HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.5 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3514-il-1000000-n5.txt Download as CSV file: xf-hq3514-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/14 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8987 0.06884 0.06609 -0.0775 1.0000 0.0061
-16.500 -0.9606 0.05376 0.05068 -0.0881 1.0000 0.0059
-16.250 -0.9827 0.04737 0.04413 -0.0923 1.0000 0.0058
-16.000 -1.0017 0.04203 0.03864 -0.0955 1.0000 0.0059
-15.750 -1.0134 0.03800 0.03449 -0.0974 1.0000 0.0060
-15.500 -1.0203 0.03487 0.03125 -0.0985 1.0000 0.0061
-15.250 -1.0266 0.03210 0.02838 -0.0988 1.0000 0.0062
-15.000 -1.0299 0.02997 0.02616 -0.0984 1.0000 0.0063
-14.750 -1.0194 0.02777 0.02385 -0.1003 0.9890 0.0064
-14.500 -0.9984 0.02585 0.02182 -0.1036 0.9828 0.0066
-14.250 -0.9736 0.02414 0.02000 -0.1070 0.9766 0.0068
-14.000 -0.9474 0.02264 0.01839 -0.1102 0.9694 0.0071
-13.750 -0.9236 0.02147 0.01711 -0.1119 0.9600 0.0073
-13.500 -0.9059 0.02062 0.01615 -0.1117 0.9479 0.0075
-13.250 -0.8895 0.01987 0.01530 -0.1110 0.9352 0.0077
-13.000 -0.8730 0.01918 0.01450 -0.1100 0.9212 0.0079
-12.750 -0.8569 0.01846 0.01368 -0.1088 0.9062 0.0083
-12.500 -0.8391 0.01784 0.01295 -0.1078 0.8929 0.0087
-12.250 -0.8202 0.01726 0.01228 -0.1069 0.8824 0.0092
-12.000 -0.8001 0.01674 0.01166 -0.1061 0.8737 0.0097
-11.750 -0.7788 0.01626 0.01109 -0.1055 0.8664 0.0102
-11.500 -0.7573 0.01574 0.01052 -0.1048 0.8600 0.0110
-11.250 -0.7349 0.01529 0.01000 -0.1043 0.8541 0.0118
-11.000 -0.7115 0.01487 0.00952 -0.1039 0.8485 0.0125
-10.750 -0.6879 0.01448 0.00906 -0.1035 0.8430 0.0132
-10.500 -0.6639 0.01407 0.00862 -0.1031 0.8383 0.0141
-10.250 -0.6392 0.01371 0.00822 -0.1029 0.8331 0.0150
-10.000 -0.6143 0.01338 0.00783 -0.1026 0.8277 0.0158
-9.750 -0.5891 0.01305 0.00745 -0.1023 0.8228 0.0166
-9.500 -0.5637 0.01271 0.00709 -0.1021 0.8168 0.0176
-9.250 -0.5381 0.01244 0.00677 -0.1019 0.8107 0.0186
-9.000 -0.5119 0.01217 0.00645 -0.1018 0.8044 0.0195
-8.750 -0.4860 0.01189 0.00612 -0.1016 0.7974 0.0205
-8.500 -0.4599 0.01162 0.00582 -0.1014 0.7908 0.0216
-8.250 -0.4335 0.01138 0.00555 -0.1013 0.7833 0.0226
-8.000 -0.4070 0.01117 0.00527 -0.1011 0.7765 0.0236
-7.750 -0.3801 0.01096 0.00501 -0.1011 0.7698 0.0243
-7.500 -0.3537 0.01070 0.00472 -0.1009 0.7637 0.0258
-7.250 -0.3266 0.01049 0.00450 -0.1009 0.7580 0.0274
-7.000 -0.2994 0.01032 0.00429 -0.1008 0.7518 0.0287
-6.750 -0.2722 0.01015 0.00406 -0.1008 0.7458 0.0296
-6.500 -0.2450 0.00993 0.00381 -0.1007 0.7398 0.0313
-6.250 -0.2177 0.00975 0.00361 -0.1007 0.7342 0.0331
-6.000 -0.1902 0.00959 0.00342 -0.1007 0.7293 0.0346
-5.750 -0.1623 0.00944 0.00324 -0.1007 0.7242 0.0359
-5.500 -0.1347 0.00928 0.00306 -0.1007 0.7194 0.0380
-5.250 -0.1070 0.00914 0.00291 -0.1008 0.7151 0.0409
-5.000 -0.0788 0.00900 0.00276 -0.1008 0.7111 0.0433
-4.750 -0.0508 0.00889 0.00261 -0.1009 0.7057 0.0454
-4.250 0.0050 0.00866 0.00236 -0.1010 0.6944 0.0526
-4.000 0.0331 0.00857 0.00224 -0.1010 0.6883 0.0556
-3.750 0.0609 0.00847 0.00214 -0.1010 0.6823 0.0602
-3.500 0.0894 0.00837 0.00204 -0.1012 0.6776 0.0643
-3.250 0.1177 0.00827 0.00195 -0.1013 0.6732 0.0699
-3.000 0.1457 0.00820 0.00187 -0.1013 0.6683 0.0759
-2.750 0.1741 0.00812 0.00178 -0.1014 0.6634 0.0820
-2.500 0.2024 0.00802 0.00171 -0.1015 0.6576 0.0909
-2.000 0.2582 0.00775 0.00153 -0.1017 0.6452 0.1350
-1.750 0.2858 0.00756 0.00148 -0.1018 0.6382 0.1935
-1.250 0.3421 0.00736 0.00138 -0.1020 0.6267 0.2366
-1.000 0.3695 0.00716 0.00134 -0.1021 0.6203 0.3013
-0.750 0.3965 0.00675 0.00126 -0.1023 0.6133 0.4106
-0.500 0.4241 0.00665 0.00128 -0.1023 0.6053 0.4752
-0.250 0.4524 0.00666 0.00130 -0.1024 0.5978 0.4890
0.000 0.4799 0.00670 0.00132 -0.1023 0.5857 0.5044
0.250 0.5071 0.00675 0.00135 -0.1022 0.5698 0.5178
0.500 0.5339 0.00686 0.00139 -0.1020 0.5478 0.5273
0.750 0.5585 0.00708 0.00147 -0.1014 0.5104 0.5371
1.000 0.5824 0.00738 0.00160 -0.1007 0.4705 0.5469
1.250 0.6082 0.00754 0.00171 -0.1004 0.4524 0.5567
1.750 0.6613 0.00781 0.00190 -0.1000 0.4290 0.5699
2.250 0.7149 0.00802 0.00209 -0.0997 0.4114 0.5886
2.500 0.7416 0.00813 0.00219 -0.0995 0.4023 0.5994
2.750 0.7683 0.00824 0.00230 -0.0994 0.3917 0.6106
3.000 0.7941 0.00839 0.00243 -0.0990 0.3741 0.6233
3.250 0.8168 0.00873 0.00261 -0.0982 0.3326 0.6352
3.500 0.8400 0.00905 0.00282 -0.0975 0.3093 0.6449
3.750 0.8647 0.00927 0.00300 -0.0970 0.2966 0.6540
4.000 0.8897 0.00946 0.00317 -0.0965 0.2876 0.6618
4.250 0.9151 0.00961 0.00333 -0.0962 0.2805 0.6697
4.500 0.9399 0.00981 0.00350 -0.0957 0.2726 0.6764
4.750 0.9651 0.00996 0.00366 -0.0953 0.2655 0.6830
5.250 1.0146 0.01029 0.00401 -0.0943 0.2528 0.6975
5.500 1.0387 0.01049 0.00420 -0.0937 0.2448 0.7043
5.750 1.0627 0.01068 0.00439 -0.0931 0.2364 0.7099
6.000 1.0850 0.01095 0.00461 -0.0922 0.2212 0.7158
6.250 1.1032 0.01142 0.00493 -0.0907 0.1912 0.7215
6.500 1.1224 0.01180 0.00524 -0.0893 0.1748 0.7273
6.750 1.1426 0.01210 0.00553 -0.0881 0.1656 0.7337
7.000 1.1612 0.01239 0.00580 -0.0865 0.1582 0.7400
7.250 1.1797 0.01264 0.00608 -0.0849 0.1528 0.7476
7.750 1.2158 0.01323 0.00670 -0.0817 0.1420 0.7654
8.000 1.2345 0.01349 0.00702 -0.0802 0.1381 0.7756
8.750 1.2868 0.01442 0.00809 -0.0753 0.1244 0.8240
9.000 1.3028 0.01470 0.00847 -0.0735 0.1193 0.8570
9.500 1.3404 0.01543 0.00936 -0.0713 0.1055 1.0000
9.750 1.3555 0.01598 0.00988 -0.0697 0.0984 1.0000
10.000 1.3703 0.01656 0.01043 -0.0680 0.0901 1.0000
10.250 1.3843 0.01720 0.01104 -0.0664 0.0822 1.0000
10.500 1.3947 0.01807 0.01183 -0.0643 0.0694 1.0000
10.750 1.4004 0.01924 0.01289 -0.0617 0.0527 1.0000
11.000 1.4058 0.02049 0.01406 -0.0593 0.0392 1.0000
11.250 1.4167 0.02143 0.01500 -0.0576 0.0342 1.0000
11.500 1.4280 0.02238 0.01595 -0.0560 0.0306 1.0000
11.750 1.4405 0.02327 0.01687 -0.0546 0.0283 1.0000
12.000 1.4509 0.02432 0.01793 -0.0531 0.0256 1.0000
12.250 1.4634 0.02526 0.01890 -0.0518 0.0242 1.0000
12.500 1.4747 0.02630 0.01998 -0.0506 0.0221 1.0000
12.750 1.4839 0.02752 0.02121 -0.0492 0.0199 1.0000
13.000 1.4946 0.02866 0.02238 -0.0480 0.0177 1.0000
13.250 1.5029 0.03002 0.02376 -0.0467 0.0152 1.0000
13.500 1.5100 0.03150 0.02525 -0.0455 0.0124 1.0000
13.750 1.5156 0.03316 0.02692 -0.0442 0.0099 1.0000
14.000 1.5221 0.03479 0.02859 -0.0431 0.0086 1.0000
14.250 1.5282 0.03651 0.03036 -0.0421 0.0077 1.0000
14.500 1.5349 0.03822 0.03214 -0.0412 0.0071 1.0000
14.750 1.5402 0.04011 0.03408 -0.0404 0.0067 1.0000
15.000 1.5446 0.04216 0.03619 -0.0397 0.0063 1.0000
15.250 1.5489 0.04427 0.03837 -0.0390 0.0059 1.0000
15.500 1.5539 0.04636 0.04053 -0.0385 0.0057 1.0000
15.750 1.5578 0.04862 0.04287 -0.0381 0.0055 1.0000
16.000 1.5610 0.05104 0.04536 -0.0379 0.0053 1.0000
16.250 1.5630 0.05366 0.04806 -0.0377 0.0051 1.0000
16.500 1.5639 0.05648 0.05096 -0.0376 0.0049 1.0000
16.750 1.5639 0.05948 0.05405 -0.0377 0.0048 1.0000
17.000 1.5629 0.06271 0.05736 -0.0380 0.0047 1.0000
17.250 1.5596 0.06636 0.06110 -0.0385 0.0045 1.0000
17.500 1.5558 0.07018 0.06502 -0.0392 0.0044 1.0000
17.750 1.5507 0.07430 0.06924 -0.0402 0.0043 1.0000
18.000 1.5449 0.07868 0.07372 -0.0413 0.0042 1.0000
18.250 1.5408 0.08292 0.07807 -0.0426 0.0041 1.0000
18.500 1.5346 0.08759 0.08285 -0.0442 0.0041 1.0000
18.750 1.5267 0.09259 0.08796 -0.0460 0.0041 1.0000
19.000 1.5179 0.09784 0.09333 -0.0481 0.0040 1.0000
19.250 1.5078 0.10341 0.09901 -0.0504 0.0040 1.0000
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