GOE 367 AIRFOIL (goe367-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 367 AIRFOIL (goe367-il) Reynolds number: 500,000 Max Cl/Cd: 83.71 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe367-il-500000-n5.txt Download as CSV file: xf-goe367-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 367 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8298 0.04997 0.04633 -0.1049 1.0000 0.0301
-15.000 -0.8531 0.04181 0.03786 -0.1136 0.9903 0.0301
-14.750 -0.8579 0.03759 0.03339 -0.1173 0.9795 0.0302
-14.500 -0.8577 0.03477 0.03039 -0.1184 0.9687 0.0304
-14.250 -0.8554 0.03282 0.02832 -0.1179 0.9571 0.0305
-14.000 -0.8515 0.03130 0.02669 -0.1165 0.9460 0.0307
-13.750 -0.8460 0.03005 0.02532 -0.1147 0.9356 0.0309
-13.500 -0.8390 0.02897 0.02414 -0.1127 0.9249 0.0310
-13.250 -0.8306 0.02808 0.02314 -0.1106 0.9150 0.0312
-13.000 -0.8193 0.02728 0.02223 -0.1087 0.9056 0.0315
-12.750 -0.8046 0.02650 0.02135 -0.1073 0.8968 0.0317
-12.500 -0.7891 0.02572 0.02046 -0.1060 0.8886 0.0320
-12.250 -0.7724 0.02493 0.01955 -0.1048 0.8808 0.0323
-12.000 -0.7552 0.02413 0.01861 -0.1037 0.8729 0.0326
-11.750 -0.7370 0.02334 0.01768 -0.1026 0.8658 0.0329
-11.500 -0.7179 0.02258 0.01679 -0.1017 0.8579 0.0332
-11.250 -0.6981 0.02186 0.01592 -0.1007 0.8509 0.0335
-11.000 -0.6772 0.02117 0.01510 -0.0999 0.8439 0.0338
-10.750 -0.6557 0.02053 0.01432 -0.0992 0.8373 0.0342
-10.500 -0.6335 0.01995 0.01359 -0.0985 0.8314 0.0344
-10.250 -0.6114 0.01930 0.01286 -0.0979 0.8248 0.0347
-10.000 -0.5888 0.01874 0.01223 -0.0972 0.8185 0.0351
-9.750 -0.5651 0.01827 0.01170 -0.0967 0.8130 0.0355
-9.500 -0.5409 0.01784 0.01121 -0.0963 0.8069 0.0358
-9.250 -0.5165 0.01746 0.01075 -0.0958 0.8000 0.0363
-9.000 -0.4917 0.01710 0.01031 -0.0954 0.7930 0.0368
-8.750 -0.4668 0.01672 0.00986 -0.0950 0.7857 0.0374
-8.500 -0.4418 0.01635 0.00939 -0.0946 0.7799 0.0379
-8.250 -0.4164 0.01597 0.00893 -0.0943 0.7747 0.0384
-8.000 -0.3907 0.01561 0.00850 -0.0940 0.7694 0.0389
-7.750 -0.3650 0.01528 0.00808 -0.0937 0.7642 0.0393
-7.500 -0.3399 0.01486 0.00763 -0.0933 0.7597 0.0399
-7.250 -0.3139 0.01454 0.00729 -0.0931 0.7548 0.0405
-7.000 -0.2876 0.01426 0.00697 -0.0929 0.7498 0.0412
-6.750 -0.2613 0.01400 0.00666 -0.0927 0.7452 0.0419
-6.500 -0.2347 0.01375 0.00636 -0.0925 0.7408 0.0427
-6.250 -0.2079 0.01351 0.00608 -0.0923 0.7360 0.0436
-6.000 -0.1810 0.01330 0.00582 -0.0922 0.7312 0.0444
-5.750 -0.1549 0.01301 0.00550 -0.0919 0.7267 0.0454
-5.500 -0.1283 0.01277 0.00525 -0.0917 0.7222 0.0463
-5.250 -0.1013 0.01256 0.00502 -0.0916 0.7173 0.0474
-5.000 -0.0744 0.01237 0.00480 -0.0915 0.7123 0.0486
-4.750 -0.0474 0.01221 0.00458 -0.0913 0.7075 0.0497
-4.500 -0.0203 0.01202 0.00438 -0.0912 0.7026 0.0509
-4.250 0.0065 0.01180 0.00417 -0.0910 0.6971 0.0526
-4.000 0.0334 0.01165 0.00398 -0.0908 0.6914 0.0544
-3.750 0.0604 0.01151 0.00382 -0.0907 0.6851 0.0562
-3.500 0.0872 0.01136 0.00364 -0.0905 0.6768 0.0582
-3.250 0.1137 0.01122 0.00348 -0.0902 0.6686 0.0608
-3.000 0.1407 0.01110 0.00335 -0.0901 0.6601 0.0638
-2.750 0.1672 0.01098 0.00322 -0.0898 0.6530 0.0688
-2.500 0.1943 0.01085 0.00314 -0.0897 0.6458 0.0772
-2.250 0.2210 0.01076 0.00308 -0.0895 0.6380 0.0897
-2.000 0.2480 0.01070 0.00303 -0.0894 0.6298 0.1001
-1.750 0.2747 0.01066 0.00298 -0.0892 0.6203 0.1081
-1.500 0.3016 0.01064 0.00294 -0.0890 0.6107 0.1150
-1.250 0.3279 0.01062 0.00290 -0.0887 0.6010 0.1207
-1.000 0.3547 0.01060 0.00287 -0.0886 0.5910 0.1268
-0.750 0.3810 0.01063 0.00284 -0.0883 0.5813 0.1317
-0.500 0.4071 0.01062 0.00283 -0.0880 0.5708 0.1382
-0.250 0.4331 0.01064 0.00282 -0.0877 0.5607 0.1443
0.000 0.4586 0.01068 0.00282 -0.0873 0.5502 0.1514
0.250 0.4846 0.01069 0.00283 -0.0870 0.5406 0.1603
0.500 0.5097 0.01072 0.00286 -0.0865 0.5314 0.1721
0.750 0.5356 0.01068 0.00288 -0.0863 0.5233 0.1952
1.000 0.5592 0.01051 0.00293 -0.0857 0.5152 0.2777
1.250 0.5791 0.00986 0.00297 -0.0846 0.5083 0.5121
1.500 0.5878 0.00901 0.00327 -0.0803 0.5013 0.8636
1.750 0.6094 0.00918 0.00344 -0.0787 0.4933 0.9028
2.000 0.6323 0.00933 0.00357 -0.0776 0.4841 0.9201
2.250 0.6549 0.00952 0.00371 -0.0764 0.4742 0.9326
2.500 0.6780 0.00970 0.00384 -0.0754 0.4636 0.9424
2.750 0.7010 0.00986 0.00395 -0.0743 0.4543 0.9515
3.000 0.7266 0.01008 0.00410 -0.0739 0.4441 0.9592
3.250 0.7511 0.01025 0.00423 -0.0733 0.4341 0.9671
3.500 0.7803 0.01048 0.00439 -0.0738 0.4240 0.9710
3.750 0.8095 0.01066 0.00453 -0.0743 0.4150 0.9745
4.000 0.8371 0.01089 0.00470 -0.0745 0.4074 0.9799
4.250 0.8714 0.01110 0.00488 -0.0762 0.3995 0.9831
4.500 0.9090 0.01139 0.00511 -0.0786 0.3916 0.9865
4.750 0.9473 0.01163 0.00533 -0.0812 0.3843 0.9904
5.000 0.9742 0.01187 0.00553 -0.0814 0.3776 0.9928
5.250 1.0022 0.01209 0.00572 -0.0818 0.3707 0.9942
5.500 1.0285 0.01235 0.00593 -0.0820 0.3613 0.9961
5.750 1.0537 0.01261 0.00616 -0.0819 0.3540 0.9984
6.000 1.0706 0.01279 0.00634 -0.0801 0.3483 1.0000
6.250 1.0712 0.01293 0.00648 -0.0749 0.3441 1.0000
6.500 1.0780 0.01313 0.00666 -0.0710 0.3400 1.0000
6.750 1.0937 0.01334 0.00688 -0.0690 0.3356 1.0000
7.000 1.1110 0.01360 0.00714 -0.0674 0.3307 1.0000
7.250 1.1284 0.01394 0.00746 -0.0659 0.3257 1.0000
7.500 1.1474 0.01426 0.00778 -0.0647 0.3215 1.0000
7.750 1.1679 0.01455 0.00810 -0.0638 0.3172 1.0000
8.000 1.1873 0.01491 0.00846 -0.0628 0.3126 1.0000
8.250 1.2057 0.01534 0.00888 -0.0616 0.3080 1.0000
8.500 1.2255 0.01572 0.00928 -0.0608 0.3040 1.0000
8.750 1.2456 0.01610 0.00969 -0.0599 0.2993 1.0000
9.000 1.2641 0.01656 0.01016 -0.0590 0.2940 1.0000
9.250 1.2816 0.01710 0.01070 -0.0579 0.2884 1.0000
9.500 1.2998 0.01761 0.01122 -0.0569 0.2800 1.0000
9.750 1.3150 0.01830 0.01189 -0.0557 0.2697 1.0000
10.000 1.3278 0.01915 0.01268 -0.0542 0.2532 1.0000
10.250 1.3299 0.02066 0.01400 -0.0516 0.2161 1.0000
10.500 1.3206 0.02301 0.01607 -0.0479 0.1726 1.0000
10.750 1.3256 0.02451 0.01752 -0.0460 0.1593 1.0000
11.000 1.3339 0.02585 0.01884 -0.0445 0.1495 1.0000
11.250 1.3432 0.02714 0.02013 -0.0431 0.1404 1.0000
11.500 1.3494 0.02868 0.02165 -0.0416 0.1268 1.0000
11.750 1.3450 0.03109 0.02389 -0.0394 0.0967 1.0000
12.000 1.3468 0.03310 0.02586 -0.0379 0.0879 1.0000
12.250 1.3538 0.03476 0.02755 -0.0368 0.0849 1.0000
12.500 1.3604 0.03650 0.02932 -0.0358 0.0824 1.0000
12.750 1.3656 0.03841 0.03127 -0.0348 0.0800 1.0000
13.000 1.3723 0.04022 0.03314 -0.0340 0.0781 1.0000
13.250 1.3798 0.04199 0.03498 -0.0332 0.0766 1.0000
13.500 1.3853 0.04400 0.03704 -0.0325 0.0749 1.0000
13.750 1.3890 0.04624 0.03934 -0.0318 0.0732 1.0000
14.000 1.3910 0.04868 0.04184 -0.0311 0.0717 1.0000
14.250 1.3912 0.05135 0.04458 -0.0305 0.0702 1.0000
14.500 1.3987 0.05332 0.04663 -0.0301 0.0690 1.0000
14.750 1.4040 0.05555 0.04894 -0.0298 0.0675 1.0000
15.000 1.4078 0.05799 0.05145 -0.0295 0.0658 1.0000
15.250 1.4093 0.06070 0.05423 -0.0293 0.0642 1.0000
15.500 1.4084 0.06374 0.05732 -0.0290 0.0626 1.0000
15.750 1.4115 0.06634 0.06000 -0.0290 0.0611 1.0000
16.000 1.4154 0.06887 0.06260 -0.0289 0.0591 1.0000
16.250 1.4167 0.07174 0.06553 -0.0289 0.0568 1.0000
16.500 1.4158 0.07491 0.06875 -0.0290 0.0548 1.0000
16.750 1.4180 0.07769 0.07161 -0.0291 0.0522 1.0000
17.000 1.4174 0.08084 0.07480 -0.0293 0.0494 1.0000
17.250 1.4161 0.08412 0.07813 -0.0295 0.0466 1.0000
17.500 1.4143 0.08748 0.08152 -0.0299 0.0436 1.0000
17.750 1.4113 0.09102 0.08511 -0.0303 0.0412 1.0000
18.000 1.4077 0.09465 0.08879 -0.0307 0.0389 1.0000
18.250 1.4043 0.09826 0.09244 -0.0313 0.0370 1.0000
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