GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 100,000 Max Cl/Cd: 47.2 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe285-il-100000.txt Download as CSV file: xf-goe285-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3456 0.10685 0.10152 -0.0280 1.0000 0.1119
-9.000 -0.3582 0.10484 0.09960 -0.0316 1.0000 0.1155
-8.750 -0.3934 0.10387 0.09880 -0.0367 1.0000 0.1166
-8.500 -0.3769 0.09849 0.09344 -0.0350 1.0000 0.1178
-8.250 -0.3519 0.09469 0.08963 -0.0320 1.0000 0.1199
-8.000 -0.3455 0.09204 0.08702 -0.0309 1.0000 0.1223
-7.750 -0.3481 0.08967 0.08472 -0.0303 1.0000 0.1251
-7.500 -0.3622 0.08769 0.08285 -0.0294 1.0000 0.1278
-7.250 -0.3957 0.08607 0.08138 -0.0316 1.0000 0.1308
-7.000 -0.4383 0.08435 0.07960 -0.0354 1.0000 0.1323
-6.750 -0.4252 0.08024 0.07565 -0.0308 1.0000 0.1335
-6.500 -0.4208 0.07797 0.07347 -0.0268 1.0000 0.1349
-6.250 -0.4211 0.07616 0.07172 -0.0236 1.0000 0.1372
-6.000 -0.4252 0.07426 0.06986 -0.0218 1.0000 0.1405
-5.750 -0.4440 0.07134 0.06661 -0.0282 1.0000 0.1489
-5.500 -0.4385 0.06827 0.06372 -0.0247 1.0000 0.1504
-5.250 -0.4344 0.06630 0.06183 -0.0219 1.0000 0.1527
-5.000 -0.3936 0.06145 0.05664 -0.0323 0.9916 0.1667
-4.750 -0.3563 0.05789 0.05314 -0.0351 0.9843 0.1714
-4.500 -0.3171 0.05381 0.04883 -0.0419 0.9747 0.1858
-4.250 -0.2628 0.04235 0.03559 -0.0523 0.9668 0.1166
-4.000 -0.2260 0.03831 0.03160 -0.0555 0.9600 0.1128
-3.750 -0.1856 0.03332 0.02556 -0.0583 0.9530 0.1015
-3.500 -0.1447 0.03070 0.02253 -0.0611 0.9455 0.1011
-3.250 -0.1050 0.02883 0.02017 -0.0632 0.9374 0.1027
-3.000 -0.0635 0.02717 0.01853 -0.0662 0.9300 0.1078
-2.750 -0.0241 0.02586 0.01697 -0.0682 0.9214 0.1127
-2.500 0.0205 0.02432 0.01523 -0.0709 0.9144 0.1200
-2.250 0.0616 0.02330 0.01414 -0.0732 0.9061 0.1344
-2.000 0.1043 0.02211 0.01304 -0.0756 0.8984 0.1558
-1.750 0.1420 0.02131 0.01222 -0.0771 0.8892 0.1808
-1.500 0.1814 0.02039 0.01152 -0.0790 0.8807 0.2090
-1.250 0.2138 0.01973 0.01096 -0.0793 0.8689 0.2359
-1.000 0.2533 0.01867 0.01009 -0.0805 0.8603 0.2686
-0.750 0.3407 0.01540 0.00924 -0.0895 0.8503 1.0000
-0.500 0.3698 0.01517 0.00871 -0.0886 0.8334 1.0000
-0.250 0.3964 0.01502 0.00832 -0.0874 0.8162 1.0000
0.000 0.4218 0.01496 0.00806 -0.0862 0.7996 1.0000
0.250 0.4466 0.01495 0.00789 -0.0849 0.7834 1.0000
0.500 0.4711 0.01497 0.00774 -0.0837 0.7670 1.0000
0.750 0.4955 0.01500 0.00762 -0.0824 0.7502 1.0000
1.000 0.5198 0.01504 0.00750 -0.0811 0.7329 1.0000
1.250 0.5440 0.01508 0.00740 -0.0799 0.7152 1.0000
1.500 0.5683 0.01514 0.00732 -0.0786 0.6971 1.0000
1.750 0.5928 0.01523 0.00725 -0.0774 0.6789 1.0000
2.000 0.6174 0.01536 0.00722 -0.0763 0.6606 1.0000
2.250 0.6420 0.01553 0.00724 -0.0752 0.6424 1.0000
2.500 0.6665 0.01574 0.00729 -0.0742 0.6243 1.0000
2.750 0.6909 0.01599 0.00740 -0.0732 0.6064 1.0000
3.250 0.7387 0.01654 0.00772 -0.0711 0.5702 1.0000
3.500 0.7624 0.01684 0.00792 -0.0701 0.5520 1.0000
3.750 0.7861 0.01714 0.00815 -0.0691 0.5343 1.0000
4.000 0.8100 0.01748 0.00838 -0.0682 0.5171 1.0000
4.250 0.8340 0.01785 0.00864 -0.0673 0.5007 1.0000
4.500 0.8583 0.01826 0.00894 -0.0665 0.4854 1.0000
4.750 0.8835 0.01872 0.00925 -0.0658 0.4718 1.0000
5.000 0.9073 0.01924 0.00975 -0.0651 0.4583 1.0000
5.250 0.9316 0.01983 0.01034 -0.0645 0.4470 1.0000
5.500 0.9585 0.02044 0.01080 -0.0643 0.4384 1.0000
5.750 0.9816 0.02108 0.01155 -0.0635 0.4290 1.0000
6.000 1.0089 0.02174 0.01210 -0.0635 0.4224 1.0000
6.250 1.0315 0.02246 0.01299 -0.0627 0.4150 1.0000
6.500 1.0568 0.02311 0.01365 -0.0624 0.4086 1.0000
6.750 1.0818 0.02383 0.01441 -0.0620 0.4025 1.0000
7.000 1.1040 0.02445 0.01516 -0.0611 0.3948 1.0000
7.250 1.1308 0.02499 0.01558 -0.0609 0.3877 1.0000
7.500 1.1502 0.02556 0.01638 -0.0597 0.3791 1.0000
7.750 1.1773 0.02596 0.01665 -0.0595 0.3714 1.0000
8.000 1.1953 0.02652 0.01747 -0.0580 0.3629 1.0000
8.250 1.2223 0.02682 0.01762 -0.0578 0.3550 1.0000
8.500 1.2390 0.02729 0.01838 -0.0561 0.3458 1.0000
8.750 1.2647 0.02757 0.01857 -0.0557 0.3381 1.0000
9.000 1.2814 0.02804 0.01929 -0.0540 0.3292 1.0000
9.250 1.3044 0.02827 0.01951 -0.0532 0.3206 1.0000
9.500 1.3221 0.02852 0.01990 -0.0516 0.3106 1.0000
9.750 1.3390 0.02878 0.02029 -0.0499 0.3002 1.0000
10.000 1.3587 0.02890 0.02038 -0.0486 0.2898 1.0000
10.250 1.3723 0.02916 0.02082 -0.0464 0.2782 1.0000
10.500 1.3829 0.02946 0.02128 -0.0438 0.2652 1.0000
10.750 1.3901 0.02975 0.02169 -0.0407 0.2500 1.0000
11.000 1.3912 0.03018 0.02220 -0.0369 0.2315 1.0000
11.250 1.3827 0.03095 0.02311 -0.0319 0.2075 1.0000
11.500 1.3691 0.03249 0.02465 -0.0272 0.1633 1.0000
11.750 1.3517 0.03520 0.02698 -0.0236 0.1346 1.0000
12.000 1.3354 0.03851 0.03009 -0.0209 0.1217 1.0000
12.250 1.3237 0.04180 0.03335 -0.0190 0.1127 1.0000
12.500 1.3128 0.04517 0.03661 -0.0174 0.1067 1.0000
12.750 1.3096 0.04805 0.03960 -0.0163 0.1008 1.0000
13.000 1.3071 0.05084 0.04231 -0.0151 0.0963 1.0000
13.250 1.3107 0.05318 0.04470 -0.0139 0.0924 1.0000
13.500 1.3154 0.05546 0.04705 -0.0129 0.0887 1.0000
13.750 1.3256 0.05718 0.04867 -0.0116 0.0851 1.0000
14.000 1.3365 0.05906 0.05060 -0.0105 0.0821 1.0000
14.250 1.3419 0.06146 0.05317 -0.0098 0.0796 1.0000
14.500 1.3520 0.06349 0.05528 -0.0089 0.0773 1.0000
14.750 1.3696 0.06493 0.05666 -0.0077 0.0748 1.0000
15.000 1.3862 0.06693 0.05870 -0.0066 0.0726 1.0000
15.250 1.3817 0.07036 0.06240 -0.0065 0.0714 1.0000
15.500 1.3778 0.07390 0.06618 -0.0064 0.0703 1.0000
15.750 1.3739 0.07760 0.07011 -0.0065 0.0694 1.0000
16.000 1.3678 0.08163 0.07436 -0.0069 0.0686 1.0000
16.250 1.3579 0.08612 0.07906 -0.0077 0.0680 1.0000
16.500 1.3447 0.09113 0.08430 -0.0090 0.0675 1.0000
16.750 1.3267 0.09696 0.09038 -0.0111 0.0672 1.0000
17.000 1.2968 0.10487 0.09859 -0.0149 0.0675 1.0000
17.250 1.2498 0.11650 0.11058 -0.0218 0.0687 1.0000
17.500 1.1875 0.13277 0.12718 -0.0325 0.0706 1.0000
17.750 1.1200 0.15304 0.14764 -0.0456 0.0727 1.0000
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