GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 500,000 Max Cl/Cd: 96.91 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe328-il-500000-n5.txt Download as CSV file: xf-goe328-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 328 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3774 0.09384 0.09160 -0.0170 1.0000 0.0182
-8.000 -0.3723 0.09046 0.08823 -0.0190 1.0000 0.0184
-7.750 -0.3680 0.08714 0.08494 -0.0210 1.0000 0.0185
-7.500 -0.3560 0.08302 0.08081 -0.0259 0.9705 0.0188
-7.250 -0.3404 0.07617 0.07390 -0.0370 0.9396 0.0204
-7.000 -0.3270 0.07466 0.07234 -0.0367 0.9176 0.0209
-6.750 -0.3129 0.07247 0.07008 -0.0384 0.8974 0.0217
-6.500 -0.2400 0.05392 0.05139 -0.0469 0.8363 0.0248
-6.000 -0.2582 0.06116 0.05846 -0.0512 0.8492 0.0233
-5.750 -0.2365 0.05700 0.05416 -0.0556 0.8357 0.0230
-5.500 -0.2117 0.05286 0.04988 -0.0600 0.8231 0.0236
-5.250 -0.1842 0.04837 0.04519 -0.0645 0.8113 0.0241
-5.000 -0.1589 0.04462 0.04128 -0.0675 0.7997 0.0239
-4.750 -0.1320 0.04086 0.03731 -0.0701 0.7881 0.0239
-4.500 -0.1046 0.03729 0.03351 -0.0723 0.7763 0.0240
-4.250 -0.0740 0.03316 0.02905 -0.0743 0.7650 0.0246
-4.000 -0.0464 0.02989 0.02552 -0.0756 0.7540 0.0247
-3.750 -0.0179 0.02678 0.02209 -0.0764 0.7441 0.0249
-3.500 0.0106 0.02354 0.01848 -0.0772 0.7346 0.0252
-3.250 0.0384 0.02099 0.01560 -0.0778 0.7253 0.0253
-3.000 0.0662 0.01886 0.01315 -0.0783 0.7165 0.0255
-2.750 0.0941 0.01771 0.01182 -0.0787 0.7074 0.0259
-2.500 0.1225 0.01646 0.01034 -0.0789 0.6984 0.0261
-2.250 0.1511 0.01513 0.00873 -0.0791 0.6889 0.0261
-2.000 0.1797 0.01423 0.00763 -0.0793 0.6799 0.0263
-1.750 0.2080 0.01354 0.00678 -0.0794 0.6701 0.0266
-1.500 0.2364 0.01298 0.00608 -0.0795 0.6582 0.0270
-1.250 0.2647 0.01249 0.00545 -0.0795 0.6453 0.0274
-1.000 0.2930 0.01207 0.00491 -0.0796 0.6315 0.0278
-0.750 0.3212 0.01170 0.00443 -0.0796 0.6169 0.0282
-0.500 0.3494 0.01136 0.00400 -0.0796 0.6021 0.0286
-0.250 0.3777 0.01107 0.00362 -0.0797 0.5884 0.0290
0.000 0.4059 0.01086 0.00334 -0.0797 0.5738 0.0297
0.250 0.4340 0.01071 0.00312 -0.0798 0.5574 0.0304
0.500 0.4622 0.01054 0.00288 -0.0798 0.5391 0.0309
0.750 0.4902 0.01041 0.00266 -0.0799 0.5188 0.0312
1.000 0.5182 0.01034 0.00250 -0.0799 0.4965 0.0315
1.250 0.5461 0.01032 0.00239 -0.0800 0.4757 0.0319
2.000 0.6302 0.01025 0.00215 -0.0803 0.4326 0.0357
2.250 0.6583 0.01030 0.00217 -0.0803 0.4224 0.0372
2.750 0.7143 0.01042 0.00225 -0.0804 0.4041 0.0437
3.000 0.7422 0.01049 0.00233 -0.0805 0.3955 0.0566
3.500 0.7908 0.00879 0.00264 -0.0795 0.3794 1.0000
3.750 0.8187 0.00894 0.00276 -0.0795 0.3710 1.0000
4.000 0.8464 0.00910 0.00288 -0.0796 0.3634 1.0000
4.250 0.8741 0.00926 0.00301 -0.0796 0.3550 1.0000
4.500 0.9017 0.00944 0.00316 -0.0796 0.3461 1.0000
4.750 0.9289 0.00965 0.00332 -0.0796 0.3314 1.0000
5.000 0.9558 0.00990 0.00349 -0.0795 0.3149 1.0000
5.250 0.9827 0.01014 0.00369 -0.0795 0.3010 1.0000
5.500 1.0093 0.01042 0.00390 -0.0794 0.2840 1.0000
5.750 1.0355 0.01073 0.00414 -0.0793 0.2674 1.0000
6.000 1.0611 0.01113 0.00443 -0.0791 0.2469 1.0000
6.250 1.0869 0.01148 0.00471 -0.0789 0.2296 1.0000
6.500 1.1126 0.01183 0.00501 -0.0787 0.2142 1.0000
6.750 1.1376 0.01227 0.00536 -0.0785 0.1904 1.0000
7.000 1.1552 0.01370 0.00627 -0.0775 0.0971 1.0000
7.250 1.1755 0.01474 0.00705 -0.0766 0.0528 1.0000
7.500 1.1989 0.01531 0.00759 -0.0762 0.0408 1.0000
7.750 1.2222 0.01586 0.00811 -0.0756 0.0318 1.0000
8.000 1.2453 0.01640 0.00865 -0.0751 0.0256 1.0000
8.250 1.2681 0.01696 0.00921 -0.0745 0.0214 1.0000
8.500 1.2906 0.01751 0.00978 -0.0739 0.0187 1.0000
8.750 1.3122 0.01814 0.01043 -0.0731 0.0167 1.0000
9.000 1.3339 0.01870 0.01107 -0.0724 0.0155 1.0000
9.250 1.3547 0.01933 0.01174 -0.0716 0.0145 1.0000
9.500 1.3742 0.02005 0.01251 -0.0706 0.0136 1.0000
9.750 1.3911 0.02096 0.01348 -0.0692 0.0127 1.0000
10.000 1.4097 0.02164 0.01425 -0.0681 0.0122 1.0000
10.250 1.4269 0.02239 0.01509 -0.0668 0.0116 1.0000
10.500 1.4425 0.02320 0.01596 -0.0653 0.0110 1.0000
10.750 1.4559 0.02407 0.01691 -0.0636 0.0105 1.0000
11.000 1.4649 0.02503 0.01794 -0.0611 0.0102 1.0000
11.250 1.4715 0.02621 0.01920 -0.0586 0.0098 1.0000
11.500 1.4748 0.02774 0.02082 -0.0561 0.0095 1.0000
11.750 1.4781 0.02942 0.02261 -0.0540 0.0093 1.0000
12.000 1.4842 0.03101 0.02431 -0.0525 0.0091 1.0000
12.250 1.4890 0.03282 0.02624 -0.0511 0.0089 1.0000
12.500 1.4927 0.03485 0.02838 -0.0500 0.0087 1.0000
12.750 1.4959 0.03704 0.03068 -0.0491 0.0085 1.0000
13.000 1.4984 0.03941 0.03316 -0.0484 0.0083 1.0000
13.250 1.5003 0.04194 0.03581 -0.0479 0.0081 1.0000
13.500 1.5013 0.04466 0.03863 -0.0476 0.0079 1.0000
13.750 1.5018 0.04752 0.04161 -0.0474 0.0077 1.0000
14.000 1.5012 0.05060 0.04479 -0.0474 0.0076 1.0000
14.250 1.4995 0.05387 0.04816 -0.0476 0.0074 1.0000
14.500 1.4963 0.05741 0.05180 -0.0479 0.0073 1.0000
14.750 1.4917 0.06120 0.05569 -0.0483 0.0072 1.0000
15.000 1.4852 0.06531 0.05992 -0.0489 0.0071 1.0000
15.250 1.4781 0.06968 0.06439 -0.0498 0.0070 1.0000
15.500 1.4697 0.07431 0.06913 -0.0507 0.0069 1.0000
15.750 1.4603 0.07916 0.07410 -0.0518 0.0068 1.0000
16.000 1.4537 0.08374 0.07879 -0.0529 0.0068 1.0000
16.250 1.4480 0.08828 0.08345 -0.0542 0.0067 1.0000
16.500 1.4417 0.09292 0.08823 -0.0555 0.0066 1.0000
16.750 1.4351 0.09769 0.09312 -0.0570 0.0066 1.0000
17.000 1.4283 0.10256 0.09813 -0.0586 0.0065 1.0000
17.250 1.4212 0.10753 0.10322 -0.0603 0.0065 1.0000
17.500 1.4137 0.11261 0.10843 -0.0621 0.0064 1.0000
17.750 1.4061 0.11780 0.11375 -0.0641 0.0063 1.0000
18.000 1.3985 0.12310 0.11918 -0.0663 0.0063 1.0000
18.250 1.3907 0.12853 0.12474 -0.0687 0.0062 1.0000
18.500 1.3825 0.13412 0.13046 -0.0713 0.0062 1.0000
18.750 1.3743 0.13982 0.13629 -0.0741 0.0061 1.0000
19.000 1.3656 0.14575 0.14235 -0.0771 0.0060 1.0000
19.250 1.3569 0.15188 0.14861 -0.0804 0.0060 1.0000
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