HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 200,000 Max Cl/Cd: 73.58 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2590sm-il-200000-n5.txt Download as CSV file: xf-hq2590sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/9.0 smoothed by Eppler
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4296 0.09260 0.08891 -0.0339 1.0000 0.0170
-9.250 -0.4313 0.08843 0.08480 -0.0355 1.0000 0.0170
-9.000 -0.4349 0.08409 0.08050 -0.0373 1.0000 0.0169
-8.750 -0.4337 0.08141 0.07787 -0.0380 1.0000 0.0176
-8.500 -0.4376 0.07791 0.07443 -0.0392 1.0000 0.0182
-8.250 -0.4482 0.07394 0.07054 -0.0403 1.0000 0.0181
-8.000 -0.4626 0.06993 0.06664 -0.0418 1.0000 0.0182
-7.750 -0.4784 0.06433 0.06106 -0.0459 1.0000 0.0178
-7.500 -0.4704 0.05710 0.05367 -0.0537 0.9943 0.0180
-7.250 -0.4526 0.04822 0.04443 -0.0626 0.9854 0.0177
-7.000 -0.4319 0.04089 0.03664 -0.0680 0.9779 0.0178
-6.750 -0.4068 0.03466 0.02987 -0.0720 0.9720 0.0183
-6.500 -0.3793 0.02981 0.02442 -0.0746 0.9670 0.0195
-6.250 -0.3508 0.02616 0.02004 -0.0761 0.9611 0.0210
-6.000 -0.3201 0.02310 0.01647 -0.0778 0.9573 0.0217
-5.750 -0.2905 0.02128 0.01442 -0.0789 0.9526 0.0225
-5.500 -0.2612 0.02018 0.01316 -0.0797 0.9471 0.0237
-5.250 -0.2292 0.01920 0.01200 -0.0808 0.9433 0.0255
-5.000 -0.1981 0.01797 0.01053 -0.0816 0.9392 0.0267
-4.750 -0.1697 0.01691 0.00931 -0.0817 0.9332 0.0275
-4.500 -0.1386 0.01603 0.00829 -0.0824 0.9289 0.0284
-4.250 -0.1095 0.01499 0.00721 -0.0829 0.9240 0.0303
-4.000 -0.0814 0.01443 0.00663 -0.0831 0.9179 0.0327
-3.750 -0.0512 0.01383 0.00598 -0.0837 0.9136 0.0347
-3.500 -0.0227 0.01332 0.00540 -0.0839 0.9084 0.0369
-3.250 0.0055 0.01285 0.00485 -0.0841 0.9027 0.0398
-3.000 0.0354 0.01241 0.00439 -0.0846 0.8984 0.0463
-2.750 0.0631 0.01206 0.00406 -0.0846 0.8925 0.0579
-2.500 0.0913 0.01170 0.00376 -0.0848 0.8874 0.0817
-2.250 0.1200 0.01113 0.00348 -0.0853 0.8835 0.1662
-2.000 0.1435 0.00993 0.00339 -0.0854 0.8770 0.4698
-1.750 0.1693 0.00960 0.00343 -0.0847 0.8697 0.5923
-1.500 0.1945 0.00950 0.00344 -0.0837 0.8600 0.6527
-1.250 0.2209 0.00943 0.00339 -0.0829 0.8509 0.6913
-1.000 0.2458 0.00937 0.00340 -0.0818 0.8419 0.7289
-0.750 0.2716 0.00933 0.00336 -0.0810 0.8333 0.7528
-0.500 0.2987 0.00928 0.00326 -0.0805 0.8249 0.7642
-0.250 0.3249 0.00925 0.00322 -0.0800 0.8150 0.7757
0.000 0.3519 0.00923 0.00317 -0.0795 0.8073 0.7875
0.250 0.3783 0.00921 0.00316 -0.0791 0.7993 0.8001
0.500 0.4051 0.00920 0.00314 -0.0786 0.7918 0.8136
0.750 0.4313 0.00919 0.00314 -0.0780 0.7833 0.8278
1.000 0.4571 0.00917 0.00315 -0.0774 0.7746 0.8430
1.250 0.4832 0.00915 0.00313 -0.0767 0.7657 0.8599
1.500 0.5089 0.00912 0.00314 -0.0760 0.7551 0.8791
1.750 0.5351 0.00909 0.00315 -0.0754 0.7438 0.9019
2.000 0.5649 0.00903 0.00313 -0.0756 0.7313 0.9328
2.250 0.5995 0.00902 0.00312 -0.0769 0.7158 1.0000
2.500 0.6267 0.00910 0.00319 -0.0767 0.6982 1.0000
2.750 0.6535 0.00920 0.00324 -0.0764 0.6757 1.0000
3.000 0.6795 0.00932 0.00329 -0.0759 0.6425 1.0000
3.250 0.7034 0.00956 0.00330 -0.0749 0.5808 1.0000
3.500 0.7224 0.01021 0.00340 -0.0731 0.4936 1.0000
3.750 0.7428 0.01088 0.00370 -0.0719 0.4324 1.0000
4.000 0.7660 0.01135 0.00400 -0.0712 0.3952 1.0000
4.250 0.7905 0.01174 0.00431 -0.0707 0.3711 1.0000
4.500 0.8149 0.01212 0.00462 -0.0702 0.3475 1.0000
4.750 0.8393 0.01250 0.00494 -0.0697 0.3233 1.0000
5.000 0.8635 0.01290 0.00527 -0.0692 0.3004 1.0000
5.250 0.8879 0.01328 0.00564 -0.0687 0.2762 1.0000
5.500 0.9108 0.01380 0.00601 -0.0680 0.2385 1.0000
5.750 0.9314 0.01455 0.00647 -0.0671 0.1811 1.0000
6.000 0.9515 0.01543 0.00704 -0.0662 0.1323 1.0000
6.250 0.9730 0.01616 0.00763 -0.0654 0.1053 1.0000
6.500 0.9953 0.01678 0.00823 -0.0647 0.0889 1.0000
6.750 1.0175 0.01742 0.00885 -0.0639 0.0762 1.0000
7.000 1.0391 0.01811 0.00952 -0.0631 0.0653 1.0000
7.250 1.0608 0.01876 0.01021 -0.0623 0.0557 1.0000
7.500 1.0820 0.01946 0.01097 -0.0614 0.0477 1.0000
7.750 1.1015 0.02032 0.01182 -0.0603 0.0417 1.0000
8.000 1.1218 0.02107 0.01269 -0.0593 0.0380 1.0000
8.250 1.1410 0.02190 0.01359 -0.0581 0.0348 1.0000
8.500 1.1576 0.02297 0.01468 -0.0567 0.0321 1.0000
8.750 1.1763 0.02382 0.01568 -0.0554 0.0301 1.0000
9.000 1.1935 0.02477 0.01674 -0.0540 0.0283 1.0000
9.250 1.2103 0.02571 0.01777 -0.0527 0.0266 1.0000
9.500 1.2237 0.02693 0.01904 -0.0510 0.0248 1.0000
9.750 1.2366 0.02820 0.02043 -0.0491 0.0236 1.0000
10.000 1.2496 0.02937 0.02176 -0.0472 0.0225 1.0000
10.250 1.2617 0.03053 0.02309 -0.0453 0.0212 1.0000
10.500 1.2726 0.03170 0.02437 -0.0434 0.0200 1.0000
10.750 1.2813 0.03300 0.02576 -0.0414 0.0190 1.0000
11.000 1.2860 0.03501 0.02785 -0.0392 0.0181 1.0000
11.250 1.2938 0.03673 0.02977 -0.0373 0.0175 1.0000
11.500 1.3002 0.03857 0.03185 -0.0355 0.0168 1.0000
11.750 1.3049 0.04049 0.03398 -0.0337 0.0160 1.0000
12.000 1.3082 0.04248 0.03615 -0.0321 0.0153 1.0000
12.250 1.3103 0.04448 0.03829 -0.0308 0.0146 1.0000
12.500 1.3111 0.04673 0.04066 -0.0297 0.0141 1.0000
12.750 1.3096 0.04935 0.04341 -0.0288 0.0137 1.0000
13.000 1.3041 0.05271 0.04695 -0.0281 0.0133 1.0000
13.250 1.2973 0.05640 0.05088 -0.0278 0.0131 1.0000
13.500 1.2889 0.06046 0.05521 -0.0280 0.0129 1.0000
13.750 1.2780 0.06508 0.06009 -0.0288 0.0127 1.0000
14.000 1.2645 0.07041 0.06567 -0.0304 0.0125 1.0000
14.250 1.2495 0.07638 0.07188 -0.0329 0.0124 1.0000
14.500 1.2325 0.08323 0.07896 -0.0364 0.0123 1.0000
14.750 1.2143 0.09094 0.08690 -0.0408 0.0123 1.0000
15.000 1.1942 0.09968 0.09585 -0.0462 0.0123 1.0000
15.250 1.1725 0.10937 0.10574 -0.0524 0.0124 1.0000
15.500 1.1495 0.11989 0.11640 -0.0591 0.0126 1.0000
15.750 1.1241 0.13169 0.12835 -0.0667 0.0127 1.0000
16.000 1.0960 0.14509 0.14188 -0.0751 0.0130 1.0000
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Polar data table (+)
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