GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 100,000 Max Cl/Cd: 54.52 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe553-il-100000-n5.txt Download as CSV file: xf-goe553-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2677 0.10802 0.10301 -0.0419 1.0000 0.0791
-9.750 -0.2829 0.10508 0.10018 -0.0449 1.0000 0.0799
-9.500 -0.2913 0.10204 0.09724 -0.0461 1.0000 0.0800
-9.250 -0.2736 0.09888 0.09412 -0.0432 1.0000 0.0812
-9.000 -0.2664 0.09669 0.09200 -0.0415 1.0000 0.0825
-8.500 -0.2915 0.07823 0.07356 -0.0577 0.9762 0.0523
-8.250 -0.2732 0.07421 0.06953 -0.0619 0.9607 0.0518
-8.000 -0.2581 0.06810 0.06339 -0.0700 0.9426 0.0512
-7.750 -0.2499 0.05810 0.05320 -0.0846 0.9194 0.0508
-7.500 -0.2403 0.05046 0.04517 -0.0940 0.8988 0.0509
-7.250 -0.2254 0.04482 0.03909 -0.0993 0.8800 0.0507
-7.000 -0.2071 0.04037 0.03416 -0.1025 0.8620 0.0505
-6.750 -0.1867 0.03673 0.03001 -0.1044 0.8447 0.0505
-6.500 -0.1643 0.03380 0.02658 -0.1056 0.8284 0.0509
-6.250 -0.1404 0.03135 0.02354 -0.1063 0.8129 0.0519
-6.000 -0.1153 0.02941 0.02113 -0.1067 0.7986 0.0527
-5.750 -0.0891 0.02783 0.01929 -0.1069 0.7856 0.0532
-5.500 -0.0630 0.02647 0.01767 -0.1069 0.7728 0.0537
-5.250 -0.0368 0.02528 0.01625 -0.1067 0.7607 0.0543
-5.000 -0.0098 0.02422 0.01496 -0.1066 0.7501 0.0550
-4.750 0.0168 0.02331 0.01386 -0.1064 0.7393 0.0559
-4.500 0.0436 0.02255 0.01292 -0.1061 0.7294 0.0576
-4.250 0.0706 0.02183 0.01200 -0.1058 0.7201 0.0593
-4.000 0.0972 0.02118 0.01117 -0.1054 0.7107 0.0605
-3.750 0.1236 0.02049 0.01044 -0.1050 0.7022 0.0616
-3.500 0.1494 0.01995 0.00989 -0.1045 0.6934 0.0630
-3.250 0.1757 0.01949 0.00938 -0.1041 0.6851 0.0647
-3.000 0.2018 0.01912 0.00895 -0.1037 0.6769 0.0672
-2.750 0.2280 0.01880 0.00854 -0.1032 0.6687 0.0705
-2.500 0.2545 0.01850 0.00823 -0.1029 0.6612 0.0747
-2.250 0.2809 0.01825 0.00790 -0.1025 0.6528 0.0794
-2.000 0.3081 0.01800 0.00758 -0.1022 0.6461 0.0868
-1.750 0.3343 0.01773 0.00735 -0.1019 0.6377 0.1033
-1.500 0.3607 0.01720 0.00704 -0.1018 0.6306 0.1602
-1.250 0.3848 0.01632 0.00704 -0.1017 0.6234 0.3845
-1.000 0.4090 0.01621 0.00726 -0.1007 0.6158 0.5203
-0.750 0.4342 0.01626 0.00736 -0.0997 0.6094 0.5862
-0.500 0.4571 0.01633 0.00758 -0.0982 0.6013 0.6475
-0.250 0.4804 0.01635 0.00765 -0.0967 0.5946 0.6943
0.000 0.5048 0.01637 0.00770 -0.0956 0.5872 0.7245
0.250 0.5300 0.01638 0.00769 -0.0947 0.5796 0.7483
0.500 0.5562 0.01639 0.00763 -0.0941 0.5734 0.7711
0.750 0.5811 0.01639 0.00768 -0.0933 0.5652 0.7925
1.000 0.6074 0.01636 0.00761 -0.0927 0.5585 0.8173
1.250 0.6340 0.01632 0.00764 -0.0922 0.5506 0.8528
1.500 0.6748 0.01621 0.00756 -0.0946 0.5426 0.9871
1.750 0.7025 0.01642 0.00765 -0.0948 0.5355 1.0000
2.000 0.7298 0.01663 0.00776 -0.0949 0.5279 1.0000
2.250 0.7576 0.01682 0.00780 -0.0949 0.5216 1.0000
2.500 0.7837 0.01706 0.00801 -0.0947 0.5132 1.0000
2.750 0.8109 0.01725 0.00807 -0.0945 0.5068 1.0000
3.000 0.8366 0.01751 0.00830 -0.0942 0.4987 1.0000
3.250 0.8630 0.01772 0.00842 -0.0940 0.4917 1.0000
3.500 0.8887 0.01798 0.00863 -0.0936 0.4843 1.0000
3.750 0.9144 0.01821 0.00881 -0.0932 0.4766 1.0000
4.000 0.9398 0.01846 0.00900 -0.0928 0.4691 1.0000
4.250 0.9647 0.01872 0.00923 -0.0923 0.4611 1.0000
4.500 0.9903 0.01899 0.00943 -0.0919 0.4546 1.0000
4.750 1.0146 0.01931 0.00977 -0.0914 0.4469 1.0000
5.000 1.0401 0.01957 0.00994 -0.0910 0.4406 1.0000
5.250 1.0635 0.01993 0.01035 -0.0903 0.4325 1.0000
5.500 1.0880 0.02022 0.01059 -0.0898 0.4256 1.0000
5.750 1.1113 0.02059 0.01097 -0.0891 0.4181 1.0000
6.000 1.1347 0.02093 0.01132 -0.0885 0.4109 1.0000
6.250 1.1585 0.02129 0.01167 -0.0879 0.4047 1.0000
6.500 1.1811 0.02172 0.01216 -0.0871 0.3982 1.0000
6.750 1.2048 0.02210 0.01254 -0.0865 0.3927 1.0000
7.000 1.2272 0.02255 0.01304 -0.0858 0.3868 1.0000
7.250 1.2489 0.02301 0.01357 -0.0850 0.3805 1.0000
7.500 1.2721 0.02341 0.01396 -0.0843 0.3751 1.0000
7.750 1.2924 0.02394 0.01460 -0.0833 0.3688 1.0000
8.000 1.3129 0.02442 0.01515 -0.0824 0.3625 1.0000
8.250 1.3350 0.02486 0.01558 -0.0816 0.3570 1.0000
8.500 1.3521 0.02546 0.01634 -0.0802 0.3498 1.0000
8.750 1.3714 0.02595 0.01687 -0.0790 0.3435 1.0000
9.000 1.3892 0.02654 0.01753 -0.0777 0.3371 1.0000
9.250 1.4049 0.02716 0.01827 -0.0762 0.3301 1.0000
9.500 1.4233 0.02767 0.01876 -0.0749 0.3239 1.0000
9.750 1.4334 0.02843 0.01970 -0.0727 0.3160 1.0000
10.000 1.4458 0.02899 0.02025 -0.0706 0.3088 1.0000
10.250 1.4513 0.02986 0.02128 -0.0678 0.3003 1.0000
10.500 1.4603 0.03059 0.02200 -0.0656 0.2927 1.0000
10.750 1.4641 0.03167 0.02324 -0.0630 0.2843 1.0000
11.000 1.4713 0.03263 0.02421 -0.0609 0.2773 1.0000
11.250 1.4750 0.03394 0.02568 -0.0589 0.2699 1.0000
11.500 1.4802 0.03520 0.02700 -0.0570 0.2634 1.0000
11.750 1.4832 0.03674 0.02866 -0.0554 0.2566 1.0000
12.000 1.4851 0.03839 0.03039 -0.0538 0.2496 1.0000
12.250 1.4855 0.04030 0.03240 -0.0524 0.2426 1.0000
12.500 1.4853 0.04237 0.03455 -0.0513 0.2358 1.0000
12.750 1.4856 0.04455 0.03682 -0.0504 0.2297 1.0000
13.000 1.4845 0.04701 0.03941 -0.0497 0.2238 1.0000
13.250 1.4850 0.04930 0.04173 -0.0490 0.2184 1.0000
13.500 1.4798 0.05243 0.04503 -0.0488 0.2120 1.0000
13.750 1.4772 0.05521 0.04785 -0.0485 0.2060 1.0000
14.000 1.4709 0.05867 0.05144 -0.0485 0.2001 1.0000
14.250 1.4658 0.06202 0.05487 -0.0487 0.1942 1.0000
14.500 1.4618 0.06531 0.05822 -0.0488 0.1888 1.0000
14.750 1.4529 0.06945 0.06250 -0.0495 0.1830 1.0000
15.000 1.4510 0.07254 0.06559 -0.0497 0.1770 1.0000
15.250 1.4389 0.07747 0.07071 -0.0509 0.1712 1.0000
15.500 1.4313 0.08172 0.07503 -0.0519 0.1649 1.0000
15.750 1.4233 0.08618 0.07957 -0.0530 0.1586 1.0000
16.000 1.4094 0.09181 0.08536 -0.0549 0.1518 1.0000
16.250 1.4011 0.09652 0.09011 -0.0563 0.1448 1.0000
16.500 1.3836 0.10315 0.09694 -0.0589 0.1371 1.0000
16.750 1.3700 0.10916 0.10307 -0.0613 0.1291 1.0000
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