HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il) Reynolds number: 200,000 Max Cl/Cd: 68.1 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq3518-il-200000.txt Download as CSV file: xf-hq3518-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/18 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5044 0.09081 0.08716 -0.0725 1.0000 0.0619
-13.000 -0.5362 0.08058 0.07684 -0.0796 0.9975 0.0609
-12.750 -0.5754 0.06846 0.06449 -0.0910 0.9919 0.0599
-12.500 -0.6111 0.05897 0.05467 -0.1005 0.9839 0.0594
-12.250 -0.6339 0.05231 0.04764 -0.1071 0.9750 0.0594
-12.000 -0.6429 0.04717 0.04208 -0.1124 0.9678 0.0599
-11.750 -0.6508 0.04369 0.03819 -0.1135 0.9565 0.0605
-11.500 -0.6466 0.04056 0.03461 -0.1146 0.9486 0.0612
-11.250 -0.6338 0.03770 0.03145 -0.1154 0.9416 0.0624
-11.000 -0.6003 0.03614 0.02992 -0.1178 0.9388 0.0640
-10.750 -0.5829 0.03509 0.02880 -0.1172 0.9303 0.0654
-10.500 -0.5618 0.03348 0.02698 -0.1177 0.9246 0.0670
-10.250 -0.5457 0.03198 0.02521 -0.1170 0.9180 0.0684
-10.000 -0.5317 0.03089 0.02379 -0.1156 0.9102 0.0698
-9.750 -0.5048 0.02907 0.02190 -0.1164 0.9065 0.0718
-9.500 -0.4853 0.02832 0.02114 -0.1155 0.8997 0.0737
-9.250 -0.4627 0.02745 0.02018 -0.1151 0.8938 0.0757
-9.000 -0.4373 0.02648 0.01902 -0.1150 0.8897 0.0780
-8.750 -0.4203 0.02607 0.01839 -0.1135 0.8829 0.0799
-8.500 -0.3947 0.02469 0.01710 -0.1135 0.8781 0.0827
-8.250 -0.3691 0.02398 0.01636 -0.1134 0.8742 0.0857
-8.000 -0.3428 0.02333 0.01559 -0.1133 0.8708 0.0888
-7.750 -0.3258 0.02306 0.01520 -0.1117 0.8638 0.0913
-7.500 -0.3008 0.02198 0.01423 -0.1115 0.8593 0.0952
-7.250 -0.2751 0.02138 0.01360 -0.1112 0.8555 0.0995
-7.000 -0.2541 0.02109 0.01321 -0.1102 0.8503 0.1031
-6.750 -0.2353 0.02032 0.01256 -0.1089 0.8445 0.1078
-6.500 -0.2123 0.01980 0.01204 -0.1083 0.8403 0.1131
-6.250 -0.1879 0.01922 0.01142 -0.1078 0.8369 0.1189
-6.000 -0.1736 0.01887 0.01117 -0.1059 0.8305 0.1250
-5.750 -0.1529 0.01848 0.01077 -0.1049 0.8256 0.1327
-5.500 -0.1301 0.01797 0.01033 -0.1043 0.8220 0.1441
-5.250 -0.1052 0.01750 0.00995 -0.1040 0.8191 0.1624
-5.000 -0.0903 0.01729 0.00992 -0.1023 0.8127 0.1927
-4.750 -0.0720 0.01659 0.00953 -0.1012 0.8079 0.2484
-4.500 -0.0499 0.01579 0.00907 -0.1007 0.8043 0.3293
-4.250 -0.0278 0.01523 0.00907 -0.0998 0.8012 0.4614
-4.000 -0.0093 0.01545 0.00935 -0.0982 0.7945 0.5064
-3.750 0.0170 0.01549 0.00940 -0.0976 0.7901 0.5354
-3.500 0.0462 0.01554 0.00943 -0.0974 0.7871 0.5588
-3.250 0.0764 0.01565 0.00950 -0.0974 0.7847 0.5779
-3.000 0.0969 0.01601 0.00989 -0.0960 0.7794 0.5913
-2.750 0.1214 0.01624 0.01009 -0.0953 0.7748 0.6044
-2.500 0.1499 0.01639 0.01021 -0.0950 0.7714 0.6166
-2.250 0.1804 0.01650 0.01029 -0.0950 0.7688 0.6269
-2.000 0.2091 0.01663 0.01032 -0.0950 0.7655 0.6382
-1.750 0.2286 0.01693 0.01071 -0.0933 0.7590 0.6444
-1.500 0.2580 0.01690 0.01061 -0.0932 0.7544 0.6530
-1.250 0.2905 0.01682 0.01048 -0.0934 0.7509 0.6615
-1.000 0.3146 0.01700 0.01066 -0.0925 0.7453 0.6707
-0.750 0.3393 0.01702 0.01066 -0.0918 0.7393 0.6772
-0.500 0.3700 0.01691 0.01052 -0.0920 0.7353 0.6818
-0.250 0.4035 0.01677 0.01029 -0.0927 0.7321 0.6878
0.000 0.4234 0.01690 0.01043 -0.0915 0.7247 0.6940
0.250 0.4518 0.01678 0.01031 -0.0913 0.7193 0.6981
0.500 0.4851 0.01658 0.01005 -0.0919 0.7153 0.7032
0.750 0.5082 0.01666 0.01012 -0.0913 0.7088 0.7093
1.000 0.5344 0.01660 0.01008 -0.0908 0.7028 0.7142
1.250 0.5658 0.01647 0.00991 -0.0912 0.6986 0.7195
1.500 0.5917 0.01649 0.00993 -0.0909 0.6925 0.7255
1.750 0.6167 0.01642 0.00986 -0.0904 0.6854 0.7309
2.000 0.6491 0.01621 0.00961 -0.0909 0.6803 0.7358
2.250 0.6712 0.01622 0.00967 -0.0898 0.6721 0.7422
2.500 0.7001 0.01607 0.00947 -0.0899 0.6653 0.7484
2.750 0.7284 0.01594 0.00935 -0.0898 0.6588 0.7534
3.000 0.7510 0.01590 0.00935 -0.0888 0.6501 0.7598
3.250 0.7840 0.01573 0.00909 -0.0896 0.6443 0.7664
3.500 0.8022 0.01573 0.00920 -0.0878 0.6345 0.7723
3.750 0.8333 0.01555 0.00895 -0.0882 0.6272 0.7800
4.000 0.8518 0.01551 0.00899 -0.0864 0.6162 0.7871
4.250 0.8782 0.01536 0.00882 -0.0859 0.6071 0.7949
4.500 0.8991 0.01529 0.00877 -0.0846 0.5957 0.8030
4.750 0.9193 0.01524 0.00876 -0.0830 0.5844 0.8109
5.000 0.9441 0.01517 0.00864 -0.0824 0.5740 0.8195
5.250 0.9617 0.01515 0.00866 -0.0804 0.5612 0.8281
5.500 0.9799 0.01517 0.00870 -0.0786 0.5481 0.8375
5.750 0.9984 0.01520 0.00873 -0.0768 0.5357 0.8473
6.000 1.0168 0.01524 0.00876 -0.0751 0.5228 0.8574
6.250 1.0333 0.01535 0.00882 -0.0730 0.5089 0.8692
6.500 1.0450 0.01545 0.00895 -0.0700 0.4949 0.8821
6.750 1.0573 0.01561 0.00911 -0.0672 0.4810 0.8981
7.000 1.0726 0.01584 0.00934 -0.0651 0.4668 0.9215
7.250 1.1025 0.01619 0.00968 -0.0662 0.4501 1.0000
7.500 1.1209 0.01670 0.01008 -0.0654 0.4353 1.0000
7.750 1.1388 0.01724 0.01050 -0.0644 0.4213 1.0000
8.000 1.1525 0.01779 0.01101 -0.0627 0.4074 1.0000
8.250 1.1660 0.01835 0.01156 -0.0610 0.3943 1.0000
8.500 1.1792 0.01893 0.01210 -0.0592 0.3819 1.0000
8.750 1.1908 0.01956 0.01266 -0.0573 0.3698 1.0000
9.000 1.2010 0.02023 0.01332 -0.0552 0.3569 1.0000
9.250 1.2113 0.02096 0.01402 -0.0533 0.3451 1.0000
9.500 1.2212 0.02179 0.01476 -0.0513 0.3341 1.0000
9.750 1.2315 0.02268 0.01556 -0.0495 0.3233 1.0000
10.000 1.2428 0.02358 0.01643 -0.0479 0.3126 1.0000
10.250 1.2560 0.02451 0.01723 -0.0466 0.3024 1.0000
10.500 1.2663 0.02549 0.01823 -0.0449 0.2917 1.0000
10.750 1.2779 0.02650 0.01920 -0.0435 0.2815 1.0000
11.000 1.2893 0.02752 0.02015 -0.0421 0.2717 1.0000
11.250 1.2982 0.02861 0.02131 -0.0406 0.2623 1.0000
11.500 1.3108 0.02964 0.02223 -0.0394 0.2539 1.0000
11.750 1.3191 0.03080 0.02350 -0.0380 0.2458 1.0000
12.000 1.3304 0.03187 0.02452 -0.0368 0.2388 1.0000
12.250 1.3410 0.03301 0.02572 -0.0357 0.2321 1.0000
12.500 1.3506 0.03419 0.02693 -0.0345 0.2258 1.0000
12.750 1.3645 0.03523 0.02790 -0.0337 0.2202 1.0000
13.000 1.3736 0.03650 0.02930 -0.0326 0.2147 1.0000
13.250 1.3840 0.03772 0.03054 -0.0317 0.2097 1.0000
13.500 1.3983 0.03877 0.03152 -0.0310 0.2047 1.0000
13.750 1.4050 0.04026 0.03315 -0.0300 0.1999 1.0000
14.000 1.4134 0.04167 0.03459 -0.0291 0.1951 1.0000
14.250 1.4291 0.04268 0.03549 -0.0286 0.1901 1.0000
14.500 1.4349 0.04435 0.03733 -0.0277 0.1863 1.0000
14.750 1.4425 0.04592 0.03897 -0.0270 0.1820 1.0000
15.000 1.4536 0.04724 0.04026 -0.0264 0.1778 1.0000
15.250 1.4650 0.04864 0.04169 -0.0259 0.1737 1.0000
15.500 1.4703 0.05051 0.04371 -0.0252 0.1703 1.0000
15.750 1.4780 0.05219 0.04546 -0.0247 0.1667 1.0000
16.000 1.4900 0.05353 0.04679 -0.0244 0.1632 1.0000
16.250 1.5034 0.05487 0.04814 -0.0240 0.1596 1.0000
16.500 1.5036 0.05729 0.05076 -0.0235 0.1567 1.0000
16.750 1.5068 0.05948 0.05307 -0.0232 0.1534 1.0000
17.000 1.5133 0.06136 0.05499 -0.0230 0.1500 1.0000
17.250 1.5270 0.06264 0.05622 -0.0228 0.1459 1.0000
17.500 1.5187 0.06608 0.05989 -0.0227 0.1430 1.0000
17.750 1.5155 0.06911 0.06306 -0.0228 0.1394 1.0000
18.000 1.5165 0.07169 0.06569 -0.0230 0.1358 1.0000
18.250 1.5196 0.07410 0.06810 -0.0232 0.1316 1.0000
18.500 1.5081 0.07843 0.07266 -0.0240 0.1282 1.0000
18.750 1.5024 0.08212 0.07646 -0.0248 0.1243 1.0000
19.000 1.5050 0.08470 0.07897 -0.0254 0.1201 1.0000
19.250 1.4925 0.08963 0.08414 -0.0268 0.1166 1.0000
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