HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/8 AIRFOIL (hq308-il) Reynolds number: 50,000 Max Cl/Cd: 42.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq308-il-50000-n5.txt Download as CSV file: xf-hq308-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/8 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3810 0.09815 0.09158 -0.0311 1.0000 0.0925
-7.750 -0.3870 0.09602 0.08958 -0.0318 1.0000 0.0954
-7.500 -0.4077 0.09504 0.08881 -0.0362 1.0000 0.0977
-7.250 -0.4041 0.09106 0.08494 -0.0352 1.0000 0.0989
-7.000 -0.3983 0.08763 0.08148 -0.0332 1.0000 0.1005
-6.750 -0.3974 0.08454 0.07846 -0.0330 1.0000 0.1022
-6.500 -0.3978 0.08149 0.07549 -0.0338 1.0000 0.1033
-6.250 -0.3910 0.07592 0.06986 -0.0379 1.0000 0.0644
-6.000 -0.3823 0.06992 0.06368 -0.0452 1.0000 0.0432
-5.750 -0.3788 0.06663 0.06039 -0.0433 1.0000 0.0414
-5.500 -0.3724 0.06314 0.05685 -0.0439 1.0000 0.0400
-5.250 -0.3628 0.05936 0.05297 -0.0451 1.0000 0.0386
-5.000 -0.3498 0.05550 0.04894 -0.0468 1.0000 0.0381
-4.750 -0.3336 0.05169 0.04489 -0.0485 1.0000 0.0382
-4.500 -0.3144 0.04808 0.04097 -0.0501 1.0000 0.0388
-4.250 -0.2926 0.04459 0.03710 -0.0516 1.0000 0.0397
-4.000 -0.2685 0.04121 0.03327 -0.0529 1.0000 0.0402
-3.750 -0.2431 0.03806 0.02967 -0.0538 1.0000 0.0399
-3.500 -0.2164 0.03515 0.02626 -0.0545 1.0000 0.0395
-3.250 -0.1890 0.03257 0.02318 -0.0549 1.0000 0.0397
-3.000 -0.1616 0.03036 0.02049 -0.0549 1.0000 0.0403
-2.750 -0.1340 0.02841 0.01805 -0.0545 1.0000 0.0417
-2.500 -0.1081 0.02691 0.01615 -0.0538 1.0000 0.0433
-2.250 -0.0785 0.02551 0.01460 -0.0543 0.9971 0.0497
-2.000 -0.0446 0.02443 0.01328 -0.0553 0.9923 0.0607
-1.750 -0.0083 0.02340 0.01204 -0.0570 0.9876 0.0833
-1.500 0.0302 0.02187 0.01080 -0.0598 0.9836 0.1561
-1.250 0.0462 0.01934 0.01086 -0.0564 0.9794 0.7806
-1.000 0.0811 0.01896 0.01030 -0.0571 0.9707 1.0000
-0.750 0.1181 0.01928 0.01006 -0.0595 0.9635 1.0000
-0.500 0.1537 0.01960 0.00998 -0.0616 0.9559 1.0000
-0.250 0.1914 0.01994 0.00999 -0.0641 0.9487 1.0000
0.000 0.2246 0.02025 0.01004 -0.0657 0.9399 1.0000
0.250 0.2621 0.02058 0.01010 -0.0680 0.9323 1.0000
0.500 0.2964 0.02088 0.01022 -0.0698 0.9231 1.0000
0.750 0.3298 0.02117 0.01038 -0.0712 0.9134 1.0000
1.000 0.3667 0.02144 0.01053 -0.0733 0.9046 1.0000
1.250 0.4028 0.02168 0.01070 -0.0751 0.8949 1.0000
1.500 0.4352 0.02193 0.01090 -0.0762 0.8839 1.0000
1.750 0.4690 0.02215 0.01111 -0.0774 0.8731 1.0000
2.000 0.5045 0.02231 0.01132 -0.0789 0.8625 1.0000
2.250 0.5407 0.02239 0.01142 -0.0802 0.8514 1.0000
2.500 0.5754 0.02240 0.01149 -0.0811 0.8385 1.0000
2.750 0.6069 0.02241 0.01158 -0.0813 0.8240 1.0000
3.000 0.6374 0.02242 0.01175 -0.0813 0.8087 1.0000
3.250 0.6677 0.02239 0.01184 -0.0812 0.7928 1.0000
3.500 0.6986 0.02229 0.01187 -0.0810 0.7763 1.0000
3.750 0.7311 0.02206 0.01178 -0.0808 0.7590 1.0000
4.000 0.7576 0.02197 0.01185 -0.0798 0.7368 1.0000
4.250 0.7862 0.02178 0.01191 -0.0788 0.7134 1.0000
4.500 0.8138 0.02163 0.01192 -0.0777 0.6874 1.0000
4.750 0.8402 0.02157 0.01202 -0.0765 0.6578 1.0000
5.000 0.8670 0.02153 0.01211 -0.0752 0.6243 1.0000
5.250 0.8920 0.02161 0.01228 -0.0738 0.5845 1.0000
5.500 0.9160 0.02183 0.01263 -0.0721 0.5383 1.0000
5.750 0.9384 0.02226 0.01298 -0.0704 0.4878 1.0000
6.000 0.9585 0.02296 0.01356 -0.0686 0.4363 1.0000
6.250 0.9769 0.02387 0.01435 -0.0668 0.3874 1.0000
6.500 0.9940 0.02494 0.01531 -0.0650 0.3407 1.0000
6.750 1.0096 0.02612 0.01636 -0.0632 0.2965 1.0000
7.000 1.0242 0.02737 0.01753 -0.0615 0.2531 1.0000
7.250 1.0386 0.02871 0.01881 -0.0598 0.2128 1.0000
7.500 1.0519 0.03021 0.02036 -0.0581 0.1743 1.0000
7.750 1.0657 0.03193 0.02210 -0.0565 0.1383 1.0000
8.000 1.0774 0.03390 0.02396 -0.0547 0.1060 1.0000
8.250 1.0886 0.03624 0.02626 -0.0528 0.0790 1.0000
8.500 1.0965 0.03844 0.02838 -0.0511 0.0532 1.0000
8.750 1.1048 0.04081 0.03080 -0.0493 0.0383 1.0000
9.000 1.1118 0.04351 0.03364 -0.0472 0.0322 1.0000
9.250 1.1240 0.04638 0.03688 -0.0452 0.0287 1.0000
9.500 1.1338 0.04932 0.04010 -0.0434 0.0263 1.0000
9.750 1.1404 0.05246 0.04348 -0.0416 0.0248 1.0000
10.000 1.1439 0.05615 0.04740 -0.0400 0.0237 1.0000
10.250 1.1444 0.06009 0.05165 -0.0382 0.0231 1.0000
10.500 1.1401 0.06397 0.05593 -0.0366 0.0228 1.0000
10.750 1.1316 0.06808 0.06039 -0.0355 0.0227 1.0000
11.000 1.1197 0.07253 0.06517 -0.0350 0.0226 1.0000
11.250 1.1057 0.07739 0.07031 -0.0354 0.0225 1.0000
11.500 1.0898 0.08279 0.07596 -0.0369 0.0226 1.0000
11.750 1.0732 0.08876 0.08214 -0.0393 0.0227 1.0000
12.000 1.0566 0.09529 0.08884 -0.0427 0.0228 1.0000
12.250 1.0404 0.10245 0.09614 -0.0469 0.0230 1.0000
12.500 1.0250 0.11022 0.10403 -0.0518 0.0232 1.0000
12.750 1.0111 0.11841 0.11231 -0.0570 0.0233 1.0000
13.000 0.9929 0.12995 0.12407 -0.0648 0.0243 1.0000
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Polar data table (+)
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