GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 200,000 Max Cl/Cd: 71.25 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe314-il-200000-n5.txt Download as CSV file: xf-goe314-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3090 0.09148 0.08798 -0.0242 1.0000 0.0318
-7.750 -0.3079 0.08918 0.08573 -0.0238 1.0000 0.0322
-7.500 -0.3100 0.08707 0.08368 -0.0231 1.0000 0.0326
-7.250 -0.3143 0.08513 0.08181 -0.0221 1.0000 0.0332
-7.000 -0.3156 0.08293 0.07967 -0.0220 1.0000 0.0343
-6.750 -0.2891 0.07850 0.07518 -0.0354 0.9899 0.0366
-6.500 -0.2583 0.07356 0.07013 -0.0453 0.9779 0.0368
-6.250 -0.2301 0.06897 0.06540 -0.0520 0.9659 0.0369
-6.000 -0.2150 0.06485 0.06134 -0.0520 0.9569 0.0374
-5.750 -0.1933 0.06179 0.05829 -0.0533 0.9478 0.0382
-5.500 -0.1661 0.05869 0.05514 -0.0569 0.9356 0.0396
-5.250 -0.1335 0.05508 0.05141 -0.0623 0.9228 0.0415
-5.000 -0.0850 0.05109 0.04703 -0.0715 0.9086 0.0441
-4.750 -0.0491 0.04758 0.04322 -0.0758 0.8945 0.0443
-4.250 0.0001 0.04098 0.03651 -0.0794 0.8642 0.0457
-4.000 0.0253 0.03880 0.03419 -0.0805 0.8478 0.0466
-3.750 0.0505 0.03665 0.03186 -0.0812 0.8317 0.0475
-3.500 0.0755 0.03461 0.02961 -0.0816 0.8160 0.0486
-3.250 0.1083 0.03156 0.02588 -0.0817 0.8016 0.0442
-3.000 0.1273 0.02952 0.02386 -0.0815 0.7854 0.0428
-2.750 0.1517 0.02768 0.02177 -0.0810 0.7693 0.0426
-2.500 0.1766 0.02594 0.01974 -0.0804 0.7523 0.0430
-2.250 0.2005 0.02431 0.01787 -0.0798 0.7341 0.0420
-2.000 0.2251 0.02272 0.01599 -0.0790 0.7146 0.0412
-1.750 0.2499 0.02125 0.01419 -0.0781 0.6937 0.0406
-1.500 0.2749 0.01994 0.01256 -0.0772 0.6706 0.0405
-1.250 0.2998 0.01882 0.01111 -0.0762 0.6463 0.0406
-1.000 0.3247 0.01790 0.00987 -0.0753 0.6213 0.0410
-0.500 0.3748 0.01660 0.00794 -0.0734 0.5727 0.0434
-0.250 0.3999 0.01603 0.00710 -0.0726 0.5521 0.0437
0.000 0.4251 0.01558 0.00641 -0.0718 0.5337 0.0441
0.250 0.4503 0.01515 0.00581 -0.0711 0.5173 0.0446
0.500 0.4754 0.01472 0.00530 -0.0704 0.5027 0.0455
0.750 0.5006 0.01446 0.00497 -0.0698 0.4894 0.0465
1.000 0.5258 0.01430 0.00476 -0.0692 0.4770 0.0483
1.250 0.5509 0.01421 0.00458 -0.0685 0.4645 0.0509
1.500 0.5756 0.01411 0.00438 -0.0678 0.4510 0.0525
1.750 0.6003 0.01393 0.00417 -0.0671 0.4379 0.0539
2.000 0.6250 0.01378 0.00402 -0.0664 0.4265 0.0561
2.250 0.6498 0.01375 0.00396 -0.0657 0.4174 0.0587
2.500 0.6753 0.01375 0.00393 -0.0652 0.4086 0.0631
2.750 0.7003 0.01376 0.00393 -0.0646 0.4011 0.0694
3.250 0.7509 0.01386 0.00404 -0.0635 0.3853 0.0905
3.500 0.7702 0.01275 0.00421 -0.0621 0.3775 0.6665
4.000 0.8493 0.01270 0.00449 -0.0669 0.3552 1.0000
4.250 0.8733 0.01289 0.00464 -0.0661 0.3433 1.0000
4.500 0.8971 0.01311 0.00479 -0.0653 0.3319 1.0000
4.750 0.9206 0.01335 0.00496 -0.0644 0.3215 1.0000
5.000 0.9444 0.01357 0.00516 -0.0636 0.3113 1.0000
5.250 0.9682 0.01381 0.00539 -0.0629 0.3022 1.0000
5.500 0.9915 0.01409 0.00561 -0.0620 0.2930 1.0000
5.750 1.0153 0.01433 0.00587 -0.0613 0.2838 1.0000
6.000 1.0384 0.01462 0.00614 -0.0604 0.2750 1.0000
6.250 1.0616 0.01491 0.00643 -0.0596 0.2655 1.0000
6.500 1.0845 0.01522 0.00673 -0.0588 0.2559 1.0000
6.750 1.1068 0.01556 0.00706 -0.0579 0.2464 1.0000
7.000 1.1290 0.01591 0.00740 -0.0570 0.2347 1.0000
7.250 1.1512 0.01627 0.00776 -0.0561 0.2248 1.0000
7.500 1.1728 0.01666 0.00815 -0.0551 0.2170 1.0000
7.750 1.1951 0.01701 0.00856 -0.0542 0.2097 1.0000
8.000 1.2161 0.01744 0.00900 -0.0532 0.2031 1.0000
8.250 1.2380 0.01780 0.00943 -0.0523 0.1966 1.0000
8.500 1.2582 0.01827 0.00991 -0.0511 0.1891 1.0000
8.750 1.2790 0.01869 0.01041 -0.0501 0.1804 1.0000
9.000 1.2980 0.01921 0.01094 -0.0489 0.1697 1.0000
9.250 1.3160 0.01980 0.01151 -0.0475 0.1555 1.0000
9.500 1.3334 0.02042 0.01213 -0.0461 0.1384 1.0000
9.750 1.3421 0.02165 0.01306 -0.0437 0.0871 1.0000
10.000 1.3480 0.02304 0.01430 -0.0409 0.0698 1.0000
10.250 1.3554 0.02412 0.01540 -0.0382 0.0636 1.0000
10.500 1.3647 0.02502 0.01638 -0.0357 0.0596 1.0000
10.750 1.3734 0.02595 0.01744 -0.0333 0.0564 1.0000
11.000 1.3793 0.02709 0.01867 -0.0307 0.0534 1.0000
11.250 1.3827 0.02843 0.02010 -0.0282 0.0502 1.0000
11.500 1.3925 0.02940 0.02124 -0.0264 0.0469 1.0000
11.750 1.3972 0.03077 0.02273 -0.0245 0.0429 1.0000
12.000 1.4015 0.03225 0.02432 -0.0228 0.0393 1.0000
12.250 1.4068 0.03376 0.02594 -0.0214 0.0348 1.0000
12.500 1.4098 0.03557 0.02784 -0.0201 0.0297 1.0000
12.750 1.4094 0.03779 0.03012 -0.0191 0.0258 1.0000
13.000 1.4069 0.04038 0.03277 -0.0184 0.0235 1.0000
13.250 1.4017 0.04347 0.03595 -0.0181 0.0219 1.0000
13.500 1.3952 0.04694 0.03956 -0.0183 0.0208 1.0000
13.750 1.3865 0.05094 0.04368 -0.0189 0.0199 1.0000
14.000 1.3762 0.05543 0.04829 -0.0200 0.0192 1.0000
14.250 1.3653 0.06022 0.05322 -0.0215 0.0188 1.0000
14.500 1.3509 0.06572 0.05884 -0.0233 0.0183 1.0000
15.000 1.3253 0.07661 0.07000 -0.0272 0.0178 1.0000
15.250 1.3134 0.08209 0.07562 -0.0293 0.0176 1.0000
15.500 1.3022 0.08755 0.08121 -0.0314 0.0174 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)