HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il) Reynolds number: 100,000 Max Cl/Cd: 60.86 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3510-il-100000-n5.txt Download as CSV file: xf-hq3510-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2718 0.09543 0.09116 -0.0359 1.0000 0.0455
-8.750 -0.2784 0.09305 0.08885 -0.0346 1.0000 0.0458
-8.500 -0.2863 0.09070 0.08657 -0.0333 1.0000 0.0460
-8.250 -0.2865 0.08710 0.08301 -0.0344 0.9980 0.0460
-8.000 -0.3583 0.09253 0.08812 -0.0367 1.0000 0.0443
-7.750 -0.3733 0.09080 0.08650 -0.0347 1.0000 0.0438
-7.500 -0.3863 0.08927 0.08506 -0.0320 1.0000 0.0444
-7.250 -0.3776 0.08463 0.08044 -0.0378 0.9932 0.0441
-7.000 -0.3568 0.07541 0.07114 -0.0501 0.9847 0.0278
-6.750 -0.3416 0.06977 0.06547 -0.0569 0.9770 0.0266
-6.500 -0.3228 0.06344 0.05902 -0.0649 0.9700 0.0253
-6.250 -0.3030 0.05714 0.05253 -0.0722 0.9624 0.0242
-6.000 -0.2807 0.05080 0.04588 -0.0784 0.9558 0.0231
-5.750 -0.2564 0.04469 0.03934 -0.0831 0.9491 0.0222
-5.500 -0.2243 0.03871 0.03276 -0.0878 0.9454 0.0216
-5.250 -0.2016 0.03485 0.02840 -0.0889 0.9382 0.0215
-5.000 -0.1696 0.03148 0.02447 -0.0912 0.9343 0.0219
-4.750 -0.1344 0.02940 0.02202 -0.0936 0.9316 0.0243
-4.500 -0.1097 0.02741 0.01959 -0.0933 0.9248 0.0264
-4.250 -0.0760 0.02510 0.01679 -0.0945 0.9212 0.0273
-4.000 -0.0404 0.02317 0.01447 -0.0958 0.9187 0.0286
-3.750 -0.0142 0.02174 0.01285 -0.0954 0.9129 0.0301
-3.500 0.0159 0.02055 0.01161 -0.0960 0.9083 0.0334
-3.250 0.0496 0.01958 0.01048 -0.0970 0.9051 0.0408
-3.000 0.0759 0.01894 0.00986 -0.0969 0.8991 0.0566
-2.750 0.1061 0.01843 0.00934 -0.0976 0.8941 0.0825
-2.500 0.1398 0.01773 0.00864 -0.0989 0.8907 0.1070
-2.250 0.1651 0.01717 0.00819 -0.0986 0.8839 0.1473
-2.000 0.1918 0.01568 0.00804 -0.0993 0.8793 0.4888
-1.750 0.2196 0.01545 0.00812 -0.0986 0.8752 0.6371
-1.500 0.2398 0.01549 0.00825 -0.0965 0.8674 0.7038
-1.250 0.2647 0.01539 0.00820 -0.0947 0.8630 0.7680
-1.000 0.2819 0.01535 0.00820 -0.0918 0.8551 0.8135
-0.750 0.3099 0.01516 0.00795 -0.0913 0.8501 0.8396
-0.500 0.3359 0.01509 0.00780 -0.0907 0.8428 0.8560
-0.250 0.3659 0.01493 0.00756 -0.0909 0.8369 0.8747
0.000 0.3960 0.01480 0.00739 -0.0911 0.8302 0.8983
0.250 0.4340 0.01465 0.00720 -0.0930 0.8238 0.9334
0.500 0.4719 0.01454 0.00700 -0.0951 0.8164 1.0000
0.750 0.5037 0.01445 0.00679 -0.0958 0.8077 1.0000
1.000 0.5318 0.01442 0.00667 -0.0958 0.7964 1.0000
1.250 0.5607 0.01435 0.00652 -0.0958 0.7847 1.0000
1.500 0.5897 0.01427 0.00636 -0.0958 0.7727 1.0000
1.750 0.6187 0.01422 0.00624 -0.0958 0.7612 1.0000
2.000 0.6484 0.01419 0.00614 -0.0959 0.7508 1.0000
2.250 0.6749 0.01427 0.00623 -0.0957 0.7389 1.0000
2.500 0.7018 0.01434 0.00627 -0.0954 0.7266 1.0000
2.750 0.7290 0.01440 0.00632 -0.0951 0.7137 1.0000
3.000 0.7561 0.01446 0.00637 -0.0949 0.7001 1.0000
3.250 0.7831 0.01453 0.00646 -0.0945 0.6852 1.0000
3.500 0.8100 0.01460 0.00652 -0.0941 0.6692 1.0000
3.750 0.8363 0.01471 0.00662 -0.0937 0.6513 1.0000
4.000 0.8615 0.01485 0.00676 -0.0930 0.6306 1.0000
4.250 0.8868 0.01500 0.00694 -0.0923 0.6078 1.0000
4.500 0.9115 0.01518 0.00709 -0.0916 0.5811 1.0000
4.750 0.9354 0.01543 0.00727 -0.0907 0.5499 1.0000
5.000 0.9585 0.01575 0.00748 -0.0896 0.5153 1.0000
5.250 0.9804 0.01618 0.00781 -0.0885 0.4778 1.0000
5.500 1.0012 0.01671 0.00818 -0.0872 0.4417 1.0000
5.750 1.0215 0.01730 0.00864 -0.0860 0.4079 1.0000
6.000 1.0416 0.01793 0.00917 -0.0847 0.3786 1.0000
6.250 1.0618 0.01856 0.00974 -0.0836 0.3533 1.0000
6.500 1.0819 0.01922 0.01037 -0.0824 0.3319 1.0000
6.750 1.1023 0.01986 0.01101 -0.0814 0.3129 1.0000
7.000 1.1224 0.02053 0.01168 -0.0803 0.2958 1.0000
7.250 1.1422 0.02121 0.01239 -0.0792 0.2801 1.0000
7.500 1.1617 0.02192 0.01313 -0.0780 0.2651 1.0000
7.750 1.1810 0.02262 0.01391 -0.0768 0.2508 1.0000
8.000 1.1998 0.02333 0.01477 -0.0756 0.2366 1.0000
8.250 1.2160 0.02408 0.01556 -0.0741 0.2191 1.0000
8.500 1.2313 0.02477 0.01634 -0.0724 0.1954 1.0000
8.750 1.2450 0.02555 0.01714 -0.0706 0.1691 1.0000
9.000 1.2549 0.02654 0.01800 -0.0684 0.1382 1.0000
9.250 1.2614 0.02796 0.01914 -0.0659 0.0991 1.0000
9.500 1.2661 0.02974 0.02062 -0.0635 0.0621 1.0000
9.750 1.2705 0.03161 0.02237 -0.0610 0.0377 1.0000
10.000 1.2724 0.03371 0.02445 -0.0582 0.0249 1.0000
10.250 1.2722 0.03598 0.02675 -0.0555 0.0202 1.0000
10.500 1.2746 0.03799 0.02900 -0.0532 0.0180 1.0000
10.750 1.2755 0.04016 0.03143 -0.0510 0.0164 1.0000
11.000 1.2750 0.04251 0.03396 -0.0492 0.0150 1.0000
11.250 1.2710 0.04527 0.03689 -0.0474 0.0139 1.0000
11.500 1.2646 0.04840 0.04017 -0.0459 0.0131 1.0000
11.750 1.2631 0.05119 0.04320 -0.0449 0.0125 1.0000
12.000 1.2605 0.05423 0.04645 -0.0441 0.0118 1.0000
12.250 1.2562 0.05761 0.05005 -0.0436 0.0114 1.0000
12.500 1.2511 0.06125 0.05390 -0.0434 0.0111 1.0000
12.750 1.2455 0.06515 0.05799 -0.0435 0.0109 1.0000
13.000 1.2393 0.06929 0.06233 -0.0439 0.0107 1.0000
13.250 1.2330 0.07364 0.06688 -0.0446 0.0105 1.0000
13.500 1.2264 0.07823 0.07167 -0.0457 0.0103 1.0000
13.750 1.2195 0.08309 0.07672 -0.0470 0.0102 1.0000
14.000 1.2119 0.08826 0.08210 -0.0487 0.0101 1.0000
14.250 1.2037 0.09379 0.08782 -0.0508 0.0100 1.0000
14.500 1.1949 0.09964 0.09388 -0.0533 0.0099 1.0000
14.750 1.1854 0.10590 0.10035 -0.0563 0.0099 1.0000
15.000 1.1748 0.11264 0.10729 -0.0598 0.0099 1.0000
15.250 1.1638 0.11977 0.11461 -0.0637 0.0099 1.0000
15.500 1.1520 0.12737 0.12241 -0.0680 0.0099 1.0000
15.750 1.1393 0.13552 0.13074 -0.0729 0.0100 1.0000
16.000 1.1261 0.14424 0.13963 -0.0782 0.0101 1.0000
16.250 1.1120 0.15362 0.14916 -0.0840 0.0103 1.0000
16.500 1.0975 0.16367 0.15933 -0.0901 0.0105 1.0000
16.750 1.0818 0.17483 0.17060 -0.0967 0.0108 1.0000
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