HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Reynolds number: 200,000 Max Cl/Cd: 68.87 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq17-il-200000.txt Download as CSV file: xf-hq17-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURE
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0502 0.09666 0.09292 -0.1387 0.9441 0.0469
-10.750 -0.0482 0.09258 0.08884 -0.1440 0.9400 0.0473
-10.500 -0.0499 0.08897 0.08524 -0.1467 0.9342 0.0474
-10.250 -0.0311 0.08505 0.08132 -0.1430 0.9332 0.0499
-10.000 -0.0189 0.08229 0.07853 -0.1444 0.9303 0.0515
-9.750 -0.0118 0.07918 0.07540 -0.1465 0.9270 0.0536
-9.500 -0.0167 0.07644 0.07268 -0.1471 0.9208 0.0556
-9.250 -0.0220 0.07221 0.06848 -0.1510 0.9157 0.0578
-9.000 -0.0440 0.06814 0.06443 -0.1540 0.9067 0.0587
-8.750 -0.0689 0.06498 0.06119 -0.1547 0.8989 0.0592
-6.750 -0.1523 0.04994 0.04531 -0.1316 0.8517 0.0757
-6.500 -0.1338 0.04806 0.04354 -0.1314 0.8494 0.0797
-6.250 -0.1257 0.04567 0.04063 -0.1304 0.8469 0.0896
-6.000 -0.1017 0.04316 0.03819 -0.1310 0.8456 0.0940
-5.750 -0.1222 0.04353 0.03854 -0.1234 0.8352 0.0956
-5.500 -0.1025 0.04120 0.03596 -0.1235 0.8335 0.1068
-5.250 -0.1268 0.04180 0.03656 -0.1152 0.8235 0.1077
-5.000 -0.0996 0.03399 0.02738 -0.1123 0.8213 0.0566
-4.750 -0.0666 0.03080 0.02342 -0.1122 0.8202 0.0488
-4.500 -0.0587 0.03055 0.02301 -0.1087 0.8147 0.0481
-4.250 -0.0049 0.02831 0.02047 -0.1129 0.8169 0.0479
-3.500 0.0009 0.02771 0.01976 -0.1003 0.7976 0.0513
-3.250 0.0252 0.02707 0.01909 -0.0998 0.7948 0.0524
-3.000 0.0562 0.02632 0.01831 -0.1003 0.7932 0.0541
-2.750 0.0897 0.02560 0.01754 -0.1013 0.7920 0.0568
-2.500 0.1010 0.02570 0.01761 -0.0988 0.7871 0.0589
-2.250 0.1060 0.02598 0.01787 -0.0954 0.7807 0.0623
-2.000 0.1380 0.02547 0.01735 -0.0963 0.7791 0.0725
-1.750 0.1674 0.02372 0.01668 -0.0974 0.7780 0.3110
-1.500 0.1464 0.02367 0.01812 -0.0894 0.7692 0.6629
-1.250 0.1601 0.02425 0.01891 -0.0847 0.7661 0.7956
-1.000 0.1802 0.02462 0.01923 -0.0812 0.7643 0.8353
-0.750 0.1707 0.02576 0.02036 -0.0749 0.7558 0.8512
-0.500 0.1780 0.02596 0.02054 -0.0699 0.7525 0.8765
-0.250 0.1848 0.02565 0.02021 -0.0641 0.7505 0.9048
0.000 0.1816 0.02565 0.02021 -0.0574 0.7463 0.9306
0.250 0.2265 0.02481 0.01928 -0.0585 0.7481 0.9551
0.500 0.2334 0.02623 0.02068 -0.0573 0.7379 0.9670
0.750 0.3138 0.02663 0.02096 -0.0677 0.7380 0.9759
1.000 0.3590 0.02662 0.02086 -0.0713 0.7369 0.9789
1.250 0.3981 0.02650 0.02066 -0.0738 0.7359 0.9813
1.500 0.4417 0.02634 0.02044 -0.0770 0.7352 0.9827
1.750 0.4858 0.02614 0.02018 -0.0803 0.7347 0.9840
2.000 0.4876 0.02801 0.02207 -0.0790 0.7237 0.9916
2.250 0.5270 0.02780 0.02183 -0.0813 0.7226 0.9939
2.500 0.5682 0.02749 0.02149 -0.0839 0.7218 0.9961
2.750 0.6114 0.02704 0.02103 -0.0867 0.7212 0.9979
3.000 0.6541 0.02652 0.02049 -0.0894 0.7201 0.9995
3.250 0.7028 0.02562 0.01959 -0.0927 0.7206 0.9998
3.500 0.6399 0.02722 0.02119 -0.0785 0.7054 1.0000
3.750 0.6870 0.02622 0.02018 -0.0812 0.7062 1.0000
5.000 0.7562 0.02814 0.02218 -0.0731 0.6751 1.0000
5.250 0.8051 0.02678 0.02087 -0.0757 0.6762 1.0000
5.500 0.8515 0.02555 0.01969 -0.0781 0.6767 1.0000
5.750 0.8998 0.02438 0.01858 -0.0810 0.6772 1.0000
6.000 0.9570 0.02272 0.01699 -0.0850 0.6775 1.0000
6.250 0.9616 0.02329 0.01761 -0.0818 0.6671 1.0000
6.500 1.0270 0.02110 0.01549 -0.0868 0.6666 1.0000
6.750 1.0875 0.01970 0.01419 -0.0918 0.6652 1.0000
7.000 1.0828 0.02047 0.01503 -0.0870 0.6544 1.0000
7.250 1.1400 0.01917 0.01382 -0.0915 0.6517 1.0000
7.500 1.1412 0.01979 0.01451 -0.0876 0.6413 1.0000
7.750 1.1945 0.01842 0.01322 -0.0912 0.6346 1.0000
8.000 1.2101 0.01825 0.01310 -0.0892 0.6221 1.0000
8.250 1.2277 0.01806 0.01296 -0.0875 0.6080 1.0000
8.500 1.2445 0.01807 0.01299 -0.0857 0.5922 1.0000
8.750 1.2499 0.01862 0.01358 -0.0826 0.5738 1.0000
9.000 1.2597 0.01901 0.01397 -0.0800 0.5505 1.0000
9.250 1.2624 0.01976 0.01467 -0.0766 0.5206 1.0000
9.500 1.2675 0.02056 0.01531 -0.0736 0.4840 1.0000
9.750 1.2721 0.02154 0.01609 -0.0707 0.4486 1.0000
10.250 1.2657 0.02463 0.01880 -0.0637 0.3719 1.0000
10.500 1.2561 0.02673 0.02065 -0.0598 0.3333 1.0000
10.750 1.2535 0.02861 0.02240 -0.0570 0.2982 1.0000
11.000 1.2413 0.03123 0.02471 -0.0535 0.2546 1.0000
11.250 1.2396 0.03331 0.02668 -0.0513 0.2259 1.0000
11.500 1.2369 0.03558 0.02879 -0.0491 0.1910 1.0000
11.750 1.2337 0.03799 0.03100 -0.0471 0.1572 1.0000
12.000 1.2311 0.04046 0.03330 -0.0453 0.1285 1.0000
12.250 1.2310 0.04281 0.03550 -0.0438 0.1003 1.0000
12.500 1.2305 0.04526 0.03781 -0.0424 0.0785 1.0000
12.750 1.2258 0.04822 0.04061 -0.0407 0.0510 1.0000
13.000 1.2183 0.05157 0.04373 -0.0391 0.0289 1.0000
13.250 1.2176 0.05439 0.04659 -0.0379 0.0239 1.0000
13.500 1.2132 0.05768 0.04996 -0.0367 0.0213 1.0000
13.750 1.2141 0.06050 0.05292 -0.0359 0.0201 1.0000
14.000 1.2151 0.06335 0.05589 -0.0353 0.0188 1.0000
14.250 1.2166 0.06619 0.05886 -0.0348 0.0178 1.0000
14.500 1.2173 0.06915 0.06191 -0.0344 0.0169 1.0000
14.750 1.2182 0.07215 0.06500 -0.0340 0.0165 1.0000
15.000 1.2136 0.07572 0.06861 -0.0333 0.0151 1.0000
15.250 1.2198 0.07814 0.07115 -0.0330 0.0149 1.0000
15.500 1.2263 0.08057 0.07371 -0.0327 0.0145 1.0000
15.750 1.2336 0.08290 0.07617 -0.0324 0.0142 1.0000
16.000 1.2412 0.08524 0.07865 -0.0321 0.0138 1.0000
16.250 1.2491 0.08757 0.08113 -0.0318 0.0137 1.0000
16.500 1.2560 0.09012 0.08385 -0.0315 0.0135 1.0000
16.750 1.2609 0.09305 0.08696 -0.0315 0.0133 1.0000
17.000 1.2638 0.09629 0.09041 -0.0316 0.0133 1.0000
17.250 1.2637 0.10003 0.09440 -0.0320 0.0132 1.0000
17.500 1.2604 0.10424 0.09885 -0.0327 0.0132 1.0000
17.750 1.2537 0.10906 0.10392 -0.0338 0.0133 1.0000
18.000 1.2448 0.11430 0.10940 -0.0354 0.0134 1.0000
18.250 1.2336 0.12001 0.11536 -0.0374 0.0135 1.0000
18.500 1.2202 0.12626 0.12186 -0.0401 0.0136 1.0000
18.750 1.2053 0.13297 0.12880 -0.0433 0.0137 1.0000
19.000 1.1897 0.14004 0.13607 -0.0470 0.0139 1.0000
19.250 1.1725 0.14777 0.14401 -0.0514 0.0141 1.0000
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