HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.86 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3512-il-1000000-n5.txt Download as CSV file: xf-hq3512-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6968 0.03735 0.03513 -0.0935 0.9833 0.0044
-11.750 -0.6827 0.03248 0.03002 -0.1027 0.9733 0.0045
-11.500 -0.6687 0.02871 0.02594 -0.1080 0.9598 0.0047
-11.250 -0.6518 0.02672 0.02375 -0.1095 0.9465 0.0048
-11.000 -0.6383 0.02493 0.02173 -0.1097 0.9318 0.0049
-10.750 -0.6247 0.02335 0.01993 -0.1092 0.9187 0.0050
-10.500 -0.6089 0.02204 0.01842 -0.1086 0.9087 0.0051
-10.250 -0.5909 0.02093 0.01712 -0.1080 0.9001 0.0053
-10.000 -0.5721 0.01982 0.01583 -0.1074 0.8917 0.0054
-9.750 -0.5525 0.01875 0.01458 -0.1069 0.8844 0.0054
-9.500 -0.5307 0.01792 0.01359 -0.1065 0.8772 0.0055
-9.250 -0.5086 0.01710 0.01261 -0.1061 0.8708 0.0056
-9.000 -0.4854 0.01638 0.01176 -0.1057 0.8642 0.0056
-8.750 -0.4620 0.01566 0.01090 -0.1054 0.8581 0.0057
-8.500 -0.4375 0.01508 0.01021 -0.1051 0.8525 0.0057
-8.250 -0.4133 0.01442 0.00944 -0.1048 0.8463 0.0058
-8.000 -0.3902 0.01347 0.00832 -0.1044 0.8406 0.0059
-7.750 -0.3655 0.01278 0.00751 -0.1042 0.8346 0.0060
-7.500 -0.3405 0.01218 0.00681 -0.1039 0.8289 0.0062
-7.250 -0.3147 0.01170 0.00625 -0.1038 0.8232 0.0064
-7.000 -0.2885 0.01130 0.00579 -0.1037 0.8172 0.0067
-6.750 -0.2621 0.01092 0.00534 -0.1035 0.8118 0.0069
-6.500 -0.2354 0.01056 0.00491 -0.1034 0.8057 0.0070
-6.250 -0.2087 0.01024 0.00451 -0.1033 0.7998 0.0072
-6.000 -0.1816 0.00993 0.00415 -0.1032 0.7942 0.0074
-5.750 -0.1545 0.00966 0.00382 -0.1031 0.7882 0.0077
-5.500 -0.1273 0.00943 0.00353 -0.1031 0.7826 0.0079
-5.250 -0.0997 0.00921 0.00326 -0.1030 0.7767 0.0082
-5.000 -0.0723 0.00900 0.00299 -0.1030 0.7710 0.0087
-4.750 -0.0447 0.00880 0.00275 -0.1030 0.7654 0.0095
-4.500 -0.0170 0.00862 0.00254 -0.1029 0.7595 0.0105
-4.250 0.0106 0.00844 0.00234 -0.1029 0.7540 0.0135
-4.000 0.0382 0.00822 0.00217 -0.1030 0.7480 0.0233
-3.750 0.0660 0.00813 0.00204 -0.1030 0.7420 0.0277
-3.500 0.0940 0.00800 0.00192 -0.1030 0.7356 0.0329
-3.250 0.1216 0.00792 0.00181 -0.1030 0.7273 0.0368
-3.000 0.1493 0.00783 0.00169 -0.1029 0.7166 0.0420
-2.750 0.1768 0.00777 0.00160 -0.1029 0.7054 0.0472
-2.500 0.2043 0.00769 0.00151 -0.1028 0.6957 0.0560
-2.250 0.2323 0.00761 0.00143 -0.1028 0.6874 0.0665
-2.000 0.2599 0.00753 0.00135 -0.1028 0.6791 0.0822
-1.750 0.2875 0.00738 0.00128 -0.1029 0.6710 0.1168
-1.500 0.3148 0.00711 0.00121 -0.1029 0.6635 0.1877
-1.250 0.3421 0.00693 0.00115 -0.1030 0.6550 0.2480
-1.000 0.3692 0.00659 0.00108 -0.1031 0.6467 0.3508
-0.750 0.3963 0.00641 0.00106 -0.1031 0.6383 0.4223
-0.500 0.4238 0.00629 0.00106 -0.1031 0.6288 0.4766
-0.250 0.4508 0.00618 0.00109 -0.1030 0.6174 0.5408
0.000 0.4776 0.00614 0.00116 -0.1028 0.6042 0.5989
0.250 0.5048 0.00619 0.00120 -0.1027 0.5907 0.6232
0.500 0.5322 0.00626 0.00124 -0.1026 0.5784 0.6345
0.750 0.5594 0.00634 0.00129 -0.1025 0.5645 0.6437
1.000 0.5864 0.00646 0.00133 -0.1023 0.5467 0.6504
1.250 0.6128 0.00660 0.00140 -0.1020 0.5254 0.6557
1.500 0.6391 0.00676 0.00148 -0.1018 0.5039 0.6614
1.750 0.6652 0.00695 0.00157 -0.1015 0.4812 0.6670
2.000 0.6909 0.00715 0.00168 -0.1011 0.4565 0.6728
2.250 0.7161 0.00739 0.00181 -0.1007 0.4295 0.6787
2.500 0.7414 0.00762 0.00195 -0.1003 0.4046 0.6843
2.750 0.7668 0.00784 0.00208 -0.0999 0.3817 0.6906
3.000 0.7916 0.00811 0.00224 -0.0994 0.3548 0.6968
3.250 0.8159 0.00840 0.00242 -0.0989 0.3245 0.7034
3.500 0.8402 0.00870 0.00261 -0.0983 0.2983 0.7103
3.750 0.8648 0.00895 0.00279 -0.0978 0.2794 0.7173
4.000 0.8900 0.00916 0.00296 -0.0974 0.2669 0.7245
4.250 0.9154 0.00934 0.00313 -0.0971 0.2575 0.7317
4.500 0.9409 0.00952 0.00330 -0.0967 0.2495 0.7392
4.750 0.9665 0.00967 0.00347 -0.0964 0.2433 0.7469
5.250 1.0169 0.01001 0.00383 -0.0956 0.2302 0.7635
5.500 1.0418 0.01019 0.00401 -0.0952 0.2222 0.7725
5.750 1.0663 0.01039 0.00421 -0.0947 0.2132 0.7826
6.000 1.0899 0.01062 0.00443 -0.0940 0.2026 0.7933
6.250 1.1135 0.01083 0.00465 -0.0934 0.1919 0.8057
6.500 1.1366 0.01105 0.00488 -0.0926 0.1809 0.8205
6.750 1.1584 0.01130 0.00513 -0.0917 0.1678 0.8414
7.000 1.1769 0.01149 0.00541 -0.0900 0.1529 0.8917
7.250 1.2030 0.01181 0.00575 -0.0901 0.1364 1.0000
7.500 1.2221 0.01232 0.00615 -0.0887 0.1163 1.0000
7.750 1.2395 0.01290 0.00661 -0.0872 0.0961 1.0000
8.000 1.2565 0.01349 0.00708 -0.0855 0.0769 1.0000
8.250 1.2694 0.01419 0.00764 -0.0831 0.0561 1.0000
8.500 1.2806 0.01492 0.00826 -0.0805 0.0373 1.0000
8.750 1.2909 0.01573 0.00895 -0.0777 0.0208 1.0000
9.000 1.3033 0.01643 0.00961 -0.0754 0.0118 1.0000
9.250 1.3158 0.01716 0.01031 -0.0731 0.0049 1.0000
9.500 1.3313 0.01772 0.01089 -0.0714 0.0039 1.0000
9.750 1.3469 0.01827 0.01148 -0.0697 0.0035 1.0000
10.000 1.3622 0.01885 0.01211 -0.0681 0.0033 1.0000
10.250 1.3762 0.01952 0.01283 -0.0663 0.0030 1.0000
10.500 1.3905 0.02019 0.01354 -0.0647 0.0029 1.0000
10.750 1.4037 0.02094 0.01435 -0.0630 0.0027 1.0000
11.000 1.4153 0.02181 0.01529 -0.0611 0.0025 1.0000
11.250 1.4290 0.02256 0.01609 -0.0596 0.0025 1.0000
11.500 1.4409 0.02346 0.01704 -0.0580 0.0024 1.0000
11.750 1.4524 0.02440 0.01805 -0.0564 0.0023 1.0000
12.000 1.4631 0.02542 0.01914 -0.0548 0.0022 1.0000
12.250 1.4740 0.02646 0.02024 -0.0533 0.0021 1.0000
12.500 1.4828 0.02768 0.02154 -0.0517 0.0020 1.0000
12.750 1.4914 0.02896 0.02288 -0.0502 0.0020 1.0000
13.000 1.4993 0.03032 0.02432 -0.0488 0.0019 1.0000
13.250 1.5052 0.03191 0.02598 -0.0473 0.0018 1.0000
13.500 1.5118 0.03346 0.02762 -0.0461 0.0018 1.0000
13.750 1.5162 0.03528 0.02952 -0.0448 0.0018 1.0000
14.000 1.5209 0.03712 0.03144 -0.0437 0.0017 1.0000
14.250 1.5236 0.03921 0.03363 -0.0427 0.0017 1.0000
14.500 1.5241 0.04163 0.03615 -0.0418 0.0016 1.0000
14.750 1.5238 0.04421 0.03883 -0.0410 0.0016 1.0000
15.000 1.5226 0.04701 0.04173 -0.0405 0.0016 1.0000
15.250 1.5217 0.04992 0.04474 -0.0402 0.0016 1.0000
15.500 1.5176 0.05333 0.04826 -0.0401 0.0015 1.0000
15.750 1.5120 0.05708 0.05213 -0.0403 0.0015 1.0000
16.000 1.5024 0.06156 0.05674 -0.0409 0.0015 1.0000
16.250 1.4935 0.06618 0.06149 -0.0418 0.0015 1.0000
16.500 1.4798 0.07175 0.06720 -0.0433 0.0014 1.0000
16.750 1.4647 0.07783 0.07343 -0.0453 0.0014 1.0000
17.000 1.4606 0.08235 0.07805 -0.0469 0.0014 1.0000
17.250 1.4457 0.08889 0.08473 -0.0495 0.0014 1.0000
17.500 1.4271 0.09633 0.09232 -0.0528 0.0014 1.0000
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