GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 100,000 Max Cl/Cd: 55.99 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe532-il-100000-n5.txt Download as CSV file: xf-goe532-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 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 -0.2650 0.09635 0.09148 -0.0366 1.0000 0.0808
-8.500 -0.2940 0.09463 0.08994 -0.0384 1.0000 0.0831
-8.250 -0.3095 0.09163 0.08705 -0.0425 0.9928 0.0835
-7.750 -0.2791 0.07463 0.06995 -0.0551 0.9705 0.0554
-7.500 -0.2583 0.06958 0.06485 -0.0616 0.9583 0.0543
-7.250 -0.2384 0.06311 0.05831 -0.0708 0.9445 0.0539
-7.000 -0.2189 0.05589 0.05091 -0.0802 0.9299 0.0530
-6.750 -0.2006 0.04872 0.04342 -0.0884 0.9149 0.0517
-6.500 -0.1805 0.04235 0.03655 -0.0945 0.9005 0.0507
-6.250 -0.1558 0.03768 0.03134 -0.0983 0.8873 0.0503
-6.000 -0.1275 0.03471 0.02796 -0.1006 0.8747 0.0513
-5.750 -0.1015 0.03221 0.02503 -0.1018 0.8594 0.0522
-5.500 -0.0746 0.02996 0.02234 -0.1025 0.8444 0.0526
-5.250 -0.0468 0.02806 0.02004 -0.1030 0.8294 0.0528
-5.000 -0.0188 0.02645 0.01804 -0.1032 0.8143 0.0532
-4.750 0.0091 0.02508 0.01632 -0.1031 0.7985 0.0536
-4.500 0.0368 0.02396 0.01484 -0.1028 0.7818 0.0545
-4.250 0.0634 0.02296 0.01366 -0.1024 0.7644 0.0558
-4.000 0.0900 0.02214 0.01274 -0.1020 0.7469 0.0571
-3.750 0.1168 0.02138 0.01183 -0.1016 0.7300 0.0582
-3.500 0.1437 0.02068 0.01098 -0.1010 0.7138 0.0591
-3.250 0.1706 0.02005 0.01022 -0.1005 0.6984 0.0602
-3.000 0.1973 0.01951 0.00954 -0.0999 0.6838 0.0615
-2.750 0.2241 0.01907 0.00896 -0.0993 0.6704 0.0633
-2.500 0.2502 0.01859 0.00847 -0.0988 0.6579 0.0659
-2.250 0.2764 0.01826 0.00808 -0.0983 0.6459 0.0689
-2.000 0.3032 0.01799 0.00767 -0.0978 0.6359 0.0715
-1.750 0.3297 0.01769 0.00731 -0.0973 0.6259 0.0747
-1.500 0.3567 0.01747 0.00700 -0.0970 0.6172 0.0799
-1.250 0.3834 0.01723 0.00674 -0.0966 0.6079 0.0896
-1.000 0.4102 0.01691 0.00648 -0.0962 0.5995 0.1141
-0.750 0.4354 0.01615 0.00647 -0.0961 0.5903 0.3119
-0.500 0.4608 0.01584 0.00658 -0.0955 0.5826 0.4683
-0.250 0.4852 0.01565 0.00674 -0.0944 0.5742 0.5776
0.000 0.5072 0.01539 0.00682 -0.0925 0.5671 0.7085
0.250 0.5476 0.01484 0.00670 -0.0940 0.5580 1.0000
0.500 0.5751 0.01503 0.00667 -0.0938 0.5504 1.0000
0.750 0.6023 0.01524 0.00671 -0.0936 0.5432 1.0000
1.000 0.6292 0.01545 0.00677 -0.0933 0.5358 1.0000
1.250 0.6566 0.01567 0.00679 -0.0930 0.5298 1.0000
1.500 0.6830 0.01588 0.00694 -0.0927 0.5225 1.0000
1.750 0.7097 0.01610 0.00704 -0.0923 0.5158 1.0000
2.000 0.7366 0.01633 0.00714 -0.0920 0.5101 1.0000
2.250 0.7627 0.01656 0.00733 -0.0916 0.5031 1.0000
2.500 0.7892 0.01678 0.00746 -0.0912 0.4969 1.0000
2.750 0.8155 0.01703 0.00763 -0.0908 0.4908 1.0000
3.000 0.8411 0.01726 0.00784 -0.0903 0.4835 1.0000
3.250 0.8672 0.01747 0.00794 -0.0898 0.4766 1.0000
3.500 0.8920 0.01771 0.00820 -0.0892 0.4683 1.0000
3.750 0.9176 0.01794 0.00839 -0.0887 0.4615 1.0000
4.000 0.9431 0.01821 0.00863 -0.0882 0.4554 1.0000
4.250 0.9680 0.01847 0.00892 -0.0876 0.4483 1.0000
4.500 0.9934 0.01872 0.00912 -0.0870 0.4420 1.0000
4.750 1.0175 0.01899 0.00945 -0.0863 0.4337 1.0000
5.000 1.0417 0.01923 0.00966 -0.0856 0.4253 1.0000
5.250 1.0650 0.01950 0.00999 -0.0848 0.4153 1.0000
5.500 1.0881 0.01974 0.01018 -0.0839 0.4052 1.0000
5.750 1.1102 0.02002 0.01051 -0.0829 0.3923 1.0000
6.000 1.1318 0.02030 0.01083 -0.0818 0.3786 1.0000
6.250 1.1530 0.02062 0.01116 -0.0807 0.3642 1.0000
6.500 1.1736 0.02096 0.01151 -0.0795 0.3485 1.0000
6.750 1.1935 0.02135 0.01189 -0.0782 0.3315 1.0000
7.000 1.2124 0.02180 0.01231 -0.0769 0.3134 1.0000
7.250 1.2299 0.02232 0.01276 -0.0753 0.2960 1.0000
7.500 1.2462 0.02292 0.01328 -0.0736 0.2806 1.0000
7.750 1.2616 0.02360 0.01390 -0.0719 0.2677 1.0000
8.000 1.2762 0.02432 0.01457 -0.0701 0.2574 1.0000
8.250 1.2895 0.02509 0.01530 -0.0682 0.2488 1.0000
8.500 1.3027 0.02584 0.01606 -0.0662 0.2412 1.0000
8.750 1.3131 0.02667 0.01687 -0.0639 0.2347 1.0000
9.000 1.3246 0.02749 0.01772 -0.0618 0.2290 1.0000
9.250 1.3358 0.02836 0.01863 -0.0598 0.2237 1.0000
9.500 1.3445 0.02937 0.01963 -0.0577 0.2186 1.0000
9.750 1.3553 0.03033 0.02067 -0.0559 0.2135 1.0000
10.000 1.3649 0.03138 0.02180 -0.0541 0.2085 1.0000
10.250 1.3732 0.03255 0.02298 -0.0524 0.2042 1.0000
10.500 1.3824 0.03374 0.02422 -0.0508 0.2001 1.0000
10.750 1.3906 0.03501 0.02562 -0.0494 0.1949 1.0000
11.000 1.3967 0.03647 0.02714 -0.0479 0.1899 1.0000
11.250 1.4027 0.03801 0.02869 -0.0465 0.1852 1.0000
11.500 1.4088 0.03962 0.03047 -0.0454 0.1800 1.0000
11.750 1.4128 0.04143 0.03236 -0.0444 0.1748 1.0000
12.000 1.4168 0.04329 0.03421 -0.0433 0.1701 1.0000
12.250 1.4204 0.04535 0.03649 -0.0427 0.1647 1.0000
12.500 1.4221 0.04763 0.03889 -0.0421 0.1592 1.0000
12.750 1.4230 0.04999 0.04125 -0.0415 0.1544 1.0000
13.000 1.4237 0.05263 0.04412 -0.0414 0.1481 1.0000
13.250 1.4221 0.05552 0.04712 -0.0413 0.1422 1.0000
13.500 1.4211 0.05846 0.05019 -0.0414 0.1365 1.0000
13.750 1.4195 0.06159 0.05347 -0.0417 0.1304 1.0000
14.000 1.4172 0.06485 0.05682 -0.0421 0.1255 1.0000
14.250 1.4155 0.06817 0.06027 -0.0425 0.1203 1.0000
14.500 1.4125 0.07168 0.06383 -0.0432 0.1167 1.0000
14.750 1.4114 0.07505 0.06730 -0.0438 0.1132 1.0000
15.000 1.4090 0.07865 0.07099 -0.0446 0.1102 1.0000
15.250 1.4057 0.08243 0.07483 -0.0455 0.1077 1.0000
15.500 1.4032 0.08614 0.07859 -0.0465 0.1055 1.0000
15.750 1.4012 0.08988 0.08244 -0.0475 0.1033 1.0000
16.000 1.3988 0.09372 0.08637 -0.0486 0.1013 1.0000
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Polar data table (+)
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