HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/8 AIRFOIL (hq258-il) Reynolds number: 500,000 Max Cl/Cd: 108.1 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq258-il-500000.txt Download as CSV file: xf-hq258-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/8 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3217 0.08373 0.08162 -0.0320 1.0000 0.0138
-8.500 -0.3209 0.07993 0.07784 -0.0330 1.0000 0.0139
-8.250 -0.3209 0.07617 0.07411 -0.0339 1.0000 0.0139
-8.000 -0.3221 0.07244 0.07041 -0.0348 1.0000 0.0139
-7.750 -0.3252 0.06882 0.06683 -0.0354 1.0000 0.0139
-7.500 -0.3312 0.06547 0.06352 -0.0355 1.0000 0.0140
-7.250 -0.3453 0.06317 0.06128 -0.0337 1.0000 0.0140
-7.000 -0.3580 0.06048 0.05865 -0.0336 0.9983 0.0140
-6.750 -0.3409 0.05264 0.05075 -0.0459 0.9942 0.0140
-6.500 -0.3247 0.04609 0.04407 -0.0534 0.9893 0.0140
-6.250 -0.3045 0.03960 0.03743 -0.0600 0.9853 0.0140
-6.000 -0.2913 0.02821 0.02574 -0.0686 0.9820 0.0147
-5.750 -0.2709 0.02325 0.02059 -0.0721 0.9770 0.0155
-5.500 -0.2442 0.01987 0.01705 -0.0752 0.9736 0.0165
-5.250 -0.2149 0.01651 0.01347 -0.0781 0.9706 0.0180
-5.000 -0.1858 0.01350 0.01018 -0.0800 0.9668 0.0200
-4.750 -0.1534 0.01335 0.00974 -0.0797 0.9608 0.0239
-4.500 -0.1253 0.01090 0.00695 -0.0806 0.9563 0.0240
-4.250 -0.1166 0.01651 0.01156 -0.0816 0.9605 0.0120
-4.000 -0.0843 0.01369 0.00833 -0.0821 0.9569 0.0114
-3.750 -0.0552 0.01222 0.00666 -0.0820 0.9517 0.0122
-3.500 -0.0262 0.01165 0.00596 -0.0820 0.9457 0.0137
-3.250 0.0013 0.01030 0.00446 -0.0819 0.9405 0.0155
-3.000 0.0273 0.00950 0.00356 -0.0813 0.9328 0.0165
-2.750 0.0552 0.00896 0.00291 -0.0810 0.9269 0.0202
-2.500 0.0816 0.00840 0.00242 -0.0806 0.9191 0.0594
-2.250 0.1082 0.00794 0.00219 -0.0804 0.9124 0.1304
-2.000 0.1309 0.00656 0.00197 -0.0803 0.9039 0.4917
-1.750 0.1558 0.00624 0.00195 -0.0796 0.8952 0.6100
-1.500 0.1822 0.00615 0.00189 -0.0790 0.8874 0.6560
-1.250 0.2083 0.00607 0.00186 -0.0784 0.8786 0.6930
-1.000 0.2348 0.00603 0.00183 -0.0780 0.8708 0.7214
-0.750 0.2610 0.00599 0.00178 -0.0774 0.8625 0.7513
-0.500 0.2855 0.00592 0.00179 -0.0763 0.8520 0.7931
-0.250 0.3104 0.00585 0.00175 -0.0754 0.8405 0.8199
0.000 0.3363 0.00580 0.00169 -0.0747 0.8297 0.8364
0.250 0.3624 0.00574 0.00164 -0.0741 0.8200 0.8534
0.500 0.3879 0.00567 0.00160 -0.0735 0.8093 0.8750
0.750 0.4127 0.00555 0.00156 -0.0725 0.7979 0.9085
1.000 0.4512 0.00545 0.00149 -0.0747 0.7859 0.9833
1.250 0.4803 0.00550 0.00147 -0.0750 0.7736 1.0000
1.500 0.5078 0.00557 0.00149 -0.0749 0.7607 1.0000
1.750 0.5350 0.00564 0.00151 -0.0748 0.7466 1.0000
2.000 0.5620 0.00573 0.00153 -0.0746 0.7306 1.0000
2.250 0.5888 0.00583 0.00157 -0.0743 0.7127 1.0000
2.500 0.6155 0.00594 0.00162 -0.0741 0.6928 1.0000
2.750 0.6419 0.00608 0.00172 -0.0738 0.6721 1.0000
3.000 0.6681 0.00624 0.00181 -0.0734 0.6470 1.0000
3.250 0.6940 0.00642 0.00191 -0.0730 0.6179 1.0000
3.500 0.7189 0.00668 0.00203 -0.0724 0.5762 1.0000
3.750 0.7429 0.00704 0.00220 -0.0717 0.5253 1.0000
4.000 0.7663 0.00749 0.00242 -0.0710 0.4678 1.0000
4.250 0.7887 0.00808 0.00274 -0.0702 0.3975 1.0000
4.500 0.8094 0.00889 0.00310 -0.0692 0.3062 1.0000
4.750 0.8330 0.00943 0.00343 -0.0687 0.2594 1.0000
5.000 0.8556 0.01009 0.00379 -0.0681 0.2004 1.0000
5.250 0.8785 0.01073 0.00418 -0.0675 0.1481 1.0000
5.500 0.8978 0.01185 0.00480 -0.0664 0.0631 1.0000
5.750 0.9168 0.01311 0.00574 -0.0651 0.0099 1.0000
6.000 0.9408 0.01371 0.00648 -0.0643 0.0079 1.0000
6.250 0.9641 0.01437 0.00728 -0.0634 0.0070 1.0000
6.500 0.9861 0.01525 0.00829 -0.0623 0.0062 1.0000
6.750 1.0067 0.01627 0.00945 -0.0611 0.0059 1.0000
7.000 1.0257 0.01752 0.01086 -0.0595 0.0059 1.0000
7.250 1.0437 0.01900 0.01249 -0.0577 0.0060 1.0000
7.500 1.0613 0.02084 0.01452 -0.0559 0.0062 1.0000
7.750 1.0793 0.02330 0.01722 -0.0540 0.0068 1.0000
8.000 1.0969 0.02653 0.02075 -0.0523 0.0075 1.0000
15.000 0.7692 0.18296 0.18122 -0.0884 0.0157 1.0000
15.250 0.7714 0.18733 0.18559 -0.0906 0.0157 1.0000
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Polar data table (+)
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