HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Reynolds number: 100,000 Max Cl/Cd: 58.39 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2590sm-il-100000.txt Download as CSV file: xf-hq2590sm-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4212 0.09199 0.08708 -0.0333 1.0000 0.1003
-8.250 -0.4429 0.08964 0.08489 -0.0369 1.0000 0.1022
-8.000 -0.4674 0.08617 0.08152 -0.0439 1.0000 0.1028
-7.750 -0.4394 0.08260 0.07798 -0.0343 1.0000 0.1069
-7.500 -0.4394 0.07997 0.07542 -0.0334 1.0000 0.1107
-7.250 -0.4509 0.07654 0.07208 -0.0366 1.0000 0.1145
-7.000 -0.4841 0.07355 0.06890 -0.0445 1.0000 0.1175
-6.750 -0.4728 0.06925 0.06484 -0.0398 1.0000 0.1202
-6.500 -0.4686 0.06722 0.06287 -0.0364 1.0000 0.1247
-6.250 -0.4841 0.06371 0.05901 -0.0420 1.0000 0.1331
-6.000 -0.4739 0.06120 0.05679 -0.0363 1.0000 0.1382
-5.750 -0.4735 0.05774 0.05317 -0.0382 1.0000 0.1497
-5.500 -0.4676 0.05499 0.05027 -0.0386 1.0000 0.1637
-5.250 -0.4588 0.05231 0.04753 -0.0383 1.0000 0.1785
-5.000 -0.4485 0.04961 0.04482 -0.0374 1.0000 0.1938
-4.750 -0.4373 0.04716 0.04241 -0.0360 1.0000 0.2105
-4.250 -0.3474 0.03361 0.02602 -0.0453 1.0000 0.0890
-4.000 -0.3231 0.03029 0.02253 -0.0455 1.0000 0.0866
-3.750 -0.2961 0.02757 0.01947 -0.0456 1.0000 0.0822
-3.500 -0.2683 0.02544 0.01683 -0.0453 1.0000 0.0790
-3.250 -0.2426 0.02393 0.01499 -0.0448 1.0000 0.0789
-3.000 -0.2187 0.02295 0.01388 -0.0443 1.0000 0.0834
-2.750 -0.1940 0.02197 0.01269 -0.0436 1.0000 0.0866
-2.500 -0.1697 0.02102 0.01161 -0.0428 1.0000 0.0894
-2.250 -0.1461 0.02001 0.01074 -0.0424 1.0000 0.0961
-2.000 -0.1226 0.01932 0.01012 -0.0418 1.0000 0.1078
-1.750 -0.0983 0.01865 0.00954 -0.0415 1.0000 0.1251
-1.500 -0.0718 0.01601 0.00927 -0.0417 1.0000 0.6213
-1.250 -0.0667 0.01598 0.00970 -0.0355 1.0000 0.7904
-1.000 -0.0613 0.01588 0.00978 -0.0299 1.0000 0.8794
-0.750 -0.0098 0.01590 0.00970 -0.0350 0.9898 1.0000
-0.500 0.0434 0.01644 0.00994 -0.0408 0.9794 1.0000
-0.250 0.0976 0.01697 0.01023 -0.0467 0.9698 1.0000
0.000 0.1371 0.01723 0.01033 -0.0497 0.9599 1.0000
0.250 0.1793 0.01758 0.01052 -0.0530 0.9512 1.0000
0.500 0.2242 0.01790 0.01073 -0.0567 0.9428 1.0000
0.750 0.2600 0.01814 0.01089 -0.0587 0.9329 1.0000
1.000 0.3051 0.01838 0.01107 -0.0622 0.9246 1.0000
1.250 0.3450 0.01854 0.01120 -0.0647 0.9145 1.0000
1.500 0.3825 0.01866 0.01132 -0.0666 0.9035 1.0000
1.750 0.4266 0.01868 0.01135 -0.0695 0.8936 1.0000
2.000 0.4758 0.01851 0.01123 -0.0730 0.8839 1.0000
2.250 0.5157 0.01839 0.01117 -0.0749 0.8716 1.0000
2.500 0.5568 0.01813 0.01099 -0.0766 0.8592 1.0000
2.750 0.5976 0.01777 0.01072 -0.0780 0.8464 1.0000
3.000 0.6365 0.01732 0.01039 -0.0788 0.8322 1.0000
3.250 0.6729 0.01683 0.00999 -0.0790 0.8159 1.0000
3.500 0.7082 0.01625 0.00950 -0.0788 0.7977 1.0000
3.750 0.7387 0.01575 0.00911 -0.0777 0.7746 1.0000
4.000 0.7678 0.01521 0.00861 -0.0762 0.7455 1.0000
4.250 0.7950 0.01472 0.00810 -0.0743 0.7078 1.0000
4.500 0.8182 0.01450 0.00786 -0.0722 0.6573 1.0000
4.750 0.8416 0.01449 0.00767 -0.0703 0.5993 1.0000
5.000 0.8647 0.01481 0.00768 -0.0687 0.5439 1.0000
5.250 0.8870 0.01543 0.00802 -0.0673 0.4973 1.0000
5.500 0.9087 0.01614 0.00855 -0.0660 0.4566 1.0000
5.750 0.9296 0.01688 0.00913 -0.0647 0.4170 1.0000
6.000 0.9494 0.01759 0.00975 -0.0632 0.3748 1.0000
6.250 0.9664 0.01836 0.01036 -0.0614 0.3209 1.0000
6.500 0.9800 0.01938 0.01104 -0.0592 0.2468 1.0000
6.750 0.9930 0.02088 0.01203 -0.0571 0.1828 1.0000
7.000 1.0083 0.02248 0.01332 -0.0554 0.1447 1.0000
7.250 1.0249 0.02419 0.01487 -0.0537 0.1194 1.0000
7.500 1.0434 0.02620 0.01664 -0.0525 0.1021 1.0000
7.750 1.0651 0.02805 0.01842 -0.0516 0.0890 1.0000
8.000 1.0900 0.03001 0.02060 -0.0509 0.0812 1.0000
8.250 1.1169 0.03273 0.02320 -0.0509 0.0749 1.0000
8.500 1.1380 0.03445 0.02532 -0.0497 0.0696 1.0000
8.750 1.1608 0.03687 0.02794 -0.0489 0.0662 1.0000
9.000 1.1835 0.04073 0.03188 -0.0488 0.0632 1.0000
9.250 1.1952 0.04321 0.03497 -0.0465 0.0610 1.0000
9.500 1.2049 0.04624 0.03855 -0.0442 0.0592 1.0000
9.750 1.2110 0.05006 0.04287 -0.0419 0.0586 1.0000
10.000 1.2117 0.05421 0.04750 -0.0393 0.0585 1.0000
10.250 1.2068 0.05844 0.05218 -0.0366 0.0586 1.0000
10.500 1.1966 0.06261 0.05673 -0.0338 0.0586 1.0000
10.750 1.1806 0.06665 0.06108 -0.0308 0.0588 1.0000
11.000 1.1597 0.07063 0.06530 -0.0281 0.0592 1.0000
11.250 1.1369 0.07499 0.06987 -0.0265 0.0596 1.0000
11.500 1.1141 0.08003 0.07508 -0.0264 0.0604 1.0000
11.750 1.0918 0.08570 0.08090 -0.0276 0.0611 1.0000
12.000 1.0716 0.09210 0.08739 -0.0297 0.0618 1.0000
12.250 1.0572 0.09906 0.09441 -0.0322 0.0626 1.0000
12.500 0.8142 0.13003 0.12585 -0.0508 0.0877 1.0000
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Polar data table (+)
Polar graphs
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