GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 362 AIRFOIL (goe362-il) Reynolds number: 100,000 Max Cl/Cd: 63.29 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe362-il-100000-n5.txt Download as CSV file: xf-goe362-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 362 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2854 0.09180 0.08735 -0.0238 1.0000 0.0390
-6.750 -0.2889 0.09001 0.08566 -0.0226 1.0000 0.0398
-6.500 -0.2917 0.08817 0.08390 -0.0217 1.0000 0.0406
-6.250 -0.2949 0.08638 0.08219 -0.0210 1.0000 0.0414
-6.000 -0.2932 0.08418 0.08006 -0.0218 0.9990 0.0423
-5.750 -0.2519 0.07987 0.07570 -0.0357 0.9894 0.0454
-5.500 -0.2048 0.07523 0.07094 -0.0504 0.9806 0.0462
-5.000 -0.1308 0.06529 0.06081 -0.0663 0.9670 0.0464
-4.750 -0.1232 0.05967 0.05523 -0.0634 0.9601 0.0327
-4.500 -0.0844 0.05471 0.05018 -0.0709 0.9539 0.0301
-4.250 -0.0426 0.04980 0.04511 -0.0789 0.9451 0.0307
-4.000 0.0080 0.04423 0.03931 -0.0882 0.9390 0.0306
-3.750 0.0520 0.03892 0.03372 -0.0950 0.9286 0.0296
-3.500 0.0984 0.03327 0.02764 -0.1015 0.9195 0.0292
-3.250 0.1426 0.02812 0.02189 -0.1063 0.9109 0.0301
-3.000 0.1802 0.02410 0.01708 -0.1088 0.9006 0.0334
-2.750 0.2170 0.02110 0.01331 -0.1104 0.8924 0.0351
-2.500 0.2491 0.01969 0.01169 -0.1112 0.8824 0.0394
-2.250 0.2807 0.01840 0.00998 -0.1115 0.8714 0.0456
-2.000 0.3116 0.01735 0.00879 -0.1118 0.8604 0.0528
-1.750 0.3427 0.01654 0.00778 -0.1119 0.8495 0.0630
-1.500 0.3732 0.01607 0.00721 -0.1120 0.8380 0.0775
-1.250 0.4022 0.01550 0.00652 -0.1118 0.8253 0.0914
-1.000 0.4309 0.01510 0.00603 -0.1116 0.8121 0.1142
-0.750 0.4585 0.01470 0.00564 -0.1112 0.7986 0.1369
-0.500 0.4864 0.01448 0.00541 -0.1109 0.7848 0.1667
-0.250 0.5148 0.01429 0.00520 -0.1107 0.7708 0.2042
0.000 0.5429 0.01403 0.00499 -0.1104 0.7563 0.2555
0.250 0.5704 0.01355 0.00489 -0.1102 0.7419 0.3976
0.500 0.6002 0.01241 0.00468 -0.1101 0.7271 1.0000
0.750 0.6272 0.01254 0.00457 -0.1095 0.7116 1.0000
1.000 0.6540 0.01268 0.00450 -0.1089 0.6962 1.0000
1.250 0.6806 0.01284 0.00447 -0.1084 0.6804 1.0000
1.500 0.7070 0.01301 0.00448 -0.1078 0.6648 1.0000
1.750 0.7333 0.01319 0.00451 -0.1072 0.6489 1.0000
2.000 0.7594 0.01340 0.00458 -0.1066 0.6331 1.0000
2.250 0.7854 0.01362 0.00468 -0.1060 0.6171 1.0000
2.500 0.8112 0.01385 0.00482 -0.1054 0.6008 1.0000
2.750 0.8369 0.01409 0.00498 -0.1048 0.5846 1.0000
3.000 0.8624 0.01434 0.00516 -0.1042 0.5686 1.0000
3.250 0.8879 0.01460 0.00537 -0.1036 0.5529 1.0000
3.500 0.9133 0.01487 0.00559 -0.1030 0.5376 1.0000
3.750 0.9387 0.01515 0.00583 -0.1024 0.5230 1.0000
4.000 0.9639 0.01545 0.00612 -0.1018 0.5090 1.0000
4.250 0.9890 0.01576 0.00640 -0.1012 0.4957 1.0000
4.500 1.0141 0.01610 0.00671 -0.1006 0.4833 1.0000
4.750 1.0390 0.01645 0.00708 -0.1000 0.4711 1.0000
5.000 1.0638 0.01682 0.00748 -0.0994 0.4590 1.0000
5.250 1.0886 0.01720 0.00791 -0.0988 0.4474 1.0000
5.500 1.1132 0.01761 0.00835 -0.0982 0.4363 1.0000
5.750 1.1371 0.01803 0.00882 -0.0975 0.4230 1.0000
6.000 1.1602 0.01844 0.00928 -0.0966 0.4064 1.0000
6.250 1.1825 0.01885 0.00973 -0.0957 0.3874 1.0000
6.500 1.2044 0.01927 0.01021 -0.0947 0.3681 1.0000
6.750 1.2265 0.01970 0.01072 -0.0937 0.3502 1.0000
7.000 1.2487 0.02013 0.01129 -0.0928 0.3325 1.0000
7.250 1.2702 0.02060 0.01187 -0.0918 0.3136 1.0000
7.500 1.2907 0.02112 0.01246 -0.0906 0.2923 1.0000
7.750 1.3102 0.02173 0.01317 -0.0894 0.2669 1.0000
8.000 1.3286 0.02246 0.01393 -0.0881 0.2391 1.0000
8.250 1.3450 0.02338 0.01483 -0.0865 0.2083 1.0000
8.500 1.3592 0.02452 0.01590 -0.0848 0.1743 1.0000
8.750 1.3713 0.02587 0.01716 -0.0828 0.1442 1.0000
9.000 1.3816 0.02734 0.01853 -0.0808 0.1202 1.0000
9.250 1.3903 0.02887 0.01996 -0.0787 0.1003 1.0000
9.500 1.3976 0.03044 0.02148 -0.0764 0.0852 1.0000
9.750 1.4056 0.03182 0.02303 -0.0741 0.0741 1.0000
10.000 1.4114 0.03324 0.02456 -0.0716 0.0626 1.0000
10.250 1.4148 0.03486 0.02629 -0.0690 0.0520 1.0000
10.500 1.4154 0.03677 0.02826 -0.0664 0.0414 1.0000
10.750 1.4136 0.03899 0.03053 -0.0640 0.0332 1.0000
11.000 1.4099 0.04150 0.03311 -0.0620 0.0287 1.0000
11.250 1.4057 0.04425 0.03602 -0.0602 0.0258 1.0000
11.500 1.4019 0.04716 0.03909 -0.0589 0.0234 1.0000
11.750 1.3972 0.05034 0.04241 -0.0581 0.0215 1.0000
12.000 1.3893 0.05410 0.04628 -0.0578 0.0201 1.0000
12.250 1.3819 0.05801 0.05034 -0.0577 0.0191 1.0000
12.500 1.3763 0.06191 0.05445 -0.0578 0.0184 1.0000
12.750 1.3700 0.06605 0.05879 -0.0581 0.0178 1.0000
13.000 1.3641 0.07027 0.06322 -0.0586 0.0173 1.0000
13.250 1.3582 0.07462 0.06776 -0.0592 0.0168 1.0000
13.500 1.3522 0.07912 0.07245 -0.0600 0.0164 1.0000
13.750 1.3457 0.08382 0.07734 -0.0611 0.0159 1.0000
14.000 1.3389 0.08876 0.08247 -0.0625 0.0155 1.0000
14.250 1.3312 0.09401 0.08792 -0.0643 0.0150 1.0000
14.500 1.3230 0.09953 0.09362 -0.0664 0.0147 1.0000
14.750 1.3140 0.10538 0.09965 -0.0689 0.0144 1.0000
15.000 1.3044 0.11155 0.10600 -0.0717 0.0141 1.0000
15.250 1.2943 0.11802 0.11265 -0.0749 0.0139 1.0000
15.500 1.2835 0.12487 0.11968 -0.0785 0.0137 1.0000
15.750 1.2721 0.13215 0.12715 -0.0825 0.0136 1.0000
16.000 1.2597 0.14000 0.13519 -0.0871 0.0136 1.0000
16.250 1.2457 0.14881 0.14420 -0.0924 0.0137 1.0000
16.500 1.2263 0.15991 0.15552 -0.0993 0.0142 1.0000
16.750 1.1931 0.17724 0.17307 -0.1098 0.0157 1.0000
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Polar data table (+)
Polar graphs
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