GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 358 AIRFOIL (goe358-il) Reynolds number: 100,000 Max Cl/Cd: 61.77 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe358-il-100000-n5.txt Download as CSV file: xf-goe358-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 358 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3404 0.09521 0.09016 -0.0387 1.0000 0.0448
-8.500 -0.3506 0.09203 0.08707 -0.0383 1.0000 0.0457
-8.250 -0.3649 0.08895 0.08409 -0.0372 1.0000 0.0464
-8.000 -0.3833 0.08612 0.08136 -0.0355 1.0000 0.0467
-7.750 -0.4002 0.08230 0.07765 -0.0353 1.0000 0.0471
-7.250 -0.4020 0.06876 0.06419 -0.0483 0.9946 0.0495
-6.750 -0.2882 0.03320 0.02657 -0.1148 0.9833 0.0607
-6.500 -0.2534 0.03142 0.02476 -0.1180 0.9790 0.0641
-6.250 -0.2125 0.02947 0.02247 -0.1226 0.9757 0.0684
-6.000 -0.1733 0.02744 0.01984 -0.1267 0.9706 0.0726
-5.750 -0.1345 0.02569 0.01785 -0.1301 0.9667 0.0758
-5.500 -0.0983 0.02465 0.01670 -0.1324 0.9617 0.0792
-5.250 -0.0607 0.02364 0.01548 -0.1348 0.9563 0.0829
-5.000 -0.0216 0.02262 0.01421 -0.1374 0.9519 0.0855
-4.750 0.0136 0.02182 0.01321 -0.1390 0.9451 0.0880
-4.500 0.0531 0.02099 0.01243 -0.1415 0.9412 0.0920
-4.250 0.0856 0.02042 0.01181 -0.1425 0.9329 0.0951
-4.000 0.1252 0.01981 0.01111 -0.1448 0.9284 0.0984
-3.750 0.1576 0.01935 0.01055 -0.1456 0.9197 0.1017
-3.500 0.1960 0.01875 0.00996 -0.1477 0.9141 0.1066
-3.250 0.2286 0.01829 0.00944 -0.1484 0.9033 0.1145
-3.000 0.2648 0.01767 0.00882 -0.1499 0.8930 0.1280
-2.750 0.3018 0.01694 0.00815 -0.1515 0.8822 0.1541
-2.500 0.3334 0.01641 0.00786 -0.1522 0.8686 0.2068
-2.250 0.3646 0.01630 0.00783 -0.1524 0.8563 0.2600
-2.000 0.3975 0.01624 0.00767 -0.1529 0.8458 0.2900
-1.750 0.4281 0.01627 0.00765 -0.1529 0.8337 0.3114
-1.500 0.4580 0.01636 0.00768 -0.1529 0.8207 0.3317
-1.250 0.4884 0.01646 0.00771 -0.1528 0.8079 0.3500
-1.000 0.5186 0.01654 0.00774 -0.1527 0.7950 0.3662
-0.750 0.5487 0.01659 0.00773 -0.1526 0.7816 0.3800
-0.500 0.5785 0.01659 0.00762 -0.1526 0.7673 0.3913
-0.250 0.6074 0.01660 0.00756 -0.1523 0.7525 0.4004
0.000 0.6361 0.01661 0.00750 -0.1521 0.7377 0.4092
0.250 0.6646 0.01664 0.00744 -0.1519 0.7230 0.4176
0.500 0.6928 0.01664 0.00737 -0.1517 0.7078 0.4238
0.750 0.7205 0.01667 0.00734 -0.1514 0.6921 0.4292
1.000 0.7483 0.01671 0.00728 -0.1511 0.6756 0.4348
1.250 0.7754 0.01675 0.00727 -0.1507 0.6586 0.4397
1.500 0.8022 0.01682 0.00730 -0.1502 0.6411 0.4452
1.750 0.8291 0.01692 0.00732 -0.1498 0.6234 0.4514
2.000 0.8558 0.01701 0.00737 -0.1494 0.6060 0.4562
2.250 0.8824 0.01714 0.00745 -0.1489 0.5888 0.4618
2.500 0.9090 0.01731 0.00752 -0.1484 0.5722 0.4686
2.750 0.9350 0.01747 0.00765 -0.1479 0.5563 0.4744
3.000 0.9612 0.01767 0.00780 -0.1474 0.5412 0.4813
3.250 0.9871 0.01789 0.00797 -0.1468 0.5268 0.4877
3.500 1.0128 0.01812 0.00819 -0.1463 0.5131 0.4950
3.750 1.0385 0.01838 0.00841 -0.1457 0.5004 0.5032
4.000 1.0639 0.01864 0.00867 -0.1452 0.4882 0.5120
4.250 1.0894 0.01889 0.00898 -0.1446 0.4769 0.5212
4.500 1.1149 0.01918 0.00927 -0.1441 0.4674 0.5320
4.750 1.1403 0.01944 0.00963 -0.1436 0.4585 0.5439
5.000 1.1658 0.01972 0.01000 -0.1431 0.4511 0.5588
5.250 1.1910 0.01998 0.01041 -0.1425 0.4426 0.5787
5.500 1.2159 0.02022 0.01079 -0.1419 0.4354 0.6104
5.750 1.2366 0.02002 0.01115 -0.1404 0.4275 1.0000
6.000 1.2621 0.02047 0.01154 -0.1399 0.4205 1.0000
6.250 1.2867 0.02089 0.01206 -0.1393 0.4119 1.0000
6.500 1.3110 0.02134 0.01249 -0.1386 0.4036 1.0000
6.750 1.3339 0.02175 0.01300 -0.1377 0.3926 1.0000
7.000 1.3564 0.02219 0.01348 -0.1367 0.3814 1.0000
7.250 1.3787 0.02265 0.01396 -0.1357 0.3714 1.0000
7.500 1.4000 0.02309 0.01455 -0.1345 0.3594 1.0000
7.750 1.4206 0.02357 0.01511 -0.1332 0.3469 1.0000
8.000 1.4405 0.02407 0.01568 -0.1318 0.3341 1.0000
8.250 1.4598 0.02460 0.01631 -0.1304 0.3218 1.0000
8.500 1.4773 0.02514 0.01697 -0.1286 0.3054 1.0000
8.750 1.4927 0.02572 0.01768 -0.1266 0.2808 1.0000
9.000 1.5046 0.02647 0.01841 -0.1242 0.2412 1.0000
9.250 1.5068 0.02785 0.01940 -0.1206 0.1897 1.0000
9.500 1.5063 0.02954 0.02087 -0.1167 0.1644 1.0000
9.750 1.5073 0.03118 0.02246 -0.1131 0.1454 1.0000
10.000 1.5096 0.03282 0.02411 -0.1099 0.1266 1.0000
10.250 1.5120 0.03450 0.02581 -0.1070 0.1074 1.0000
10.500 1.5112 0.03648 0.02775 -0.1040 0.0931 1.0000
10.750 1.5084 0.03872 0.02997 -0.1012 0.0832 1.0000
11.000 1.5039 0.04122 0.03250 -0.0986 0.0758 1.0000
11.250 1.5003 0.04381 0.03519 -0.0964 0.0696 1.0000
11.500 1.4931 0.04689 0.03832 -0.0945 0.0647 1.0000
11.750 1.4885 0.04993 0.04150 -0.0930 0.0602 1.0000
12.000 1.4825 0.05327 0.04499 -0.0918 0.0563 1.0000
12.250 1.4727 0.05720 0.04897 -0.0909 0.0535 1.0000
12.500 1.4692 0.06056 0.05251 -0.0902 0.0501 1.0000
12.750 1.4643 0.06418 0.05628 -0.0898 0.0470 1.0000
13.000 1.4576 0.06811 0.06031 -0.0896 0.0448 1.0000
13.250 1.4490 0.07234 0.06460 -0.0895 0.0430 1.0000
13.500 1.4461 0.07593 0.06834 -0.0893 0.0410 1.0000
13.750 1.4433 0.07959 0.07215 -0.0893 0.0389 1.0000
14.000 1.4398 0.08341 0.07610 -0.0895 0.0371 1.0000
14.250 1.4359 0.08737 0.08017 -0.0898 0.0356 1.0000
14.500 1.4316 0.09142 0.08430 -0.0903 0.0344 1.0000
14.750 1.4277 0.09528 0.08818 -0.0905 0.0332 1.0000
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Polar data table (+)
Polar graphs
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