GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.44 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe324-il-1000000.txt Download as CSV file: xf-goe324-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 324 (HANSA-BRANDENBURG) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2692 0.09198 0.08902 -0.0061 0.5955 0.0210
-7.750 -0.2674 0.08727 0.08432 -0.0118 0.5929 0.0217
-7.500 -0.2648 0.08243 0.07948 -0.0187 0.5902 0.0218
-7.250 -0.2523 0.07755 0.07457 -0.0253 0.5871 0.0218
-7.000 -0.2397 0.07270 0.06967 -0.0303 0.5838 0.0219
-6.750 -0.2273 0.06954 0.06651 -0.0318 0.5811 0.0220
-6.500 -0.2116 0.06674 0.06370 -0.0337 0.5777 0.0221
-6.250 -0.1943 0.06389 0.06082 -0.0360 0.5739 0.0222
-6.000 -0.1755 0.06097 0.05784 -0.0386 0.5700 0.0223
-5.750 -0.1553 0.05799 0.05479 -0.0414 0.5658 0.0225
-5.500 -0.1336 0.05491 0.05168 -0.0442 0.5624 0.0227
-5.250 -0.1107 0.05181 0.04850 -0.0470 0.5583 0.0230
-5.000 -0.0867 0.04866 0.04526 -0.0496 0.5541 0.0235
-4.750 -0.0498 0.04183 0.03807 -0.0548 0.5506 0.0251
-4.500 -0.0272 0.03700 0.03304 -0.0566 0.5472 0.0253
-4.250 -0.0044 0.03501 0.03100 -0.0573 0.5429 0.0255
-4.000 0.0200 0.03334 0.02925 -0.0579 0.5381 0.0256
-3.750 0.0452 0.03174 0.02755 -0.0584 0.5331 0.0258
-3.500 0.0713 0.03009 0.02580 -0.0589 0.5286 0.0261
-3.250 0.0982 0.02836 0.02395 -0.0593 0.5233 0.0265
-3.000 0.1256 0.02654 0.02197 -0.0596 0.5178 0.0272
-2.750 0.1567 0.02217 0.01696 -0.0592 0.5136 0.0291
-2.500 0.1834 0.02085 0.01562 -0.0595 0.5085 0.0293
-2.250 0.2108 0.01989 0.01459 -0.0597 0.5029 0.0296
-2.000 0.2386 0.01905 0.01364 -0.0599 0.4974 0.0300
-1.750 0.2669 0.01815 0.01265 -0.0600 0.4925 0.0306
-1.500 0.2980 0.01786 0.01194 -0.0595 0.4870 0.0330
-1.250 0.3250 0.01570 0.00967 -0.0598 0.4814 0.0338
-1.000 0.3536 0.01507 0.00901 -0.0599 0.4768 0.0343
-0.750 0.3824 0.01453 0.00840 -0.0601 0.4719 0.0350
-0.500 0.4125 0.01484 0.00848 -0.0599 0.4667 0.0376
-0.250 0.4408 0.01334 0.00689 -0.0600 0.4626 0.0386
0.000 0.4697 0.01284 0.00639 -0.0602 0.4581 0.0394
0.250 0.4986 0.01252 0.00601 -0.0603 0.4529 0.0408
0.500 0.5277 0.01217 0.00553 -0.0603 0.4474 0.0444
0.750 0.5567 0.01177 0.00515 -0.0605 0.4427 0.0457
1.000 0.5858 0.01159 0.00490 -0.0605 0.4376 0.0479
1.250 0.6150 0.01025 0.00335 -0.0598 0.4327 0.0325
1.500 0.6440 0.01007 0.00318 -0.0599 0.4293 0.0327
1.750 0.6730 0.00995 0.00305 -0.0600 0.4257 0.0330
2.000 0.7017 0.00969 0.00279 -0.0601 0.4222 0.0337
2.250 0.7305 0.00962 0.00273 -0.0603 0.4184 0.0348
2.500 0.7593 0.00959 0.00269 -0.0604 0.4146 0.0356
2.750 0.7885 0.00952 0.00264 -0.0606 0.4117 0.0367
3.000 0.8176 0.00951 0.00263 -0.0608 0.4079 0.0376
3.250 0.8464 0.00949 0.00259 -0.0609 0.4032 0.0393
3.500 0.8750 0.00954 0.00263 -0.0611 0.3982 0.0415
3.750 0.9042 0.00952 0.00264 -0.0613 0.3948 0.0456
4.000 0.9330 0.00940 0.00272 -0.0615 0.3910 0.1504
4.250 0.9587 0.00777 0.00294 -0.0616 0.3870 1.0000
4.500 0.9869 0.00793 0.00304 -0.0617 0.3825 1.0000
4.750 1.0157 0.00801 0.00312 -0.0619 0.3796 1.0000
5.000 1.0443 0.00811 0.00320 -0.0620 0.3757 1.0000
5.250 1.0726 0.00824 0.00331 -0.0622 0.3714 1.0000
5.500 1.1005 0.00842 0.00344 -0.0623 0.3667 1.0000
5.750 1.1291 0.00851 0.00354 -0.0625 0.3631 1.0000
6.000 1.1574 0.00863 0.00366 -0.0627 0.3583 1.0000
6.250 1.1852 0.00882 0.00380 -0.0629 0.3526 1.0000
6.500 1.2133 0.00895 0.00394 -0.0631 0.3476 1.0000
6.750 1.2412 0.00911 0.00408 -0.0632 0.3408 1.0000
7.000 1.2686 0.00932 0.00426 -0.0634 0.3337 1.0000
7.250 1.2962 0.00950 0.00442 -0.0635 0.3261 1.0000
7.500 1.3232 0.00974 0.00463 -0.0636 0.3177 1.0000
7.750 1.3501 0.00999 0.00484 -0.0637 0.3077 1.0000
8.000 1.3767 0.01026 0.00508 -0.0638 0.2978 1.0000
8.250 1.4026 0.01058 0.00536 -0.0639 0.2872 1.0000
8.750 1.4537 0.01129 0.00598 -0.0639 0.2664 1.0000
9.000 1.4787 0.01167 0.00633 -0.0638 0.2573 1.0000
9.250 1.5032 0.01208 0.00670 -0.0637 0.2483 1.0000
9.500 1.5280 0.01244 0.00705 -0.0636 0.2411 1.0000
9.750 1.5518 0.01287 0.00746 -0.0635 0.2339 1.0000
10.000 1.5758 0.01326 0.00785 -0.0633 0.2274 1.0000
10.250 1.5983 0.01377 0.00832 -0.0631 0.2192 1.0000
10.500 1.6213 0.01420 0.00875 -0.0628 0.2124 1.0000
10.750 1.6429 0.01471 0.00924 -0.0625 0.2058 1.0000
11.000 1.6647 0.01519 0.00972 -0.0621 0.2005 1.0000
11.250 1.6863 0.01564 0.01020 -0.0618 0.1953 1.0000
11.500 1.7048 0.01630 0.01084 -0.0611 0.1891 1.0000
11.750 1.7249 0.01680 0.01137 -0.0606 0.1842 1.0000
12.000 1.7390 0.01759 0.01215 -0.0595 0.1767 1.0000
12.250 1.7505 0.01848 0.01305 -0.0582 0.1695 1.0000
12.500 1.7575 0.01993 0.01449 -0.0573 0.1612 1.0000
12.750 1.7654 0.02163 0.01619 -0.0570 0.1516 1.0000
13.000 1.7685 0.02392 0.01846 -0.0569 0.1398 1.0000
13.250 1.7629 0.02709 0.02157 -0.0565 0.1249 1.0000
13.750 1.7403 0.03442 0.02883 -0.0554 0.0998 1.0000
14.000 1.7320 0.03776 0.03219 -0.0548 0.0942 1.0000
14.250 1.7273 0.04077 0.03524 -0.0543 0.0908 1.0000
14.500 1.7226 0.04379 0.03832 -0.0539 0.0886 1.0000
14.750 1.7160 0.04704 0.04162 -0.0535 0.0864 1.0000
15.000 1.7095 0.05040 0.04503 -0.0532 0.0840 1.0000
15.250 1.7068 0.05346 0.04816 -0.0531 0.0823 1.0000
15.500 1.7073 0.05623 0.05100 -0.0531 0.0813 1.0000
15.750 1.7056 0.05930 0.05415 -0.0531 0.0801 1.0000
16.000 1.7026 0.06251 0.05743 -0.0532 0.0787 1.0000
16.250 1.6982 0.06597 0.06094 -0.0534 0.0772 1.0000
16.500 1.6912 0.06980 0.06484 -0.0536 0.0755 1.0000
16.750 1.6828 0.07383 0.06894 -0.0540 0.0736 1.0000
17.000 1.6834 0.07673 0.07191 -0.0542 0.0721 1.0000
17.250 1.6824 0.07991 0.07516 -0.0546 0.0703 1.0000
17.500 1.6785 0.08346 0.07876 -0.0551 0.0679 1.0000
17.750 1.6694 0.08770 0.08304 -0.0557 0.0652 1.0000
18.000 1.6656 0.09129 0.08670 -0.0562 0.0624 1.0000
18.500 1.6404 0.10098 0.09637 -0.0581 0.0469 1.0000
18.750 1.6163 0.10756 0.10291 -0.0596 0.0384 1.0000
19.000 1.5974 0.11354 0.10893 -0.0611 0.0341 1.0000
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Polar data table (+)
Polar graphs
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