HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.91 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3014-il-1000000-n5.txt Download as CSV file: xf-hq3014-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/14 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 -0.7330 0.10517 0.10279 -0.0488 1.0000 0.0060
-16.500 -0.8116 0.08685 0.08428 -0.0589 1.0000 0.0059
-16.250 -0.9056 0.06572 0.06283 -0.0715 1.0000 0.0057
-16.000 -0.9399 0.05580 0.05272 -0.0782 1.0000 0.0056
-15.750 -0.9617 0.04911 0.04586 -0.0826 1.0000 0.0056
-15.500 -0.9763 0.04405 0.04066 -0.0856 1.0000 0.0056
-15.250 -0.9853 0.04010 0.03660 -0.0875 1.0000 0.0056
-15.000 -0.9917 0.03674 0.03312 -0.0888 1.0000 0.0057
-14.750 -0.9941 0.03406 0.03034 -0.0895 1.0000 0.0057
-14.500 -0.9951 0.03174 0.02793 -0.0897 1.0000 0.0058
-14.250 -0.9965 0.02962 0.02572 -0.0894 1.0000 0.0058
-14.000 -0.9974 0.02786 0.02387 -0.0885 1.0000 0.0059
-13.750 -0.9887 0.02612 0.02202 -0.0891 0.9913 0.0060
-13.500 -0.9668 0.02449 0.02028 -0.0918 0.9834 0.0061
-13.250 -0.9414 0.02304 0.01872 -0.0946 0.9759 0.0062
-13.000 -0.9126 0.02187 0.01744 -0.0971 0.9683 0.0063
-12.750 -0.8853 0.02080 0.01625 -0.0989 0.9566 0.0063
-12.500 -0.8607 0.01996 0.01530 -0.0998 0.9412 0.0064
-12.250 -0.8413 0.01924 0.01445 -0.0993 0.9236 0.0065
-12.000 -0.8249 0.01853 0.01361 -0.0982 0.9085 0.0065
-11.500 -0.7916 0.01710 0.01196 -0.0958 0.8852 0.0070
-11.250 -0.7721 0.01653 0.01130 -0.0949 0.8766 0.0072
-11.000 -0.7514 0.01602 0.01072 -0.0941 0.8685 0.0074
-10.750 -0.7300 0.01553 0.01015 -0.0934 0.8614 0.0076
-10.500 -0.7078 0.01508 0.00961 -0.0927 0.8543 0.0078
-10.250 -0.6853 0.01464 0.00909 -0.0921 0.8483 0.0080
-10.000 -0.6619 0.01421 0.00861 -0.0916 0.8423 0.0082
-9.750 -0.6382 0.01383 0.00815 -0.0911 0.8362 0.0084
-9.500 -0.6140 0.01345 0.00771 -0.0907 0.8308 0.0086
-9.250 -0.5895 0.01308 0.00728 -0.0904 0.8251 0.0088
-9.000 -0.5653 0.01268 0.00682 -0.0899 0.8197 0.0094
-8.750 -0.5404 0.01232 0.00642 -0.0896 0.8144 0.0099
-8.500 -0.5151 0.01199 0.00605 -0.0893 0.8087 0.0106
-8.000 -0.4642 0.01134 0.00534 -0.0887 0.7983 0.0134
-7.750 -0.4386 0.01102 0.00501 -0.0885 0.7925 0.0167
-7.500 -0.4127 0.01076 0.00476 -0.0883 0.7875 0.0212
-7.250 -0.3859 0.01054 0.00452 -0.0882 0.7825 0.0237
-7.000 -0.3592 0.01033 0.00430 -0.0881 0.7770 0.0259
-6.750 -0.3322 0.01017 0.00408 -0.0879 0.7720 0.0276
-6.500 -0.3049 0.00999 0.00387 -0.0879 0.7670 0.0288
-6.250 -0.2779 0.00979 0.00366 -0.0878 0.7616 0.0308
-6.000 -0.2509 0.00963 0.00347 -0.0877 0.7566 0.0325
-5.750 -0.2233 0.00946 0.00329 -0.0877 0.7517 0.0342
-5.500 -0.1959 0.00930 0.00311 -0.0876 0.7463 0.0367
-5.250 -0.1687 0.00915 0.00295 -0.0875 0.7412 0.0399
-5.000 -0.1409 0.00901 0.00279 -0.0876 0.7363 0.0425
-4.750 -0.1134 0.00885 0.00264 -0.0875 0.7307 0.0472
-4.500 -0.0858 0.00872 0.00250 -0.0875 0.7255 0.0516
-4.250 -0.0580 0.00859 0.00236 -0.0875 0.7195 0.0559
-4.000 -0.0305 0.00847 0.00223 -0.0875 0.7128 0.0615
-3.750 -0.0026 0.00836 0.00211 -0.0875 0.7066 0.0672
-3.500 0.0251 0.00824 0.00200 -0.0875 0.7002 0.0758
-3.250 0.0527 0.00812 0.00189 -0.0874 0.6950 0.0876
-3.000 0.0807 0.00797 0.00179 -0.0875 0.6897 0.1033
-2.750 0.1082 0.00782 0.00168 -0.0875 0.6843 0.1256
-2.500 0.1354 0.00761 0.00159 -0.0875 0.6793 0.1646
-2.250 0.1630 0.00739 0.00150 -0.0876 0.6739 0.2068
-2.000 0.1903 0.00722 0.00142 -0.0876 0.6676 0.2465
-1.750 0.2178 0.00705 0.00135 -0.0876 0.6608 0.2854
-1.500 0.2432 0.00658 0.00124 -0.0874 0.6525 0.4060
-1.250 0.2703 0.00640 0.00121 -0.0874 0.6446 0.4673
-1.000 0.2981 0.00638 0.00120 -0.0874 0.6362 0.4883
-0.750 0.3260 0.00633 0.00121 -0.0874 0.6283 0.5146
-0.500 0.3534 0.00631 0.00123 -0.0873 0.6191 0.5440
-0.250 0.3814 0.00630 0.00125 -0.0873 0.6104 0.5658
0.000 0.4093 0.00633 0.00126 -0.0872 0.6024 0.5747
0.250 0.4374 0.00638 0.00128 -0.0872 0.5927 0.5825
0.500 0.4651 0.00642 0.00131 -0.0872 0.5829 0.5903
0.750 0.4926 0.00650 0.00135 -0.0871 0.5703 0.5991
1.000 0.5193 0.00659 0.00140 -0.0869 0.5519 0.6086
1.250 0.5459 0.00671 0.00146 -0.0866 0.5337 0.6180
1.500 0.5726 0.00682 0.00153 -0.0864 0.5170 0.6259
1.750 0.5991 0.00697 0.00160 -0.0861 0.4994 0.6317
2.000 0.6253 0.00711 0.00169 -0.0859 0.4815 0.6371
2.250 0.6517 0.00725 0.00178 -0.0856 0.4652 0.6428
2.500 0.6777 0.00743 0.00188 -0.0853 0.4467 0.6479
2.750 0.7031 0.00762 0.00200 -0.0849 0.4258 0.6530
3.000 0.7285 0.00782 0.00214 -0.0845 0.4067 0.6587
3.500 0.7787 0.00824 0.00242 -0.0836 0.3657 0.6702
3.750 0.8028 0.00850 0.00259 -0.0830 0.3421 0.6763
4.000 0.8270 0.00876 0.00276 -0.0824 0.3195 0.6820
4.250 0.8513 0.00899 0.00294 -0.0818 0.3028 0.6886
4.500 0.8757 0.00922 0.00312 -0.0812 0.2874 0.6950
4.750 0.8998 0.00944 0.00331 -0.0807 0.2734 0.7014
5.000 0.9244 0.00964 0.00349 -0.0801 0.2629 0.7086
5.250 0.9484 0.00986 0.00368 -0.0795 0.2519 0.7153
5.500 0.9720 0.01009 0.00389 -0.0789 0.2394 0.7228
5.750 0.9962 0.01028 0.00407 -0.0783 0.2299 0.7297
6.000 1.0194 0.01052 0.00429 -0.0775 0.2188 0.7376
6.250 1.0417 0.01078 0.00453 -0.0766 0.2060 0.7455
6.500 1.0636 0.01106 0.00477 -0.0757 0.1943 0.7539
6.750 1.0853 0.01133 0.00502 -0.0747 0.1829 0.7618
7.000 1.1047 0.01169 0.00533 -0.0733 0.1672 0.7713
7.250 1.1254 0.01196 0.00560 -0.0722 0.1577 0.7807
7.500 1.1436 0.01229 0.00590 -0.0706 0.1451 0.7909
7.750 1.1604 0.01259 0.00619 -0.0687 0.1365 0.8023
8.000 1.1783 0.01283 0.00648 -0.0670 0.1302 0.8158
8.250 1.1932 0.01319 0.00683 -0.0648 0.1199 0.8327
8.500 1.2058 0.01359 0.00724 -0.0622 0.1070 0.8576
9.000 1.2435 0.01442 0.00817 -0.0600 0.0845 1.0000
9.250 1.2587 0.01492 0.00864 -0.0582 0.0760 1.0000
9.500 1.2733 0.01545 0.00914 -0.0564 0.0683 1.0000
9.750 1.2865 0.01608 0.00972 -0.0544 0.0598 1.0000
10.000 1.2986 0.01678 0.01038 -0.0524 0.0510 1.0000
10.250 1.3120 0.01745 0.01101 -0.0506 0.0445 1.0000
10.500 1.3244 0.01818 0.01173 -0.0488 0.0384 1.0000
10.750 1.3349 0.01905 0.01256 -0.0468 0.0313 1.0000
11.000 1.3474 0.01983 0.01333 -0.0451 0.0278 1.0000
11.250 1.3586 0.02072 0.01422 -0.0434 0.0226 1.0000
11.500 1.3687 0.02171 0.01519 -0.0417 0.0179 1.0000
11.750 1.3785 0.02275 0.01622 -0.0400 0.0142 1.0000
12.000 1.3890 0.02377 0.01726 -0.0385 0.0114 1.0000
12.250 1.3900 0.02550 0.01897 -0.0362 0.0041 1.0000
12.500 1.4003 0.02661 0.02012 -0.0348 0.0038 1.0000
12.750 1.4095 0.02784 0.02140 -0.0335 0.0034 1.0000
13.000 1.4194 0.02904 0.02265 -0.0323 0.0033 1.0000
13.250 1.4284 0.03034 0.02401 -0.0312 0.0031 1.0000
13.500 1.4378 0.03164 0.02537 -0.0301 0.0030 1.0000
13.750 1.4459 0.03308 0.02688 -0.0291 0.0029 1.0000
14.000 1.4537 0.03458 0.02844 -0.0281 0.0028 1.0000
14.250 1.4608 0.03619 0.03012 -0.0273 0.0028 1.0000
14.500 1.4674 0.03790 0.03189 -0.0265 0.0027 1.0000
14.750 1.4735 0.03970 0.03376 -0.0257 0.0027 1.0000
15.000 1.4784 0.04167 0.03581 -0.0251 0.0026 1.0000
15.250 1.4818 0.04386 0.03807 -0.0246 0.0025 1.0000
15.500 1.4843 0.04622 0.04051 -0.0241 0.0024 1.0000
15.750 1.4880 0.04851 0.04288 -0.0238 0.0024 1.0000
16.000 1.4878 0.05131 0.04577 -0.0237 0.0023 1.0000
16.250 1.4875 0.05422 0.04877 -0.0237 0.0022 1.0000
16.500 1.4845 0.05757 0.05222 -0.0238 0.0022 1.0000
16.750 1.4819 0.06095 0.05570 -0.0242 0.0021 1.0000
17.000 1.4775 0.06471 0.05957 -0.0248 0.0021 1.0000
17.250 1.4720 0.06875 0.06371 -0.0257 0.0021 1.0000
17.500 1.4673 0.07280 0.06786 -0.0267 0.0020 1.0000
17.750 1.4610 0.07720 0.07237 -0.0280 0.0020 1.0000
18.000 1.4547 0.08174 0.07702 -0.0294 0.0020 1.0000
18.250 1.4469 0.08663 0.08202 -0.0312 0.0020 1.0000
18.500 1.4369 0.09202 0.08753 -0.0333 0.0020 1.0000
18.750 1.4272 0.09746 0.09308 -0.0356 0.0020 1.0000
19.000 1.4166 0.10319 0.09892 -0.0381 0.0020 1.0000
19.250 1.4031 0.10958 0.10544 -0.0411 0.0019 1.0000
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