GOE 382 AIRFOIL (goe382-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 382 AIRFOIL (goe382-il) Reynolds number: 200,000 Max Cl/Cd: 59.48 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe382-il-200000-n5.txt Download as CSV file: xf-goe382-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 382 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 -0.1407 0.08641 0.08192 -0.0895 0.7799 0.0368
-11.000 -0.2965 0.05072 0.04573 -0.1181 0.7792 0.0356
-10.750 -0.3306 0.04495 0.03955 -0.1209 0.7671 0.0356
-10.500 -0.3517 0.04163 0.03586 -0.1193 0.7555 0.0357
-10.250 -0.3605 0.03863 0.03246 -0.1178 0.7452 0.0359
-10.000 -0.3608 0.03610 0.02951 -0.1162 0.7356 0.0361
-9.750 -0.3542 0.03398 0.02702 -0.1149 0.7268 0.0363
-9.500 -0.3432 0.03218 0.02487 -0.1136 0.7185 0.0364
-9.250 -0.3289 0.03062 0.02298 -0.1125 0.7111 0.0366
-9.000 -0.3116 0.02929 0.02140 -0.1115 0.7034 0.0367
-8.750 -0.2915 0.02819 0.02014 -0.1109 0.6966 0.0369
-8.500 -0.2704 0.02721 0.01904 -0.1103 0.6900 0.0372
-8.250 -0.2487 0.02631 0.01801 -0.1097 0.6833 0.0374
-8.000 -0.2265 0.02549 0.01702 -0.1091 0.6773 0.0377
-7.750 -0.2037 0.02470 0.01612 -0.1085 0.6714 0.0380
-7.500 -0.1804 0.02396 0.01526 -0.1080 0.6653 0.0383
-7.250 -0.1568 0.02329 0.01444 -0.1075 0.6598 0.0387
-7.000 -0.1327 0.02267 0.01369 -0.1070 0.6548 0.0393
-6.750 -0.1085 0.02207 0.01300 -0.1066 0.6495 0.0399
-6.500 -0.0839 0.02150 0.01231 -0.1061 0.6444 0.0404
-6.250 -0.0591 0.02097 0.01166 -0.1056 0.6398 0.0409
-6.000 -0.0344 0.02046 0.01108 -0.1052 0.6356 0.0412
-5.750 -0.0100 0.01997 0.01061 -0.1048 0.6308 0.0417
-5.500 0.0146 0.01956 0.01019 -0.1043 0.6260 0.0422
-5.250 0.0394 0.01919 0.00977 -0.1039 0.6216 0.0427
-5.000 0.0645 0.01885 0.00936 -0.1035 0.6176 0.0433
-4.750 0.0894 0.01853 0.00902 -0.1030 0.6133 0.0440
-4.500 0.1142 0.01822 0.00869 -0.1026 0.6085 0.0448
-4.250 0.1394 0.01795 0.00837 -0.1021 0.6041 0.0456
-4.000 0.1649 0.01772 0.00810 -0.1018 0.6000 0.0466
-3.750 0.1909 0.01755 0.00787 -0.1015 0.5961 0.0482
-3.500 0.2163 0.01735 0.00769 -0.1011 0.5913 0.0501
-3.250 0.2420 0.01719 0.00755 -0.1008 0.5865 0.0521
-3.000 0.2681 0.01705 0.00737 -0.1005 0.5822 0.0549
-2.750 0.2945 0.01694 0.00721 -0.1003 0.5782 0.0586
-2.500 0.3204 0.01682 0.00708 -0.0999 0.5736 0.0645
-2.250 0.3461 0.01670 0.00694 -0.0995 0.5685 0.0724
-2.000 0.3716 0.01654 0.00674 -0.0992 0.5638 0.0805
-1.750 0.3970 0.01632 0.00652 -0.0988 0.5597 0.0912
-1.500 0.4213 0.01603 0.00649 -0.0985 0.5553 0.1457
-1.250 0.4465 0.01593 0.00645 -0.0981 0.5499 0.1691
-1.000 0.4718 0.01582 0.00639 -0.0977 0.5447 0.1905
-0.750 0.4970 0.01567 0.00633 -0.0974 0.5403 0.2255
-0.500 0.5213 0.01550 0.00636 -0.0970 0.5354 0.2847
-0.250 0.5453 0.01532 0.00639 -0.0965 0.5300 0.3461
0.000 0.5685 0.01506 0.00638 -0.0959 0.5249 0.4243
0.250 0.5896 0.01473 0.00647 -0.0947 0.5205 0.5678
0.500 0.6123 0.01463 0.00661 -0.0938 0.5146 0.6371
0.750 0.6348 0.01454 0.00672 -0.0926 0.5091 0.6980
1.000 0.6575 0.01450 0.00681 -0.0914 0.5045 0.7569
1.250 0.6813 0.01454 0.00696 -0.0905 0.4994 0.8042
1.500 0.7068 0.01463 0.00712 -0.0898 0.4936 0.8516
1.750 0.7379 0.01477 0.00725 -0.0903 0.4880 0.8980
2.000 0.7732 0.01496 0.00740 -0.0919 0.4826 0.9335
2.250 0.8101 0.01516 0.00757 -0.0940 0.4766 0.9599
2.500 0.8483 0.01539 0.00770 -0.0964 0.4712 0.9805
2.750 0.8912 0.01563 0.00785 -0.0999 0.4660 0.9962
3.000 0.9150 0.01582 0.00800 -0.0995 0.4605 1.0000
3.250 0.9304 0.01600 0.00811 -0.0975 0.4556 1.0000
3.500 0.9470 0.01620 0.00821 -0.0956 0.4512 1.0000
3.750 0.9643 0.01641 0.00838 -0.0939 0.4468 1.0000
4.000 0.9820 0.01664 0.00858 -0.0923 0.4424 1.0000
4.250 1.0001 0.01688 0.00877 -0.0909 0.4381 1.0000
4.500 1.0180 0.01714 0.00894 -0.0893 0.4341 1.0000
4.750 1.0355 0.01741 0.00918 -0.0878 0.4301 1.0000
5.000 1.0526 0.01770 0.00947 -0.0862 0.4256 1.0000
5.250 1.0705 0.01801 0.00975 -0.0848 0.4214 1.0000
5.500 1.0894 0.01834 0.01002 -0.0837 0.4177 1.0000
5.750 1.1094 0.01869 0.01030 -0.0827 0.4144 1.0000
6.000 1.1278 0.01906 0.01071 -0.0816 0.4107 1.0000
6.250 1.1462 0.01946 0.01111 -0.0805 0.4068 1.0000
6.500 1.1648 0.01986 0.01150 -0.0795 0.4031 1.0000
6.750 1.1840 0.02028 0.01186 -0.0786 0.3996 1.0000
7.000 1.2036 0.02071 0.01225 -0.0778 0.3963 1.0000
7.250 1.2205 0.02121 0.01281 -0.0767 0.3927 1.0000
7.500 1.2380 0.02172 0.01335 -0.0757 0.3892 1.0000
7.750 1.2559 0.02223 0.01386 -0.0748 0.3860 1.0000
8.000 1.2746 0.02273 0.01434 -0.0740 0.3830 1.0000
8.250 1.2949 0.02320 0.01476 -0.0734 0.3801 1.0000
8.500 1.3101 0.02385 0.01548 -0.0723 0.3768 1.0000
8.750 1.3245 0.02455 0.01624 -0.0711 0.3733 1.0000
9.000 1.3399 0.02523 0.01696 -0.0701 0.3699 1.0000
9.250 1.3565 0.02587 0.01761 -0.0693 0.3670 1.0000
9.500 1.3746 0.02647 0.01819 -0.0686 0.3644 1.0000
9.750 1.3937 0.02705 0.01875 -0.0681 0.3618 1.0000
10.000 1.4047 0.02801 0.01983 -0.0668 0.3588 1.0000
10.250 1.4164 0.02897 0.02087 -0.0657 0.3554 1.0000
10.500 1.4288 0.02990 0.02185 -0.0647 0.3522 1.0000
10.750 1.4432 0.03074 0.02271 -0.0639 0.3493 1.0000
11.000 1.4602 0.03144 0.02341 -0.0633 0.3469 1.0000
11.250 1.4767 0.03220 0.02418 -0.0627 0.3444 1.0000
11.500 1.4826 0.03363 0.02574 -0.0614 0.3412 1.0000
11.750 1.4894 0.03503 0.02723 -0.0603 0.3376 1.0000
12.000 1.4977 0.03633 0.02861 -0.0593 0.3341 1.0000
12.250 1.5102 0.03734 0.02960 -0.0586 0.3306 1.0000
12.500 1.5205 0.03854 0.03082 -0.0578 0.3268 1.0000
12.750 1.5178 0.04084 0.03328 -0.0565 0.3220 1.0000
13.000 1.5201 0.04279 0.03530 -0.0555 0.3170 1.0000
13.250 1.5308 0.04400 0.03647 -0.0549 0.3127 1.0000
13.500 1.5304 0.04637 0.03895 -0.0541 0.3082 1.0000
13.750 1.5291 0.04889 0.04160 -0.0533 0.3037 1.0000
14.000 1.5337 0.05087 0.04364 -0.0528 0.3000 1.0000
14.250 1.5440 0.05225 0.04502 -0.0524 0.2968 1.0000
14.500 1.5469 0.05447 0.04732 -0.0519 0.2933 1.0000
14.750 1.5408 0.05773 0.05074 -0.0513 0.2891 1.0000
15.000 1.5403 0.06038 0.05348 -0.0509 0.2849 1.0000
15.250 1.5478 0.06212 0.05522 -0.0506 0.2809 1.0000
15.500 1.5431 0.06533 0.05853 -0.0503 0.2764 1.0000
15.750 1.5316 0.06942 0.06277 -0.0500 0.2711 1.0000
16.000 1.5331 0.07195 0.06531 -0.0499 0.2660 1.0000
16.250 1.5267 0.07550 0.06895 -0.0498 0.2609 1.0000
16.500 1.5114 0.08025 0.07383 -0.0498 0.2547 1.0000
16.750 1.5155 0.08253 0.07609 -0.0499 0.2492 1.0000
17.000 1.4933 0.08836 0.08209 -0.0501 0.2429 1.0000
17.250 1.4850 0.09235 0.08613 -0.0504 0.2365 1.0000
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