HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.5/8 AIRFOIL (hq358-il) Reynolds number: 50,000 Max Cl/Cd: 43.3 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq358-il-50000-n5.txt Download as CSV file: xf-hq358-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3563 0.10741 0.10067 -0.0339 1.0000 0.0821
-8.250 -0.3679 0.10643 0.09994 -0.0352 1.0000 0.0833
-8.000 -0.3795 0.10526 0.09892 -0.0355 1.0000 0.0837
-7.750 -0.3662 0.10003 0.09364 -0.0334 1.0000 0.0856
-7.500 -0.3621 0.09685 0.09052 -0.0317 1.0000 0.0881
-7.250 -0.3668 0.09469 0.08847 -0.0304 1.0000 0.0904
-7.000 -0.3731 0.09263 0.08652 -0.0297 1.0000 0.0926
-6.750 -0.3828 0.09087 0.08489 -0.0314 1.0000 0.0960
-6.500 -0.3933 0.08909 0.08317 -0.0384 1.0000 0.0976
-6.250 -0.3884 0.08498 0.07918 -0.0330 1.0000 0.0994
-6.000 -0.3863 0.08211 0.07636 -0.0314 1.0000 0.1016
-5.750 -0.3845 0.07923 0.07352 -0.0316 1.0000 0.1046
-5.250 -0.3764 0.07260 0.06691 -0.0361 1.0000 0.1145
-5.000 -0.3457 0.06551 0.05942 -0.0436 1.0000 0.0547
-4.750 -0.3208 0.06020 0.05371 -0.0491 1.0000 0.0435
-4.500 -0.3111 0.05679 0.05035 -0.0481 1.0000 0.0408
-4.250 -0.2920 0.05302 0.04640 -0.0501 1.0000 0.0397
-4.000 -0.2684 0.04928 0.04237 -0.0526 1.0000 0.0396
-3.750 -0.2416 0.04573 0.03843 -0.0551 1.0000 0.0403
-3.500 -0.2129 0.04240 0.03464 -0.0573 1.0000 0.0409
-3.250 -0.1745 0.03890 0.03061 -0.0609 0.9968 0.0407
-3.000 -0.1352 0.03577 0.02693 -0.0640 0.9933 0.0400
-2.750 -0.0961 0.03303 0.02361 -0.0665 0.9896 0.0399
-2.500 -0.0571 0.03076 0.02071 -0.0686 0.9862 0.0404
-2.250 -0.0213 0.02889 0.01833 -0.0696 0.9820 0.0417
-2.000 0.0130 0.02736 0.01646 -0.0703 0.9777 0.0435
-1.750 0.0471 0.02624 0.01519 -0.0716 0.9736 0.0516
-1.500 0.0795 0.02532 0.01405 -0.0725 0.9680 0.0623
-1.250 0.1172 0.02434 0.01294 -0.0746 0.9634 0.0940
-1.000 0.1502 0.02126 0.01240 -0.0760 0.9617 0.6790
-0.750 0.1706 0.02053 0.01179 -0.0731 0.9522 1.0000
-0.500 0.2077 0.02088 0.01159 -0.0753 0.9458 1.0000
-0.250 0.2415 0.02120 0.01151 -0.0770 0.9379 1.0000
0.000 0.2758 0.02153 0.01151 -0.0787 0.9304 1.0000
0.250 0.3118 0.02187 0.01152 -0.0807 0.9228 1.0000
0.500 0.3435 0.02218 0.01161 -0.0819 0.9137 1.0000
0.750 0.3807 0.02248 0.01173 -0.0840 0.9060 1.0000
1.000 0.4138 0.02276 0.01187 -0.0853 0.8965 1.0000
1.250 0.4456 0.02304 0.01204 -0.0863 0.8864 1.0000
1.500 0.4805 0.02327 0.01220 -0.0878 0.8770 1.0000
1.750 0.5177 0.02343 0.01232 -0.0896 0.8679 1.0000
2.000 0.5508 0.02355 0.01243 -0.0905 0.8557 1.0000
2.250 0.5876 0.02345 0.01236 -0.0916 0.8419 1.0000
2.500 0.6245 0.02321 0.01215 -0.0925 0.8272 1.0000
2.750 0.6561 0.02307 0.01206 -0.0925 0.8115 1.0000
3.000 0.6857 0.02303 0.01209 -0.0923 0.7963 1.0000
3.250 0.7154 0.02299 0.01222 -0.0921 0.7814 1.0000
3.500 0.7450 0.02291 0.01226 -0.0918 0.7656 1.0000
3.750 0.7753 0.02278 0.01225 -0.0915 0.7492 1.0000
4.000 0.8065 0.02257 0.01219 -0.0912 0.7320 1.0000
4.250 0.8318 0.02257 0.01234 -0.0901 0.7099 1.0000
4.500 0.8597 0.02246 0.01249 -0.0892 0.6866 1.0000
4.750 0.8875 0.02236 0.01255 -0.0883 0.6599 1.0000
5.000 0.9145 0.02232 0.01265 -0.0872 0.6286 1.0000
5.250 0.9412 0.02235 0.01278 -0.0861 0.5923 1.0000
5.500 0.9669 0.02252 0.01297 -0.0848 0.5514 1.0000
5.750 0.9911 0.02289 0.01343 -0.0834 0.5077 1.0000
6.000 1.0135 0.02350 0.01397 -0.0819 0.4655 1.0000
6.250 1.0345 0.02430 0.01471 -0.0805 0.4273 1.0000
6.500 1.0549 0.02520 0.01560 -0.0791 0.3937 1.0000
6.750 1.0747 0.02617 0.01662 -0.0777 0.3623 1.0000
7.000 1.0936 0.02719 0.01774 -0.0763 0.3319 1.0000
7.250 1.1111 0.02825 0.01892 -0.0747 0.3019 1.0000
7.500 1.1267 0.02940 0.02029 -0.0729 0.2712 1.0000
7.750 1.1350 0.03064 0.02157 -0.0703 0.2296 1.0000
8.000 1.1363 0.03210 0.02283 -0.0673 0.1582 1.0000
8.250 1.1342 0.03524 0.02494 -0.0647 0.0714 1.0000
8.500 1.1379 0.03826 0.02771 -0.0623 0.0428 1.0000
8.750 1.1420 0.04088 0.03038 -0.0598 0.0341 1.0000
9.000 1.1468 0.04337 0.03313 -0.0573 0.0299 1.0000
9.250 1.1504 0.04595 0.03590 -0.0551 0.0274 1.0000
9.500 1.1523 0.04887 0.03898 -0.0529 0.0258 1.0000
9.750 1.1597 0.05176 0.04214 -0.0510 0.0246 1.0000
10.000 1.1699 0.05479 0.04554 -0.0493 0.0236 1.0000
10.250 1.1784 0.05816 0.04930 -0.0477 0.0228 1.0000
10.500 1.1823 0.06184 0.05337 -0.0462 0.0223 1.0000
10.750 1.1808 0.06581 0.05772 -0.0449 0.0220 1.0000
11.000 1.1745 0.07002 0.06228 -0.0440 0.0217 1.0000
11.250 1.1645 0.07460 0.06719 -0.0438 0.0216 1.0000
11.500 1.1517 0.07962 0.07250 -0.0443 0.0215 1.0000
11.750 1.1369 0.08516 0.07832 -0.0457 0.0216 1.0000
12.000 1.1204 0.09134 0.08473 -0.0482 0.0217 1.0000
12.250 1.1033 0.09816 0.09176 -0.0516 0.0219 1.0000
12.500 1.0861 0.10572 0.09949 -0.0561 0.0222 1.0000
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Polar data table (+)
Polar graphs
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