HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il) Reynolds number: 50,000 Max Cl/Cd: 37.41 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2511-il-50000-n5.txt Download as CSV file: xf-hq2511-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4118 0.09867 0.09158 -0.0411 1.0000 0.0441
-9.500 -0.4122 0.09473 0.08772 -0.0424 1.0000 0.0435
-9.250 -0.4154 0.09046 0.08354 -0.0441 1.0000 0.0431
-9.000 -0.4201 0.08607 0.07925 -0.0459 1.0000 0.0426
-8.750 -0.4273 0.08155 0.07483 -0.0480 1.0000 0.0421
-8.500 -0.4395 0.07680 0.07019 -0.0502 1.0000 0.0415
-8.250 -0.4580 0.07279 0.06628 -0.0512 1.0000 0.0410
-8.000 -0.4741 0.06894 0.06247 -0.0517 1.0000 0.0405
-7.750 -0.4901 0.06524 0.05874 -0.0513 1.0000 0.0402
-7.500 -0.5033 0.06172 0.05513 -0.0504 1.0000 0.0399
-7.250 -0.5127 0.05826 0.05153 -0.0493 1.0000 0.0396
-7.000 -0.5179 0.05478 0.04783 -0.0481 1.0000 0.0396
-6.750 -0.5186 0.05134 0.04410 -0.0470 1.0000 0.0397
-6.500 -0.5150 0.04793 0.04035 -0.0460 1.0000 0.0402
-6.250 -0.5073 0.04463 0.03666 -0.0451 1.0000 0.0409
-6.000 -0.4959 0.04150 0.03307 -0.0442 1.0000 0.0418
-5.750 -0.4811 0.03846 0.02947 -0.0434 1.0000 0.0441
-5.500 -0.4641 0.03590 0.02645 -0.0425 1.0000 0.0472
-5.250 -0.4470 0.03440 0.02478 -0.0418 1.0000 0.0516
-5.000 -0.4183 0.03242 0.02238 -0.0427 0.9964 0.0606
-4.750 -0.3870 0.03096 0.02068 -0.0443 0.9913 0.0748
-4.500 -0.3548 0.02932 0.01870 -0.0452 0.9866 0.0861
-4.250 -0.3231 0.02806 0.01725 -0.0460 0.9821 0.0982
-4.000 -0.2939 0.02698 0.01613 -0.0465 0.9767 0.1096
-3.750 -0.2622 0.02606 0.01512 -0.0475 0.9718 0.1222
-3.500 -0.2322 0.02528 0.01429 -0.0485 0.9662 0.1395
-3.250 -0.2011 0.02447 0.01351 -0.0498 0.9605 0.1641
-3.000 -0.1676 0.02326 0.01274 -0.0520 0.9561 0.2407
-2.750 -0.1481 0.02197 0.01288 -0.0509 0.9496 0.5012
-2.500 -0.1233 0.02214 0.01327 -0.0492 0.9436 0.6387
-2.250 -0.1027 0.02235 0.01340 -0.0471 0.9362 0.7056
-2.000 -0.0832 0.02256 0.01367 -0.0440 0.9296 0.7697
-1.750 -0.0705 0.02263 0.01380 -0.0394 0.9219 0.8287
-1.500 -0.0465 0.02262 0.01375 -0.0372 0.9158 0.8828
-1.250 -0.0041 0.02265 0.01358 -0.0395 0.9104 0.9179
-1.000 0.0431 0.02267 0.01338 -0.0437 0.9034 0.9398
-0.750 0.1001 0.02269 0.01315 -0.0498 0.8981 0.9583
-0.500 0.1472 0.02269 0.01297 -0.0544 0.8895 0.9834
-0.250 0.1899 0.02271 0.01282 -0.0581 0.8828 1.0000
0.000 0.2123 0.02279 0.01276 -0.0582 0.8728 1.0000
0.250 0.2380 0.02294 0.01278 -0.0587 0.8639 1.0000
0.500 0.2717 0.02307 0.01279 -0.0604 0.8567 1.0000
0.750 0.2965 0.02331 0.01293 -0.0606 0.8470 1.0000
1.000 0.3333 0.02344 0.01297 -0.0625 0.8407 1.0000
1.250 0.3568 0.02373 0.01320 -0.0623 0.8301 1.0000
1.500 0.3881 0.02393 0.01336 -0.0633 0.8220 1.0000
1.750 0.4185 0.02413 0.01353 -0.0640 0.8129 1.0000
2.000 0.4454 0.02434 0.01372 -0.0640 0.8015 1.0000
2.250 0.4765 0.02435 0.01373 -0.0643 0.7894 1.0000
2.500 0.5089 0.02425 0.01366 -0.0646 0.7767 1.0000
2.750 0.5415 0.02412 0.01353 -0.0648 0.7640 1.0000
3.000 0.5737 0.02401 0.01346 -0.0650 0.7522 1.0000
3.250 0.6006 0.02407 0.01360 -0.0646 0.7387 1.0000
3.500 0.6283 0.02406 0.01366 -0.0641 0.7246 1.0000
3.750 0.6563 0.02402 0.01368 -0.0636 0.7100 1.0000
4.000 0.6847 0.02393 0.01367 -0.0631 0.6947 1.0000
4.250 0.7134 0.02380 0.01366 -0.0625 0.6788 1.0000
4.500 0.7365 0.02389 0.01386 -0.0613 0.6593 1.0000
4.750 0.7624 0.02382 0.01387 -0.0603 0.6389 1.0000
5.000 0.7879 0.02372 0.01388 -0.0591 0.6160 1.0000
5.250 0.8136 0.02358 0.01380 -0.0578 0.5900 1.0000
5.500 0.8367 0.02360 0.01387 -0.0564 0.5599 1.0000
5.750 0.8595 0.02370 0.01400 -0.0549 0.5268 1.0000
6.000 0.8832 0.02385 0.01408 -0.0535 0.4927 1.0000
6.250 0.9057 0.02421 0.01432 -0.0521 0.4583 1.0000
6.500 0.9257 0.02481 0.01484 -0.0506 0.4246 1.0000
6.750 0.9443 0.02555 0.01556 -0.0491 0.3921 1.0000
7.000 0.9619 0.02637 0.01633 -0.0476 0.3615 1.0000
7.250 0.9794 0.02724 0.01716 -0.0461 0.3346 1.0000
7.500 0.9967 0.02821 0.01805 -0.0447 0.3110 1.0000
7.750 1.0150 0.02926 0.01913 -0.0435 0.2896 1.0000
8.000 1.0345 0.03036 0.02023 -0.0424 0.2709 1.0000
8.250 1.0543 0.03148 0.02141 -0.0415 0.2535 1.0000
8.500 1.0748 0.03263 0.02270 -0.0406 0.2378 1.0000
8.750 1.0953 0.03382 0.02403 -0.0398 0.2238 1.0000
9.250 1.1118 0.03604 0.02651 -0.0356 0.1885 1.0000
9.500 1.1098 0.03721 0.02765 -0.0326 0.1703 1.0000
9.750 1.1087 0.03865 0.02915 -0.0301 0.1508 1.0000
10.000 1.1104 0.04031 0.03089 -0.0282 0.1328 1.0000
10.250 1.1116 0.04227 0.03289 -0.0266 0.1162 1.0000
10.500 1.1120 0.04458 0.03527 -0.0251 0.0981 1.0000
10.750 1.1112 0.04722 0.03796 -0.0239 0.0818 1.0000
11.000 1.1103 0.05008 0.04085 -0.0228 0.0708 1.0000
11.250 1.1082 0.05308 0.04380 -0.0220 0.0643 1.0000
11.500 1.1100 0.05605 0.04699 -0.0212 0.0580 1.0000
11.750 1.1078 0.05922 0.05024 -0.0209 0.0542 1.0000
12.000 1.1082 0.06252 0.05374 -0.0206 0.0505 1.0000
12.250 1.1075 0.06598 0.05740 -0.0206 0.0476 1.0000
12.500 1.1056 0.06960 0.06117 -0.0208 0.0457 1.0000
12.750 1.1034 0.07335 0.06503 -0.0212 0.0443 1.0000
13.000 1.1018 0.07726 0.06904 -0.0216 0.0432 1.0000
13.250 1.0971 0.08196 0.07407 -0.0225 0.0423 1.0000
13.500 1.0883 0.08740 0.07981 -0.0242 0.0416 1.0000
13.750 1.0768 0.09346 0.08614 -0.0266 0.0412 1.0000
14.000 1.0622 0.10040 0.09334 -0.0300 0.0409 1.0000
14.250 1.0450 0.10833 0.10151 -0.0342 0.0410 1.0000
14.500 1.0245 0.11762 0.11101 -0.0396 0.0413 1.0000
14.750 1.0021 0.12815 0.12170 -0.0459 0.0419 1.0000
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