GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 50,000 Max Cl/Cd: 38.01 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe315-il-50000-n5.txt Download as CSV file: xf-goe315-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3693 0.11038 0.10330 -0.0173 1.0000 0.0875
-8.750 -0.3775 0.10964 0.10269 -0.0206 1.0000 0.0889
-8.500 -0.3858 0.10855 0.10172 -0.0237 1.0000 0.0893
-8.250 -0.3568 0.10080 0.09392 -0.0196 1.0000 0.0933
-8.000 -0.3517 0.09783 0.09101 -0.0199 1.0000 0.0962
-7.750 -0.3513 0.09536 0.08863 -0.0208 1.0000 0.0994
-7.500 -0.3556 0.09355 0.08693 -0.0240 1.0000 0.1025
-7.250 -0.3586 0.09221 0.08564 -0.0304 1.0000 0.1038
-7.000 -0.3478 0.08715 0.08069 -0.0274 1.0000 0.1058
-6.750 -0.3387 0.08371 0.07731 -0.0257 1.0000 0.1102
-6.500 -0.3347 0.08128 0.07493 -0.0282 1.0000 0.1160
-6.000 -0.3233 0.07514 0.06893 -0.0287 1.0000 0.1252
-5.750 -0.3180 0.07414 0.06780 -0.0349 1.0000 0.1337
-5.500 -0.3124 0.06978 0.06363 -0.0310 1.0000 0.1366
-5.250 -0.3075 0.06727 0.06119 -0.0296 1.0000 0.1419
-5.000 -0.3045 0.06543 0.05929 -0.0313 1.0000 0.1506
-4.750 -0.2984 0.06259 0.05655 -0.0293 0.9978 0.1553
-4.500 -0.2648 0.05877 0.05261 -0.0348 0.9836 0.1726
-4.250 -0.2350 0.05529 0.04905 -0.0390 0.9685 0.2013
-3.500 -0.0890 0.04415 0.03617 -0.0576 0.9286 0.1031
-3.000 -0.0119 0.03845 0.02967 -0.0629 0.9040 0.0881
-2.750 0.0220 0.03595 0.02696 -0.0647 0.8911 0.0849
-2.500 0.0577 0.03385 0.02450 -0.0663 0.8785 0.0815
-2.250 0.0943 0.03204 0.02222 -0.0676 0.8663 0.0785
-2.000 0.1301 0.03053 0.02026 -0.0686 0.8543 0.0769
-1.750 0.1610 0.02925 0.01876 -0.0691 0.8408 0.0783
-1.500 0.1919 0.02817 0.01744 -0.0693 0.8275 0.0801
-1.250 0.2229 0.02718 0.01617 -0.0694 0.8148 0.0802
-1.000 0.2542 0.02627 0.01499 -0.0695 0.8030 0.0801
-0.750 0.2853 0.02547 0.01398 -0.0694 0.7912 0.0803
-0.500 0.3138 0.02486 0.01319 -0.0689 0.7785 0.0810
-0.250 0.3436 0.02434 0.01250 -0.0687 0.7664 0.0824
0.000 0.3728 0.02394 0.01193 -0.0683 0.7553 0.0864
0.250 0.4002 0.02363 0.01148 -0.0677 0.7439 0.0899
0.500 0.4254 0.02329 0.01111 -0.0670 0.7316 0.0929
0.750 0.4514 0.02307 0.01081 -0.0664 0.7201 0.0965
1.000 0.4784 0.02289 0.01049 -0.0657 0.7093 0.1015
1.250 0.5038 0.02275 0.01031 -0.0650 0.6964 0.1088
1.500 0.5289 0.02259 0.01018 -0.0643 0.6828 0.1267
1.750 0.5688 0.02029 0.00995 -0.0662 0.6683 1.0000
2.000 0.5931 0.02051 0.00985 -0.0650 0.6541 1.0000
2.250 0.6172 0.02073 0.00985 -0.0639 0.6402 1.0000
2.500 0.6415 0.02094 0.00990 -0.0629 0.6269 1.0000
2.750 0.6661 0.02116 0.00999 -0.0619 0.6144 1.0000
3.000 0.6908 0.02137 0.01009 -0.0609 0.6020 1.0000
3.250 0.7146 0.02165 0.01032 -0.0600 0.5886 1.0000
3.500 0.7385 0.02194 0.01057 -0.0591 0.5754 1.0000
3.750 0.7626 0.02223 0.01083 -0.0581 0.5624 1.0000
4.000 0.7868 0.02253 0.01108 -0.0572 0.5494 1.0000
4.250 0.8112 0.02282 0.01135 -0.0563 0.5364 1.0000
4.500 0.8357 0.02314 0.01163 -0.0554 0.5233 1.0000
4.750 0.8588 0.02356 0.01208 -0.0544 0.5088 1.0000
5.000 0.8818 0.02400 0.01256 -0.0535 0.4941 1.0000
5.250 0.9046 0.02448 0.01311 -0.0525 0.4796 1.0000
5.500 0.9273 0.02499 0.01369 -0.0516 0.4655 1.0000
5.750 0.9499 0.02552 0.01429 -0.0507 0.4517 1.0000
6.000 0.9725 0.02604 0.01491 -0.0497 0.4384 1.0000
6.250 0.9945 0.02652 0.01545 -0.0487 0.4241 1.0000
6.500 1.0159 0.02697 0.01597 -0.0475 0.4094 1.0000
6.750 1.0372 0.02743 0.01649 -0.0464 0.3953 1.0000
7.000 1.0577 0.02788 0.01704 -0.0452 0.3804 1.0000
7.250 1.0775 0.02835 0.01758 -0.0439 0.3655 1.0000
7.500 1.0963 0.02885 0.01816 -0.0425 0.3496 1.0000
7.750 1.1150 0.02941 0.01880 -0.0411 0.3352 1.0000
8.000 1.1329 0.03002 0.01953 -0.0397 0.3206 1.0000
8.250 1.1484 0.03071 0.02032 -0.0381 0.3036 1.0000
8.500 1.1626 0.03146 0.02119 -0.0365 0.2863 1.0000
8.750 1.1749 0.03230 0.02214 -0.0346 0.2679 1.0000
9.000 1.1828 0.03326 0.02310 -0.0324 0.2453 1.0000
9.250 1.1890 0.03448 0.02447 -0.0303 0.2214 1.0000
9.500 1.1925 0.03589 0.02596 -0.0280 0.1963 1.0000
9.750 1.1917 0.03757 0.02774 -0.0255 0.1640 1.0000
10.000 1.1863 0.03976 0.02980 -0.0233 0.1319 1.0000
10.250 1.1783 0.04255 0.03238 -0.0216 0.1136 1.0000
10.500 1.1703 0.04573 0.03544 -0.0207 0.1034 1.0000
10.750 1.1636 0.04909 0.03876 -0.0203 0.0967 1.0000
11.000 1.1571 0.05260 0.04223 -0.0201 0.0921 1.0000
11.250 1.1540 0.05588 0.04562 -0.0199 0.0877 1.0000
11.500 1.1500 0.05935 0.04916 -0.0200 0.0838 1.0000
12.000 1.1468 0.06595 0.05593 -0.0200 0.0771 1.0000
12.250 1.1482 0.06902 0.05916 -0.0200 0.0742 1.0000
12.500 1.1509 0.07194 0.06219 -0.0197 0.0719 1.0000
12.750 1.1546 0.07470 0.06501 -0.0194 0.0696 1.0000
13.000 1.1593 0.07749 0.06788 -0.0191 0.0673 1.0000
13.250 1.1596 0.08116 0.07185 -0.0196 0.0652 1.0000
13.500 1.1584 0.08505 0.07600 -0.0204 0.0631 1.0000
13.750 1.1580 0.08889 0.08003 -0.0211 0.0614 1.0000
14.000 1.1582 0.09273 0.08404 -0.0218 0.0602 1.0000
14.250 1.1606 0.09615 0.08755 -0.0222 0.0587 1.0000
14.500 1.1568 0.10079 0.09234 -0.0237 0.0576 1.0000
14.750 1.1427 0.10751 0.09933 -0.0269 0.0571 1.0000
15.000 1.1257 0.11515 0.10723 -0.0310 0.0568 1.0000
15.250 1.1062 0.12389 0.11620 -0.0360 0.0568 1.0000
15.500 1.0839 0.13398 0.12647 -0.0419 0.0570 1.0000
15.750 1.0600 0.14539 0.13797 -0.0487 0.0574 1.0000
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Polar data table (+)
Polar graphs
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