0.0032 1.0000
16.500 1.4671 0.07300 0.06857 -0.0425 0.0032 1.0000
16.750 1.4553 0.07862 0.07434 -0.0444 0.0032 1.0000
17.000 1.4448 0.08425 0.08009 -0.0465 0.0032 1.0000
17.250 1.4317 0.09054 0.08651 -0.0490 0.0032 1.0000
17.500 1.4186 0.09699 0.09309 -0.0518 0.0031 1.0000
17.750 1.4063 0.10350 0.09972 -0.0548 0.0031 1.0000
18.000 1.3926 0.11039 0.10674 -0.0581 0.0031 1.0000
18.250 1.3789 0.11738 0.11386 -0.0616 0.0031 1.0000
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