HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 500,000 Max Cl/Cd: 84.36 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2511-il-500000-n5.txt Download as CSV file: xf-hq2511-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6522 0.04395 0.04141 -0.0683 1.0000 0.0059
-10.250 -0.6867 0.04006 0.03738 -0.0667 1.0000 0.0058
-10.000 -0.6850 0.03380 0.03061 -0.0717 0.9868 0.0059
-9.750 -0.6696 0.02939 0.02572 -0.0750 0.9789 0.0059
-9.500 -0.6472 0.02651 0.02246 -0.0772 0.9724 0.0060
-9.250 -0.6240 0.02420 0.01982 -0.0786 0.9653 0.0061
-9.000 -0.5978 0.02254 0.01789 -0.0798 0.9586 0.0062
-8.750 -0.5737 0.02108 0.01617 -0.0802 0.9505 0.0063
-8.500 -0.5484 0.01987 0.01474 -0.0806 0.9428 0.0065
-8.250 -0.5256 0.01880 0.01348 -0.0803 0.9330 0.0065
-8.000 -0.5022 0.01777 0.01228 -0.0800 0.9239 0.0065
-7.750 -0.4789 0.01680 0.01114 -0.0796 0.9144 0.0066
-7.500 -0.4553 0.01596 0.01017 -0.0791 0.9052 0.0066
-7.250 -0.4312 0.01521 0.00928 -0.0787 0.8967 0.0066
-7.000 -0.4068 0.01454 0.00848 -0.0783 0.8880 0.0066
-6.750 -0.3820 0.01393 0.00776 -0.0779 0.8803 0.0067
-6.500 -0.3570 0.01332 0.00704 -0.0775 0.8728 0.0067
-6.250 -0.3317 0.01276 0.00638 -0.0772 0.8662 0.0068
-6.000 -0.3059 0.01232 0.00582 -0.0769 0.8593 0.0069
-5.750 -0.2799 0.01188 0.00528 -0.0767 0.8530 0.0072
-5.500 -0.2534 0.01152 0.00485 -0.0765 0.8462 0.0073
-5.000 -0.2001 0.01089 0.00406 -0.0761 0.8336 0.0081
-4.750 -0.1733 0.01063 0.00372 -0.0759 0.8266 0.0086
-4.500 -0.1464 0.01036 0.00341 -0.0758 0.8193 0.0102
-4.250 -0.1197 0.01006 0.00313 -0.0756 0.8123 0.0193
-4.000 -0.0925 0.00983 0.00291 -0.0756 0.8060 0.0286
-3.750 -0.0650 0.00966 0.00274 -0.0755 0.7997 0.0359
-3.500 -0.0376 0.00949 0.00258 -0.0755 0.7937 0.0456
-3.250 -0.0101 0.00931 0.00242 -0.0754 0.7868 0.0562
-3.000 0.0173 0.00916 0.00226 -0.0754 0.7805 0.0678
-2.750 0.0450 0.00900 0.00213 -0.0754 0.7733 0.0806
-2.500 0.0723 0.00881 0.00198 -0.0753 0.7668 0.1039
-2.250 0.0987 0.00832 0.00181 -0.0754 0.7596 0.2009
-2.000 0.1244 0.00771 0.00163 -0.0755 0.7528 0.3330
-1.750 0.1511 0.00733 0.00155 -0.0755 0.7467 0.4370
-1.500 0.1779 0.00708 0.00150 -0.0754 0.7397 0.5088
-1.250 0.2051 0.00697 0.00149 -0.0752 0.7316 0.5565
-1.000 0.2324 0.00693 0.00150 -0.0750 0.7233 0.5928
-0.750 0.2600 0.00690 0.00152 -0.0749 0.7154 0.6237
-0.500 0.2873 0.00691 0.00155 -0.0747 0.7081 0.6521
-0.250 0.3152 0.00691 0.00156 -0.0746 0.6999 0.6682
0.000 0.3429 0.00695 0.00156 -0.0745 0.6906 0.6783
0.250 0.3704 0.00699 0.00156 -0.0743 0.6792 0.6867
0.500 0.3981 0.00702 0.00157 -0.0743 0.6685 0.6950
0.750 0.4258 0.00706 0.00160 -0.0742 0.6589 0.7036
1.000 0.4532 0.00711 0.00162 -0.0740 0.6469 0.7110
1.250 0.4807 0.00716 0.00165 -0.0739 0.6355 0.7183
1.500 0.5083 0.00721 0.00170 -0.0738 0.6242 0.7244
1.750 0.5355 0.00728 0.00175 -0.0736 0.6097 0.7311
2.000 0.5620 0.00739 0.00179 -0.0733 0.5878 0.7375
2.250 0.5872 0.00757 0.00186 -0.0728 0.5508 0.7441
2.750 0.6356 0.00815 0.00211 -0.0715 0.4681 0.7584
3.000 0.6608 0.00840 0.00227 -0.0711 0.4435 0.7665
3.250 0.6861 0.00861 0.00243 -0.0707 0.4211 0.7751
3.500 0.7112 0.00883 0.00260 -0.0702 0.3965 0.7858
3.750 0.7359 0.00905 0.00279 -0.0697 0.3679 0.7992
4.500 0.8061 0.00994 0.00347 -0.0675 0.2801 0.8456
4.750 0.8296 0.01013 0.00369 -0.0667 0.2647 0.8675
5.000 0.8521 0.01026 0.00390 -0.0656 0.2498 0.9081
5.250 0.8858 0.01050 0.00415 -0.0671 0.2311 1.0000
5.500 0.9100 0.01087 0.00442 -0.0666 0.2096 1.0000
5.750 0.9333 0.01130 0.00473 -0.0661 0.1837 1.0000
6.250 0.9788 0.01224 0.00542 -0.0648 0.1349 1.0000
6.500 1.0020 0.01266 0.00578 -0.0642 0.1198 1.0000
6.750 1.0249 0.01308 0.00614 -0.0635 0.1063 1.0000
7.000 1.0480 0.01348 0.00651 -0.0629 0.0957 1.0000
7.250 1.0703 0.01392 0.00692 -0.0622 0.0830 1.0000
7.500 1.0904 0.01455 0.00742 -0.0611 0.0610 1.0000
7.750 1.1038 0.01574 0.00831 -0.0592 0.0219 1.0000
8.000 1.1239 0.01633 0.00891 -0.0581 0.0171 1.0000
8.250 1.1434 0.01695 0.00957 -0.0569 0.0145 1.0000
8.500 1.1638 0.01745 0.01014 -0.0559 0.0136 1.0000
8.750 1.1832 0.01801 0.01076 -0.0547 0.0126 1.0000
9.000 1.2013 0.01863 0.01144 -0.0533 0.0116 1.0000
9.250 1.2161 0.01941 0.01227 -0.0515 0.0106 1.0000
9.500 1.2311 0.02005 0.01299 -0.0496 0.0102 1.0000
9.750 1.2455 0.02071 0.01374 -0.0477 0.0098 1.0000
10.000 1.2587 0.02146 0.01456 -0.0457 0.0094 1.0000
10.250 1.2710 0.02226 0.01544 -0.0437 0.0091 1.0000
10.500 1.2829 0.02311 0.01636 -0.0417 0.0087 1.0000
10.750 1.2934 0.02406 0.01740 -0.0397 0.0084 1.0000
11.000 1.3032 0.02509 0.01850 -0.0378 0.0081 1.0000
11.250 1.3102 0.02634 0.01982 -0.0357 0.0077 1.0000
11.500 1.3123 0.02801 0.02159 -0.0334 0.0075 1.0000
11.750 1.3210 0.02923 0.02292 -0.0318 0.0073 1.0000
12.000 1.3292 0.03054 0.02433 -0.0303 0.0071 1.0000
12.250 1.3360 0.03202 0.02592 -0.0289 0.0068 1.0000
12.500 1.3398 0.03381 0.02782 -0.0274 0.0067 1.0000
12.750 1.3434 0.03570 0.02982 -0.0261 0.0065 1.0000
13.000 1.3472 0.03764 0.03187 -0.0251 0.0064 1.0000
13.250 1.3489 0.03987 0.03421 -0.0242 0.0062 1.0000
13.500 1.3494 0.04232 0.03677 -0.0235 0.0061 1.0000
13.750 1.3501 0.04484 0.03940 -0.0230 0.0059 1.0000
14.000 1.3498 0.04759 0.04227 -0.0227 0.0058 1.0000
14.250 1.3486 0.05056 0.04535 -0.0227 0.0057 1.0000
14.500 1.3458 0.05386 0.04878 -0.0230 0.0056 1.0000
14.750 1.3410 0.05759 0.05264 -0.0236 0.0056 1.0000
15.000 1.3359 0.06156 0.05673 -0.0245 0.0055 1.0000
15.250 1.3291 0.06599 0.06128 -0.0258 0.0054 1.0000
15.500 1.3211 0.07084 0.06626 -0.0276 0.0053 1.0000
15.750 1.3116 0.07615 0.07171 -0.0296 0.0052 1.0000
16.000 1.3012 0.08184 0.07753 -0.0321 0.0052 1.0000
16.250 1.2872 0.08833 0.08416 -0.0350 0.0051 1.0000
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