HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.3 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3013-il-1000000.txt Download as CSV file: xf-hq3013-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/13 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7376 0.06815 0.06587 -0.0653 1.0000 0.0074
-14.000 -0.7635 0.05833 0.05589 -0.0722 1.0000 0.0073
-13.750 -0.7873 0.05043 0.04782 -0.0780 1.0000 0.0073
-13.500 -0.7955 0.04589 0.04316 -0.0811 1.0000 0.0072
-13.250 -0.8166 0.04030 0.03740 -0.0843 1.0000 0.0073
-13.000 -0.8275 0.03666 0.03363 -0.0857 1.0000 0.0073
-12.750 -0.8469 0.03298 0.02980 -0.0858 1.0000 0.0074
-12.500 -0.8649 0.03084 0.02756 -0.0834 1.0000 0.0074
-12.250 -0.8692 0.02832 0.02488 -0.0838 0.9966 0.0075
-12.000 -0.8476 0.02606 0.02246 -0.0867 0.9914 0.0077
-11.750 -0.8239 0.02426 0.02050 -0.0888 0.9869 0.0078
-11.500 -0.7958 0.02284 0.01897 -0.0910 0.9840 0.0080
-11.250 -0.7664 0.02159 0.01760 -0.0931 0.9811 0.0082
-11.000 -0.7406 0.02034 0.01622 -0.0943 0.9751 0.0084
-10.750 -0.7106 0.01922 0.01497 -0.0961 0.9709 0.0086
-10.500 -0.6860 0.01818 0.01380 -0.0966 0.9620 0.0088
-10.250 -0.6604 0.01728 0.01277 -0.0970 0.9536 0.0089
-10.000 -0.6380 0.01654 0.01191 -0.0966 0.9423 0.0092
-9.750 -0.6159 0.01590 0.01117 -0.0960 0.9311 0.0093
-9.500 -0.5935 0.01531 0.01046 -0.0954 0.9206 0.0095
-9.250 -0.5725 0.01452 0.00952 -0.0945 0.9104 0.0097
-9.000 -0.5523 0.01364 0.00852 -0.0936 0.9002 0.0101
-8.750 -0.5294 0.01306 0.00784 -0.0930 0.8918 0.0106
-8.500 -0.5053 0.01261 0.00732 -0.0925 0.8835 0.0111
-8.250 -0.4805 0.01223 0.00687 -0.0921 0.8762 0.0117
-8.000 -0.4552 0.01189 0.00645 -0.0918 0.8690 0.0123
-7.750 -0.4306 0.01142 0.00589 -0.0913 0.8624 0.0131
-7.500 -0.4055 0.01098 0.00541 -0.0910 0.8557 0.0142
-7.250 -0.3796 0.01069 0.00505 -0.0907 0.8498 0.0154
-7.000 -0.3537 0.01031 0.00466 -0.0904 0.8437 0.0179
-6.750 -0.3275 0.01002 0.00436 -0.0902 0.8379 0.0222
-6.500 -0.3006 0.00982 0.00415 -0.0901 0.8326 0.0274
-6.250 -0.2734 0.00965 0.00399 -0.0900 0.8269 0.0312
-6.000 -0.2462 0.00949 0.00379 -0.0899 0.8216 0.0341
-5.750 -0.2189 0.00930 0.00361 -0.0899 0.8164 0.0376
-5.500 -0.1912 0.00918 0.00346 -0.0899 0.8110 0.0399
-5.250 -0.1640 0.00901 0.00323 -0.0898 0.8058 0.0424
-5.000 -0.1366 0.00879 0.00302 -0.0897 0.8007 0.0462
-4.750 -0.1089 0.00866 0.00287 -0.0897 0.7952 0.0495
-4.500 -0.0814 0.00851 0.00267 -0.0896 0.7900 0.0543
-4.250 -0.0537 0.00833 0.00252 -0.0896 0.7846 0.0607
-4.000 -0.0262 0.00815 0.00234 -0.0896 0.7787 0.0694
-3.750 0.0013 0.00800 0.00218 -0.0895 0.7729 0.0802
-3.500 0.0289 0.00779 0.00204 -0.0895 0.7665 0.0982
-3.250 0.0560 0.00757 0.00189 -0.0894 0.7607 0.1300
-3.000 0.0829 0.00722 0.00175 -0.0895 0.7554 0.1915
-2.750 0.1099 0.00688 0.00162 -0.0895 0.7499 0.2585
-2.500 0.1361 0.00646 0.00146 -0.0894 0.7448 0.3500
-2.250 0.1626 0.00605 0.00140 -0.0894 0.7396 0.4649
-2.000 0.1906 0.00595 0.00137 -0.0894 0.7340 0.5013
-1.750 0.2186 0.00592 0.00135 -0.0894 0.7284 0.5264
-1.500 0.2469 0.00586 0.00134 -0.0894 0.7217 0.5492
-1.250 0.2749 0.00587 0.00133 -0.0894 0.7146 0.5650
-1.000 0.3034 0.00586 0.00131 -0.0894 0.7071 0.5751
-0.750 0.3314 0.00588 0.00130 -0.0894 0.6998 0.5845
-0.500 0.3597 0.00587 0.00131 -0.0894 0.6927 0.6001
-0.250 0.3876 0.00589 0.00133 -0.0893 0.6860 0.6160
0.000 0.4160 0.00590 0.00134 -0.0894 0.6794 0.6246
0.250 0.4441 0.00593 0.00136 -0.0894 0.6721 0.6326
0.500 0.4722 0.00595 0.00137 -0.0894 0.6641 0.6402
1.000 0.5276 0.00602 0.00142 -0.0892 0.6445 0.6583
1.250 0.5555 0.00607 0.00145 -0.0892 0.6359 0.6659
1.500 0.5830 0.00611 0.00149 -0.0891 0.6261 0.6725
1.750 0.6108 0.00615 0.00153 -0.0891 0.6154 0.6798
2.000 0.6383 0.00621 0.00157 -0.0889 0.6048 0.6870
2.250 0.6654 0.00628 0.00163 -0.0888 0.5919 0.6950
2.500 0.6922 0.00636 0.00169 -0.0886 0.5771 0.7026
2.750 0.7189 0.00647 0.00176 -0.0883 0.5608 0.7112
3.000 0.7451 0.00659 0.00185 -0.0880 0.5418 0.7198
3.250 0.7707 0.00675 0.00195 -0.0876 0.5210 0.7294
3.500 0.7961 0.00692 0.00207 -0.0872 0.4980 0.7395
3.750 0.8209 0.00712 0.00221 -0.0866 0.4755 0.7497
4.000 0.8457 0.00734 0.00237 -0.0861 0.4511 0.7606
4.250 0.8699 0.00757 0.00254 -0.0855 0.4271 0.7722
4.500 0.8941 0.00780 0.00271 -0.0849 0.4043 0.7845
4.750 0.9180 0.00804 0.00291 -0.0842 0.3822 0.7973
5.000 0.9412 0.00831 0.00311 -0.0834 0.3564 0.8111
5.250 0.9641 0.00857 0.00332 -0.0826 0.3313 0.8260
5.500 0.9862 0.00886 0.00355 -0.0816 0.3079 0.8435
5.750 1.0080 0.00909 0.00377 -0.0805 0.2880 0.8663
6.000 1.0291 0.00918 0.00399 -0.0792 0.2710 0.9360
6.250 1.0603 0.00950 0.00425 -0.0803 0.2530 1.0000
6.500 1.0833 0.00983 0.00450 -0.0796 0.2369 1.0000
6.750 1.1058 0.01016 0.00475 -0.0788 0.2204 1.0000
7.000 1.1282 0.01049 0.00501 -0.0780 0.2055 1.0000
7.250 1.1501 0.01083 0.00530 -0.0771 0.1917 1.0000
7.500 1.1713 0.01120 0.00560 -0.0760 0.1767 1.0000
7.750 1.1916 0.01160 0.00591 -0.0749 0.1614 1.0000
8.000 1.2117 0.01199 0.00624 -0.0737 0.1493 1.0000
8.250 1.2325 0.01232 0.00654 -0.0726 0.1398 1.0000
8.500 1.2520 0.01268 0.00688 -0.0713 0.1299 1.0000
8.750 1.2691 0.01307 0.00723 -0.0696 0.1205 1.0000
9.000 1.2851 0.01349 0.00760 -0.0676 0.1109 1.0000
9.250 1.2997 0.01397 0.00802 -0.0655 0.0990 1.0000
9.500 1.3150 0.01444 0.00846 -0.0636 0.0896 1.0000
9.750 1.3294 0.01497 0.00895 -0.0616 0.0804 1.0000
10.000 1.3427 0.01556 0.00949 -0.0595 0.0707 1.0000
10.250 1.3561 0.01618 0.01006 -0.0575 0.0623 1.0000
10.500 1.3692 0.01682 0.01068 -0.0555 0.0544 1.0000
10.750 1.3817 0.01751 0.01134 -0.0535 0.0477 1.0000
11.000 1.3940 0.01824 0.01206 -0.0516 0.0422 1.0000
11.250 1.4069 0.01895 0.01277 -0.0498 0.0375 1.0000
11.500 1.4169 0.01986 0.01365 -0.0478 0.0315 1.0000
11.750 1.4297 0.02063 0.01443 -0.0462 0.0285 1.0000
12.000 1.4379 0.02171 0.01549 -0.0442 0.0221 1.0000
12.250 1.4466 0.02281 0.01657 -0.0423 0.0175 1.0000
12.500 1.4515 0.02420 0.01793 -0.0403 0.0116 1.0000
12.750 1.4568 0.02563 0.01935 -0.0383 0.0071 1.0000
13.000 1.4603 0.02725 0.02101 -0.0364 0.0053 1.0000
13.250 1.4703 0.02841 0.02223 -0.0351 0.0052 1.0000
13.500 1.4775 0.02984 0.02372 -0.0337 0.0048 1.0000
13.750 1.4845 0.03132 0.02528 -0.0325 0.0046 1.0000
14.000 1.4912 0.03287 0.02691 -0.0313 0.0044 1.0000
14.250 1.4968 0.03455 0.02868 -0.0302 0.0043 1.0000
14.500 1.5009 0.03644 0.03064 -0.0291 0.0041 1.0000
14.750 1.5035 0.03852 0.03281 -0.0281 0.0039 1.0000
15.000 1.5076 0.04053 0.03491 -0.0274 0.0039 1.0000
15.250 1.5079 0.04300 0.03748 -0.0267 0.0038 1.0000
15.500 1.5052 0.04591 0.04049 -0.0261 0.0036 1.0000
15.750 1.5036 0.04880 0.04349 -0.0258 0.0036 1.0000
16.000 1.5050 0.05147 0.04625 -0.0257 0.0036 1.0000
16.250 1.4918 0.05605 0.05097 -0.0259 0.0034 1.0000
16.500 1.4880 0.05965 0.05468 -0.0264 0.0034 1.0000
16.750 1.4771 0.06434 0.05951 -0.0273 0.0033 1.0000
17.000 1.4713 0.06855 0.06383 -0.0283 0.0033 1.0000
17.250 1.4600 0.07374 0.06915 -0.0298 0.0033 1.0000
17.500 1.4515 0.07870 0.07423 -0.0315 0.0033 1.0000
17.750 1.4378 0.08468 0.08035 -0.0338 0.0033 1.0000
18.000 1.4281 0.09021 0.08599 -0.0361 0.0033 1.0000
18.250 1.4143 0.09657 0.09249 -0.0389 0.0033 1.0000
18.500 1.3998 0.10325 0.09930 -0.0420 0.0033 1.0000
18.750 1.3859 0.10997 0.10615 -0.0452 0.0033 1.0000
19.000 1.3682 0.11757 0.11388 -0.0491 0.0033 1.0000
19.250 1.3523 0.12497 0.12141 -0.0530 0.0033 1.0000
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