GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 100,000 Max Cl/Cd: 53.93 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe479-il-100000.txt Download as CSV file: xf-goe479-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3273 0.10060 0.09548 -0.0356 1.0000 0.1246
-8.750 -0.3565 0.09985 0.09488 -0.0369 1.0000 0.1281
-8.500 -0.3972 0.09970 0.09492 -0.0365 1.0000 0.1288
-8.250 -0.3667 0.09399 0.08919 -0.0341 1.0000 0.1312
-8.000 -0.3510 0.09151 0.08671 -0.0312 1.0000 0.1354
-7.750 -0.3620 0.08993 0.08521 -0.0290 1.0000 0.1388
-7.500 -0.3869 0.08890 0.08432 -0.0264 1.0000 0.1412
-7.250 -0.4234 0.08797 0.08353 -0.0255 1.0000 0.1432
-7.000 -0.4755 0.08655 0.08206 -0.0315 1.0000 0.1448
-6.750 -0.4569 0.08261 0.07830 -0.0244 1.0000 0.1466
-6.500 -0.4535 0.08084 0.07660 -0.0201 1.0000 0.1487
-6.250 -0.4578 0.07910 0.07489 -0.0178 1.0000 0.1514
-6.000 -0.4525 0.07357 0.06918 -0.0304 0.9939 0.1623
-5.750 -0.4252 0.07057 0.06625 -0.0294 0.9882 0.1656
-5.500 -0.3961 0.06565 0.06111 -0.0390 0.9784 0.1798
-5.250 -0.3659 0.06312 0.05862 -0.0395 0.9722 0.1867
-5.000 -0.3397 0.05911 0.05447 -0.0448 0.9624 0.1995
-4.750 -0.2995 0.04132 0.03484 -0.0603 0.9551 0.1160
-4.500 -0.2703 0.03801 0.03109 -0.0617 0.9458 0.1118
-4.250 -0.2305 0.03461 0.02722 -0.0649 0.9402 0.1096
-4.000 -0.2017 0.03213 0.02429 -0.0655 0.9300 0.1084
-3.750 -0.1566 0.02996 0.02163 -0.0687 0.9250 0.1102
-3.500 -0.1297 0.02874 0.01999 -0.0684 0.9141 0.1129
-3.250 -0.0849 0.02697 0.01795 -0.0714 0.9094 0.1161
-3.000 -0.0589 0.02617 0.01712 -0.0711 0.8988 0.1205
-2.750 -0.0136 0.02524 0.01594 -0.0739 0.8938 0.1287
-2.500 0.0131 0.02437 0.01517 -0.0737 0.8839 0.1352
-2.250 0.0565 0.02342 0.01422 -0.0762 0.8785 0.1491
-1.750 0.1263 0.02182 0.01291 -0.0782 0.8634 0.1993
-1.500 0.1708 0.02048 0.01209 -0.0808 0.8597 0.2897
-1.250 0.1903 0.01960 0.01194 -0.0793 0.8484 0.4250
-1.000 0.3208 0.01754 0.01125 -0.0972 0.8517 1.0000
-0.750 0.3622 0.01723 0.01071 -0.0992 0.8447 1.0000
-0.500 0.3853 0.01729 0.01061 -0.0981 0.8330 1.0000
-0.250 0.4275 0.01693 0.01007 -0.1001 0.8268 1.0000
0.000 0.4479 0.01706 0.01008 -0.0984 0.8141 1.0000
0.250 0.4748 0.01705 0.00996 -0.0978 0.8033 1.0000
0.500 0.5099 0.01682 0.00960 -0.0985 0.7949 1.0000
0.750 0.5317 0.01697 0.00965 -0.0970 0.7824 1.0000
1.000 0.5591 0.01698 0.00957 -0.0965 0.7716 1.0000
1.250 0.5912 0.01685 0.00933 -0.0966 0.7618 1.0000
1.500 0.6131 0.01704 0.00946 -0.0951 0.7489 1.0000
1.750 0.6382 0.01716 0.00950 -0.0941 0.7368 1.0000
2.000 0.6692 0.01712 0.00935 -0.0940 0.7264 1.0000
2.250 0.6931 0.01725 0.00941 -0.0928 0.7129 1.0000
2.500 0.7160 0.01743 0.00953 -0.0915 0.6989 1.0000
2.750 0.7401 0.01758 0.00963 -0.0903 0.6854 1.0000
3.000 0.7662 0.01772 0.00968 -0.0895 0.6731 1.0000
3.250 0.7934 0.01784 0.00972 -0.0888 0.6614 1.0000
3.500 0.8145 0.01815 0.01004 -0.0874 0.6480 1.0000
3.750 0.8375 0.01843 0.01030 -0.0862 0.6357 1.0000
4.000 0.8641 0.01861 0.01042 -0.0855 0.6245 1.0000
4.250 0.8879 0.01885 0.01065 -0.0844 0.6122 1.0000
4.500 0.9093 0.01917 0.01099 -0.0831 0.5993 1.0000
4.750 0.9329 0.01943 0.01124 -0.0820 0.5873 1.0000
5.000 0.9602 0.01957 0.01133 -0.0814 0.5760 1.0000
5.250 0.9814 0.01985 0.01165 -0.0800 0.5626 1.0000
5.500 1.0028 0.02014 0.01199 -0.0786 0.5493 1.0000
5.750 1.0255 0.02038 0.01223 -0.0773 0.5358 1.0000
6.000 1.0482 0.02052 0.01238 -0.0760 0.5210 1.0000
6.250 1.0699 0.02061 0.01244 -0.0745 0.5045 1.0000
6.500 1.0905 0.02068 0.01246 -0.0727 0.4864 1.0000
6.750 1.1108 0.02079 0.01253 -0.0710 0.4680 1.0000
7.000 1.1309 0.02102 0.01272 -0.0693 0.4504 1.0000
7.250 1.1503 0.02133 0.01300 -0.0676 0.4332 1.0000
7.500 1.1689 0.02168 0.01334 -0.0657 0.4162 1.0000
7.750 1.1863 0.02204 0.01369 -0.0638 0.3990 1.0000
8.000 1.2025 0.02241 0.01407 -0.0616 0.3820 1.0000
8.250 1.2165 0.02278 0.01446 -0.0592 0.3645 1.0000
8.500 1.2282 0.02316 0.01493 -0.0564 0.3466 1.0000
8.750 1.2384 0.02356 0.01541 -0.0534 0.3278 1.0000
9.000 1.2472 0.02401 0.01591 -0.0503 0.3085 1.0000
9.250 1.2521 0.02455 0.01641 -0.0466 0.2874 1.0000
9.500 1.2515 0.02525 0.01711 -0.0421 0.2620 1.0000
9.750 1.2461 0.02635 0.01808 -0.0373 0.2304 1.0000
10.000 1.2362 0.02800 0.01953 -0.0326 0.1922 1.0000
10.250 1.2249 0.03012 0.02138 -0.0284 0.1552 1.0000
10.500 1.2174 0.03232 0.02338 -0.0250 0.1339 1.0000
10.750 1.2136 0.03444 0.02538 -0.0223 0.1219 1.0000
11.000 1.2126 0.03651 0.02738 -0.0201 0.1139 1.0000
11.250 1.2155 0.03841 0.02928 -0.0183 0.1076 1.0000
11.500 1.2192 0.04032 0.03117 -0.0167 0.1025 1.0000
11.750 1.2268 0.04210 0.03291 -0.0151 0.0985 1.0000
12.000 1.2386 0.04365 0.03453 -0.0138 0.0950 1.0000
12.250 1.2518 0.04516 0.03603 -0.0127 0.0918 1.0000
12.500 1.2749 0.04649 0.03719 -0.0118 0.0882 1.0000
12.750 1.2880 0.04819 0.03910 -0.0107 0.0856 1.0000
13.000 1.3061 0.04983 0.04086 -0.0099 0.0834 1.0000
13.250 1.3260 0.05152 0.04262 -0.0092 0.0812 1.0000
13.500 1.3708 0.05342 0.04432 -0.0100 0.0777 1.0000
13.750 1.3731 0.05579 0.04701 -0.0085 0.0767 1.0000
14.000 1.3760 0.05846 0.04997 -0.0073 0.0758 1.0000
14.250 1.3756 0.06141 0.05320 -0.0061 0.0750 1.0000
14.500 1.3712 0.06461 0.05667 -0.0051 0.0742 1.0000
14.750 1.3634 0.06814 0.06047 -0.0043 0.0735 1.0000
15.000 1.3526 0.07196 0.06455 -0.0039 0.0729 1.0000
15.250 1.3386 0.07620 0.06905 -0.0038 0.0724 1.0000
15.500 1.3190 0.08121 0.07433 -0.0044 0.0722 1.0000
15.750 1.2931 0.08715 0.08056 -0.0058 0.0724 1.0000
16.000 1.2598 0.09440 0.08811 -0.0085 0.0728 1.0000
16.250 1.2185 0.10365 0.09765 -0.0129 0.0738 1.0000
16.500 1.1724 0.11496 0.10923 -0.0192 0.0752 1.0000
16.750 1.1259 0.12801 0.12244 -0.0270 0.0767 1.0000
17.000 1.0919 0.14022 0.13476 -0.0339 0.0777 1.0000
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