GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 200,000 Max Cl/Cd: 71.21 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe316-il-200000.txt Download as CSV file: xf-goe316-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4090 0.10783 0.10445 0.0009 1.0000 0.0336
-8.750 -0.4034 0.10452 0.10117 -0.0012 1.0000 0.0346
-8.500 -0.3994 0.10152 0.09821 -0.0049 1.0000 0.0356
-8.250 -0.3005 0.08559 0.08254 -0.0169 1.0000 0.0373
-8.000 -0.2926 0.08206 0.07903 -0.0167 1.0000 0.0382
-7.750 -0.2884 0.07860 0.07560 -0.0176 1.0000 0.0390
-7.500 -0.3797 0.08621 0.08305 -0.0188 1.0000 0.0371
-7.250 -0.3697 0.08296 0.07982 -0.0180 1.0000 0.0379
-7.000 -0.3588 0.07955 0.07644 -0.0201 1.0000 0.0388
-6.750 -0.3465 0.07594 0.07284 -0.0235 1.0000 0.0399
-6.500 -0.3326 0.07221 0.06911 -0.0274 1.0000 0.0412
-6.250 -0.3154 0.06840 0.06527 -0.0326 1.0000 0.0431
-6.000 -0.2862 0.06548 0.06197 -0.0428 0.9963 0.0447
-5.750 -0.2636 0.05857 0.05516 -0.0462 0.9856 0.0456
-5.500 -0.2362 0.05487 0.05148 -0.0490 0.9720 0.0471
-5.250 -0.2038 0.05124 0.04773 -0.0533 0.9551 0.0493
-5.000 -0.1601 0.04901 0.04496 -0.0586 0.9330 0.0546
-4.750 -0.1375 0.04445 0.04011 -0.0602 0.9126 0.0557
-4.500 -0.1218 0.04119 0.03689 -0.0598 0.8921 0.0571
-4.250 -0.1033 0.03906 0.03467 -0.0591 0.8724 0.0593
-4.000 -0.0802 0.03707 0.03245 -0.0589 0.8551 0.0630
-3.750 -0.0505 0.03513 0.02990 -0.0592 0.8405 0.0684
-3.500 -0.0301 0.03247 0.02724 -0.0591 0.8266 0.0704
-3.250 -0.0065 0.03076 0.02537 -0.0589 0.8132 0.0739
-3.000 0.0220 0.02947 0.02357 -0.0587 0.8006 0.0829
-2.750 0.0450 0.02750 0.02161 -0.0586 0.7875 0.0870
-2.500 0.0732 0.02646 0.02015 -0.0584 0.7741 0.0977
-2.250 0.0980 0.02474 0.01841 -0.0584 0.7606 0.1032
-2.000 0.1247 0.02346 0.01689 -0.0583 0.7473 0.1153
-1.750 0.1510 0.02227 0.01553 -0.0582 0.7339 0.1304
-1.500 0.1779 0.02182 0.01486 -0.0580 0.7203 0.1534
-1.250 0.2027 0.02034 0.01328 -0.0581 0.7068 0.1871
-1.000 0.2283 0.01885 0.01180 -0.0581 0.6928 0.2115
-0.750 0.2564 0.01793 0.01071 -0.0578 0.6778 0.2295
-0.500 0.3002 0.01745 0.00910 -0.0550 0.6635 0.0817
-0.250 0.3281 0.01617 0.00775 -0.0546 0.6467 0.0772
0.000 0.3561 0.01553 0.00700 -0.0542 0.6270 0.0774
0.250 0.3837 0.01490 0.00624 -0.0538 0.6056 0.0764
0.500 0.4111 0.01439 0.00559 -0.0533 0.5820 0.0753
0.750 0.4380 0.01403 0.00508 -0.0528 0.5566 0.0755
1.000 0.4649 0.01378 0.00471 -0.0525 0.5301 0.0766
1.250 0.4918 0.01368 0.00446 -0.0522 0.5065 0.0790
1.500 0.5189 0.01353 0.00423 -0.0520 0.4859 0.0838
1.750 0.5464 0.01351 0.00410 -0.0519 0.4694 0.0890
2.000 0.5741 0.01355 0.00402 -0.0518 0.4562 0.0968
2.250 0.6017 0.01347 0.00399 -0.0518 0.4461 0.1430
2.750 0.6553 0.01197 0.00412 -0.0511 0.4300 1.0000
3.000 0.6829 0.01222 0.00427 -0.0511 0.4230 1.0000
3.250 0.7103 0.01253 0.00445 -0.0510 0.4174 1.0000
3.500 0.7380 0.01278 0.00467 -0.0510 0.4119 1.0000
3.750 0.7656 0.01306 0.00491 -0.0510 0.4074 1.0000
4.000 0.7930 0.01343 0.00516 -0.0510 0.4037 1.0000
4.250 0.8207 0.01371 0.00548 -0.0510 0.3999 1.0000
4.500 0.8483 0.01401 0.00579 -0.0510 0.3963 1.0000
4.750 0.8758 0.01434 0.00612 -0.0511 0.3930 1.0000
5.000 0.9033 0.01472 0.00646 -0.0511 0.3898 1.0000
5.250 0.9306 0.01510 0.00686 -0.0511 0.3864 1.0000
5.500 0.9578 0.01539 0.00724 -0.0511 0.3816 1.0000
5.750 0.9847 0.01569 0.00750 -0.0510 0.3759 1.0000
6.000 1.0112 0.01602 0.00788 -0.0509 0.3698 1.0000
6.250 1.0377 0.01627 0.00818 -0.0508 0.3630 1.0000
6.500 1.0644 0.01671 0.00856 -0.0508 0.3578 1.0000
6.750 1.0907 0.01698 0.00900 -0.0507 0.3527 1.0000
7.000 1.1173 0.01732 0.00941 -0.0506 0.3482 1.0000
7.250 1.1439 0.01779 0.00984 -0.0506 0.3434 1.0000
7.500 1.1695 0.01807 0.01033 -0.0504 0.3380 1.0000
7.750 1.1954 0.01836 0.01069 -0.0502 0.3319 1.0000
8.000 1.2209 0.01873 0.01113 -0.0500 0.3254 1.0000
8.250 1.2457 0.01889 0.01144 -0.0496 0.3171 1.0000
8.500 1.2699 0.01908 0.01172 -0.0492 0.3076 1.0000
8.750 1.2935 0.01914 0.01181 -0.0487 0.2957 1.0000
9.000 1.3165 0.01912 0.01193 -0.0481 0.2824 1.0000
9.250 1.3395 0.01912 0.01211 -0.0475 0.2676 1.0000
9.500 1.3630 0.01914 0.01237 -0.0470 0.2463 1.0000
9.750 1.3828 0.01950 0.01263 -0.0462 0.1920 1.0000
10.000 1.3879 0.02168 0.01429 -0.0442 0.1257 1.0000
10.250 1.3911 0.02401 0.01629 -0.0420 0.0807 1.0000
10.500 1.3921 0.02626 0.01843 -0.0395 0.0628 1.0000
10.750 1.3876 0.02856 0.02080 -0.0363 0.0540 1.0000
11.000 1.3784 0.03105 0.02334 -0.0332 0.0493 1.0000
11.250 1.3722 0.03377 0.02619 -0.0314 0.0458 1.0000
11.500 1.3712 0.03638 0.02892 -0.0306 0.0424 1.0000
11.750 1.3669 0.03952 0.03213 -0.0303 0.0401 1.0000
12.000 1.3560 0.04344 0.03606 -0.0299 0.0384 1.0000
12.250 1.3587 0.04610 0.03890 -0.0298 0.0367 1.0000
12.500 1.3582 0.04910 0.04202 -0.0297 0.0351 1.0000
12.750 1.3573 0.05214 0.04515 -0.0296 0.0338 1.0000
13.000 1.3564 0.05520 0.04827 -0.0296 0.0327 1.0000
13.250 1.3552 0.05819 0.05127 -0.0292 0.0317 1.0000
13.500 1.3564 0.06069 0.05378 -0.0277 0.0305 1.0000
13.750 1.3583 0.06356 0.05681 -0.0277 0.0297 1.0000
14.000 1.3596 0.06648 0.05987 -0.0277 0.0287 1.0000
14.250 1.3603 0.06952 0.06303 -0.0278 0.0278 1.0000
14.500 1.3612 0.07251 0.06614 -0.0278 0.0270 1.0000
14.750 1.3625 0.07546 0.06920 -0.0278 0.0264 1.0000
15.000 1.3637 0.07847 0.07229 -0.0278 0.0258 1.0000
15.250 1.3660 0.08134 0.07523 -0.0274 0.0253 1.0000
15.500 1.3696 0.08410 0.07808 -0.0263 0.0247 1.0000
15.750 1.3669 0.08809 0.08223 -0.0259 0.0244 1.0000
16.000 1.3583 0.09292 0.08729 -0.0275 0.0243 1.0000
16.250 1.3481 0.09818 0.09277 -0.0296 0.0242 1.0000
16.500 1.3364 0.10384 0.09864 -0.0320 0.0241 1.0000
16.750 1.3231 0.10997 0.10499 -0.0350 0.0240 1.0000
17.000 1.3089 0.11650 0.11173 -0.0384 0.0240 1.0000
17.250 1.2935 0.12352 0.11896 -0.0423 0.0240 1.0000
17.500 1.2770 0.13100 0.12663 -0.0467 0.0240 1.0000
17.750 1.2597 0.13897 0.13479 -0.0516 0.0241 1.0000
18.000 1.2422 0.14733 0.14333 -0.0568 0.0242 1.0000
18.250 1.2239 0.15626 0.15241 -0.0626 0.0243 1.0000
18.500 1.2063 0.16549 0.16180 -0.0687 0.0245 1.0000
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Polar data table (+)
Polar graphs
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