GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 200,000 Max Cl/Cd: 64.93 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe655-il-200000-n5.txt Download as CSV file: xf-goe655-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3612 0.09654 0.09285 -0.0478 1.0000 0.0298
-11.000 -0.3620 0.09401 0.09036 -0.0477 1.0000 0.0300
-10.500 -0.5965 0.04586 0.04174 -0.0811 0.9878 0.0301
-10.250 -0.5716 0.04423 0.04007 -0.0841 0.9831 0.0307
-10.000 -0.5585 0.04132 0.03695 -0.0866 0.9750 0.0313
-9.750 -0.5448 0.03821 0.03354 -0.0888 0.9677 0.0321
-9.500 -0.5296 0.03472 0.02961 -0.0908 0.9608 0.0330
-9.250 -0.5151 0.03173 0.02612 -0.0914 0.9529 0.0342
-9.000 -0.4924 0.02937 0.02334 -0.0925 0.9472 0.0353
-8.750 -0.4600 0.02811 0.02200 -0.0944 0.9441 0.0361
-8.500 -0.4383 0.02704 0.02080 -0.0939 0.9354 0.0368
-8.250 -0.4081 0.02581 0.01939 -0.0951 0.9304 0.0378
-8.000 -0.3824 0.02467 0.01804 -0.0952 0.9230 0.0390
-7.750 -0.3552 0.02347 0.01657 -0.0955 0.9157 0.0401
-7.500 -0.3251 0.02231 0.01512 -0.0962 0.9099 0.0410
-7.250 -0.3006 0.02127 0.01401 -0.0958 0.9004 0.0418
-7.000 -0.2688 0.02043 0.01314 -0.0968 0.8944 0.0429
-6.750 -0.2439 0.01980 0.01244 -0.0963 0.8838 0.0440
-6.500 -0.2147 0.01908 0.01162 -0.0965 0.8755 0.0453
-6.250 -0.1868 0.01836 0.01078 -0.0964 0.8648 0.0464
-6.000 -0.1600 0.01772 0.01001 -0.0961 0.8523 0.0475
-5.750 -0.1325 0.01713 0.00928 -0.0958 0.8381 0.0486
-5.500 -0.1061 0.01646 0.00859 -0.0954 0.8216 0.0502
-5.250 -0.0794 0.01600 0.00805 -0.0950 0.8054 0.0519
-5.000 -0.0529 0.01558 0.00753 -0.0946 0.7910 0.0537
-4.750 -0.0265 0.01519 0.00703 -0.0941 0.7788 0.0555
-4.500 -0.0006 0.01484 0.00657 -0.0935 0.7665 0.0574
-4.250 0.0243 0.01445 0.00614 -0.0929 0.7544 0.0600
-4.000 0.0501 0.01419 0.00579 -0.0923 0.7427 0.0636
-3.500 0.1009 0.01367 0.00514 -0.0910 0.7195 0.0735
-3.250 0.1264 0.01345 0.00486 -0.0904 0.7088 0.0811
-3.000 0.1517 0.01320 0.00461 -0.0898 0.6978 0.0955
-2.750 0.1760 0.01290 0.00442 -0.0891 0.6859 0.1275
-2.500 0.2006 0.01266 0.00429 -0.0884 0.6739 0.1712
-2.250 0.2253 0.01248 0.00418 -0.0877 0.6616 0.2116
-2.000 0.2500 0.01234 0.00410 -0.0869 0.6484 0.2486
-1.750 0.2746 0.01222 0.00404 -0.0862 0.6352 0.2850
-1.500 0.2992 0.01211 0.00398 -0.0854 0.6217 0.3204
-1.250 0.3233 0.01201 0.00394 -0.0845 0.6076 0.3590
-1.000 0.3467 0.01189 0.00392 -0.0835 0.5928 0.4099
-0.750 0.3695 0.01176 0.00390 -0.0824 0.5773 0.4643
-0.500 0.3922 0.01168 0.00388 -0.0812 0.5613 0.5111
-0.250 0.4145 0.01160 0.00387 -0.0800 0.5451 0.5583
0.000 0.4354 0.01146 0.00390 -0.0783 0.5297 0.6286
0.250 0.4560 0.01128 0.00397 -0.0764 0.5149 0.7314
0.500 0.4936 0.01121 0.00411 -0.0779 0.4988 0.8618
0.750 0.5594 0.01140 0.00420 -0.0856 0.4800 0.9576
1.000 0.6056 0.01162 0.00425 -0.0895 0.4645 0.9919
1.250 0.6332 0.01183 0.00433 -0.0895 0.4513 1.0000
1.500 0.6541 0.01202 0.00440 -0.0881 0.4389 1.0000
1.750 0.6746 0.01224 0.00449 -0.0867 0.4264 1.0000
2.000 0.6950 0.01247 0.00458 -0.0852 0.4153 1.0000
2.250 0.7166 0.01267 0.00470 -0.0839 0.4053 1.0000
2.500 0.7379 0.01290 0.00482 -0.0826 0.3975 1.0000
2.750 0.7600 0.01310 0.00496 -0.0815 0.3902 1.0000
3.000 0.7814 0.01334 0.00511 -0.0803 0.3837 1.0000
3.250 0.8040 0.01354 0.00526 -0.0792 0.3770 1.0000
3.500 0.8258 0.01378 0.00543 -0.0780 0.3701 1.0000
3.750 0.8477 0.01403 0.00561 -0.0769 0.3642 1.0000
4.000 0.8703 0.01424 0.00580 -0.0759 0.3583 1.0000
4.250 0.8926 0.01449 0.00600 -0.0749 0.3535 1.0000
4.500 0.9146 0.01476 0.00622 -0.0738 0.3490 1.0000
4.750 0.9374 0.01497 0.00644 -0.0729 0.3436 1.0000
5.000 0.9594 0.01522 0.00667 -0.0718 0.3382 1.0000
5.250 0.9806 0.01553 0.00691 -0.0707 0.3336 1.0000
5.500 1.0033 0.01575 0.00716 -0.0698 0.3289 1.0000
5.750 1.0253 0.01600 0.00742 -0.0688 0.3240 1.0000
6.000 1.0465 0.01629 0.00769 -0.0676 0.3195 1.0000
6.250 1.0676 0.01659 0.00797 -0.0665 0.3154 1.0000
6.500 1.0896 0.01684 0.00828 -0.0655 0.3109 1.0000
6.750 1.1103 0.01712 0.00858 -0.0643 0.3060 1.0000
7.000 1.1299 0.01744 0.00889 -0.0630 0.3016 1.0000
7.250 1.1502 0.01773 0.00922 -0.0617 0.2970 1.0000
7.500 1.1693 0.01801 0.00955 -0.0603 0.2917 1.0000
7.750 1.1862 0.01834 0.00988 -0.0585 0.2862 1.0000
8.000 1.2039 0.01866 0.01025 -0.0568 0.2808 1.0000
8.250 1.2209 0.01898 0.01063 -0.0551 0.2742 1.0000
8.500 1.2360 0.01938 0.01102 -0.0531 0.2680 1.0000
8.750 1.2535 0.01973 0.01145 -0.0516 0.2611 1.0000
9.000 1.2678 0.02019 0.01191 -0.0496 0.2544 1.0000
9.250 1.2841 0.02061 0.01241 -0.0480 0.2466 1.0000
9.500 1.2971 0.02116 0.01295 -0.0460 0.2394 1.0000
9.750 1.3121 0.02167 0.01353 -0.0444 0.2313 1.0000
10.000 1.3242 0.02232 0.01418 -0.0424 0.2240 1.0000
10.250 1.3369 0.02298 0.01489 -0.0406 0.2164 1.0000
10.500 1.3474 0.02376 0.01567 -0.0386 0.2099 1.0000
10.750 1.3575 0.02461 0.01653 -0.0368 0.2020 1.0000
11.000 1.3659 0.02558 0.01750 -0.0348 0.1957 1.0000
11.250 1.3749 0.02658 0.01852 -0.0331 0.1894 1.0000
11.500 1.3803 0.02782 0.01975 -0.0311 0.1841 1.0000
11.750 1.3909 0.02884 0.02085 -0.0297 0.1796 1.0000
12.000 1.3989 0.03005 0.02211 -0.0283 0.1755 1.0000
12.250 1.4047 0.03144 0.02352 -0.0268 0.1718 1.0000
12.500 1.4115 0.03283 0.02496 -0.0255 0.1686 1.0000
12.750 1.4205 0.03412 0.02637 -0.0244 0.1647 1.0000
13.000 1.4270 0.03563 0.02795 -0.0233 0.1612 1.0000
13.250 1.4305 0.03741 0.02978 -0.0223 0.1577 1.0000
13.500 1.4342 0.03924 0.03165 -0.0213 0.1549 1.0000
13.750 1.4420 0.04082 0.03339 -0.0207 0.1508 1.0000
14.000 1.4465 0.04271 0.03539 -0.0200 0.1470 1.0000
14.250 1.4465 0.04507 0.03781 -0.0194 0.1429 1.0000
14.500 1.4487 0.04733 0.04015 -0.0190 0.1392 1.0000
14.750 1.4531 0.04945 0.04243 -0.0188 0.1351 1.0000
15.000 1.4521 0.05220 0.04526 -0.0187 0.1302 1.0000
15.250 1.4504 0.05513 0.04829 -0.0188 0.1255 1.0000
15.500 1.4493 0.05815 0.05143 -0.0190 0.1186 1.0000
15.750 1.4442 0.06171 0.05508 -0.0195 0.1118 1.0000
16.000 1.4354 0.06588 0.05931 -0.0203 0.1022 1.0000
16.250 1.4201 0.07106 0.06451 -0.0215 0.0885 1.0000
16.500 1.3960 0.07763 0.07105 -0.0234 0.0731 1.0000
16.750 1.3709 0.08456 0.07795 -0.0255 0.0606 1.0000
17.000 1.3452 0.09180 0.08521 -0.0279 0.0497 1.0000
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