HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 200,000 Max Cl/Cd: 78.36 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq309-il-200000-n5.txt Download as CSV file: xf-hq309-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3728 0.08962 0.08624 -0.0389 1.0000 0.0205
-8.250 -0.3705 0.08730 0.08396 -0.0376 1.0000 0.0214
-8.000 -0.3747 0.08453 0.08126 -0.0374 1.0000 0.0215
-7.500 -0.2959 0.06229 0.05929 -0.0438 0.9894 0.0169
-7.000 -0.3609 0.06798 0.06484 -0.0519 0.9858 0.0172
-6.750 -0.3409 0.06057 0.05734 -0.0624 0.9775 0.0153
-6.250 -0.2891 0.04394 0.04008 -0.0793 0.9635 0.0116
-6.000 -0.2609 0.03798 0.03374 -0.0844 0.9596 0.0113
-5.750 -0.2385 0.03308 0.02844 -0.0864 0.9518 0.0111
-5.500 -0.2090 0.02819 0.02300 -0.0889 0.9474 0.0110
-5.250 -0.1821 0.02436 0.01860 -0.0897 0.9415 0.0111
-5.000 -0.1530 0.02139 0.01508 -0.0904 0.9365 0.0115
-4.750 -0.1213 0.01913 0.01236 -0.0913 0.9330 0.0124
-4.500 -0.0949 0.01800 0.01109 -0.0915 0.9268 0.0144
-4.250 -0.0650 0.01660 0.00946 -0.0918 0.9221 0.0153
-4.000 -0.0344 0.01534 0.00799 -0.0923 0.9183 0.0161
-3.750 -0.0082 0.01442 0.00694 -0.0919 0.9115 0.0172
-3.500 0.0216 0.01362 0.00601 -0.0922 0.9068 0.0190
-3.250 0.0492 0.01296 0.00529 -0.0922 0.9008 0.0238
-3.000 0.0777 0.01247 0.00478 -0.0923 0.8949 0.0375
-2.750 0.1070 0.01212 0.00434 -0.0926 0.8898 0.0555
-2.500 0.1339 0.01177 0.00407 -0.0925 0.8828 0.0828
-2.250 0.1628 0.01127 0.00373 -0.0929 0.8778 0.1362
-2.000 0.1878 0.01045 0.00350 -0.0929 0.8702 0.3161
-1.750 0.2135 0.00979 0.00346 -0.0927 0.8645 0.5226
-1.500 0.2386 0.00963 0.00346 -0.0919 0.8567 0.6046
-1.250 0.2647 0.00950 0.00347 -0.0911 0.8503 0.6753
-1.000 0.2879 0.00943 0.00353 -0.0897 0.8412 0.7341
-0.750 0.3130 0.00936 0.00349 -0.0886 0.8332 0.7686
-0.500 0.3397 0.00932 0.00338 -0.0882 0.8248 0.7819
-0.250 0.3665 0.00929 0.00331 -0.0878 0.8163 0.7941
0.000 0.3939 0.00924 0.00321 -0.0875 0.8089 0.8067
0.250 0.4199 0.00920 0.00317 -0.0870 0.7996 0.8205
0.500 0.4460 0.00915 0.00310 -0.0864 0.7892 0.8358
0.750 0.4719 0.00907 0.00301 -0.0857 0.7766 0.8536
1.000 0.4982 0.00900 0.00293 -0.0850 0.7638 0.8763
1.250 0.5277 0.00891 0.00288 -0.0851 0.7527 0.9115
1.500 0.5639 0.00887 0.00282 -0.0868 0.7406 1.0000
1.750 0.5913 0.00895 0.00283 -0.0867 0.7267 1.0000
2.000 0.6183 0.00904 0.00285 -0.0865 0.7104 1.0000
2.250 0.6451 0.00914 0.00291 -0.0862 0.6930 1.0000
2.500 0.6718 0.00926 0.00296 -0.0860 0.6754 1.0000
2.750 0.6983 0.00940 0.00303 -0.0856 0.6571 1.0000
3.000 0.7245 0.00955 0.00313 -0.0853 0.6361 1.0000
3.250 0.7503 0.00973 0.00328 -0.0848 0.6127 1.0000
3.500 0.7755 0.00994 0.00341 -0.0843 0.5847 1.0000
3.750 0.8001 0.01021 0.00356 -0.0836 0.5526 1.0000
4.000 0.8238 0.01054 0.00375 -0.0829 0.5158 1.0000
4.250 0.8469 0.01093 0.00399 -0.0820 0.4773 1.0000
4.500 0.8694 0.01138 0.00431 -0.0811 0.4381 1.0000
4.750 0.8919 0.01185 0.00465 -0.0803 0.4006 1.0000
5.000 0.9142 0.01235 0.00502 -0.0794 0.3644 1.0000
5.250 0.9362 0.01287 0.00542 -0.0786 0.3287 1.0000
5.500 0.9581 0.01343 0.00585 -0.0777 0.2953 1.0000
5.750 0.9797 0.01401 0.00635 -0.0769 0.2634 1.0000
6.000 1.0012 0.01460 0.00684 -0.0760 0.2328 1.0000
6.250 1.0220 0.01526 0.00735 -0.0751 0.1962 1.0000
6.500 1.0411 0.01609 0.00791 -0.0741 0.1522 1.0000
6.750 1.0601 0.01696 0.00852 -0.0730 0.1100 1.0000
7.000 1.0802 0.01771 0.00916 -0.0721 0.0837 1.0000
7.250 1.1004 0.01845 0.00984 -0.0711 0.0633 1.0000
7.500 1.1204 0.01921 0.01065 -0.0700 0.0489 1.0000
7.750 1.1383 0.02018 0.01155 -0.0687 0.0310 1.0000
8.000 1.1546 0.02129 0.01257 -0.0673 0.0148 1.0000
8.250 1.1717 0.02230 0.01360 -0.0658 0.0087 1.0000
8.500 1.1888 0.02329 0.01470 -0.0643 0.0069 1.0000
8.750 1.2048 0.02433 0.01587 -0.0627 0.0062 1.0000
9.000 1.2186 0.02554 0.01724 -0.0608 0.0057 1.0000
9.250 1.2312 0.02669 0.01858 -0.0588 0.0055 1.0000
9.500 1.2411 0.02794 0.02001 -0.0563 0.0054 1.0000
9.750 1.2489 0.02932 0.02157 -0.0538 0.0052 1.0000
10.000 1.2552 0.03083 0.02333 -0.0512 0.0051 1.0000
10.250 1.2600 0.03251 0.02518 -0.0487 0.0050 1.0000
10.500 1.2642 0.03429 0.02715 -0.0463 0.0050 1.0000
10.750 1.2669 0.03630 0.02934 -0.0441 0.0049 1.0000
11.000 1.2688 0.03849 0.03172 -0.0420 0.0049 1.0000
11.250 1.2698 0.04089 0.03432 -0.0401 0.0048 1.0000
11.500 1.2698 0.04347 0.03711 -0.0385 0.0048 1.0000
11.750 1.2688 0.04627 0.04012 -0.0371 0.0047 1.0000
12.000 1.2655 0.04947 0.04355 -0.0359 0.0047 1.0000
12.250 1.2612 0.05285 0.04716 -0.0351 0.0047 1.0000
12.500 1.2544 0.05672 0.05127 -0.0347 0.0047 1.0000
12.750 1.2461 0.06093 0.05572 -0.0348 0.0047 1.0000
13.000 1.2357 0.06565 0.06068 -0.0355 0.0047 1.0000
13.250 1.2243 0.07074 0.06600 -0.0369 0.0046 1.0000
13.500 1.2111 0.07648 0.07197 -0.0390 0.0047 1.0000
13.750 1.1963 0.08292 0.07863 -0.0419 0.0047 1.0000
14.000 1.1809 0.08996 0.08588 -0.0456 0.0047 1.0000
14.250 1.1649 0.09774 0.09386 -0.0500 0.0047 1.0000
14.500 1.1480 0.10626 0.10257 -0.0551 0.0047 1.0000
14.750 1.1306 0.11550 0.11199 -0.0608 0.0048 1.0000
15.000 1.1134 0.12519 0.12184 -0.0669 0.0049 1.0000
15.250 1.0959 0.13551 0.13229 -0.0732 0.0049 1.0000
15.500 1.0781 0.14640 0.14330 -0.0797 0.0050 1.0000
15.750 1.0595 0.15825 0.15523 -0.0866 0.0051 1.0000
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Polar data table (+)
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