GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 500,000 Max Cl/Cd: 104.32 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe264-il-500000-n5.txt Download as CSV file: xf-goe264-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3226 0.09784 0.09568 -0.0226 1.0000 0.0076
-8.250 -0.3184 0.09454 0.09240 -0.0240 1.0000 0.0078
-8.000 -0.3137 0.09106 0.08895 -0.0259 0.9962 0.0079
-7.750 -0.3003 0.08622 0.08411 -0.0312 0.9845 0.0084
-7.500 -0.2850 0.07975 0.07764 -0.0390 0.9731 0.0091
-7.250 -0.2663 0.07615 0.07402 -0.0439 0.9618 0.0094
-7.000 -0.2481 0.07283 0.07067 -0.0481 0.9504 0.0097
-6.750 -0.2299 0.06935 0.06716 -0.0524 0.9385 0.0102
-6.500 -0.2096 0.06527 0.06303 -0.0575 0.9269 0.0107
-6.250 -0.1850 0.05911 0.05679 -0.0654 0.9154 0.0120
-6.000 -0.1569 0.05343 0.05101 -0.0729 0.9037 0.0133
-5.750 -0.1317 0.05136 0.04885 -0.0756 0.8911 0.0140
-5.500 -0.1033 0.04807 0.04543 -0.0798 0.8779 0.0152
-5.250 -0.0616 0.03961 0.03669 -0.0903 0.8659 0.0187
-5.000 -0.0359 0.03892 0.03590 -0.0910 0.8512 0.0194
-4.750 -0.0067 0.03694 0.03376 -0.0932 0.8362 0.0209
-4.500 0.0395 0.02851 0.02484 -0.1017 0.8238 0.0257
-4.250 0.0665 0.02791 0.02411 -0.1022 0.8073 0.0264
-4.000 0.0941 0.02727 0.02333 -0.1027 0.7894 0.0275
-3.750 0.1419 0.01671 0.01166 -0.1098 0.7767 0.0327
-3.500 0.1729 0.01444 0.00886 -0.1112 0.7553 0.0334
-3.250 0.2018 0.01350 0.00760 -0.1116 0.7279 0.0340
-3.000 0.2301 0.01294 0.00675 -0.1118 0.6935 0.0345
-2.750 0.2585 0.01253 0.00607 -0.1120 0.6641 0.0349
-2.500 0.2867 0.01235 0.00570 -0.1121 0.6422 0.0357
-2.250 0.3153 0.01202 0.00518 -0.1123 0.6245 0.0364
-2.000 0.3441 0.01163 0.00460 -0.1125 0.6102 0.0370
-1.750 0.3728 0.01132 0.00415 -0.1127 0.5976 0.0377
-1.500 0.4014 0.01108 0.00377 -0.1129 0.5849 0.0388
-1.250 0.4300 0.01088 0.00347 -0.1130 0.5727 0.0399
-1.000 0.4586 0.01073 0.00323 -0.1132 0.5611 0.0409
-0.750 0.4870 0.01063 0.00305 -0.1133 0.5488 0.0416
-0.500 0.5154 0.01057 0.00291 -0.1134 0.5359 0.0421
-0.250 0.5442 0.01032 0.00259 -0.1136 0.5233 0.0436
0.000 0.5727 0.01022 0.00244 -0.1138 0.5101 0.0452
0.250 0.6010 0.01020 0.00236 -0.1139 0.4962 0.0468
0.750 0.6575 0.01023 0.00229 -0.1141 0.4694 0.0516
1.000 0.6857 0.01027 0.00228 -0.1142 0.4569 0.0536
1.250 0.7138 0.01031 0.00226 -0.1143 0.4430 0.0556
1.500 0.7419 0.01036 0.00226 -0.1145 0.4292 0.0602
1.750 0.7699 0.01044 0.00231 -0.1145 0.4162 0.0652
2.000 0.7979 0.01051 0.00238 -0.1147 0.4062 0.0760
2.250 0.8260 0.01055 0.00249 -0.1148 0.3973 0.1094
2.500 0.8539 0.01063 0.00262 -0.1149 0.3894 0.1319
2.750 0.8818 0.01073 0.00273 -0.1150 0.3814 0.1472
3.000 0.9096 0.01082 0.00285 -0.1150 0.3740 0.1662
3.250 0.9373 0.01092 0.00300 -0.1151 0.3662 0.1895
3.500 0.9654 0.01093 0.00318 -0.1154 0.3591 0.2726
4.000 1.0136 0.00996 0.00350 -0.1141 0.3446 1.0000
4.250 1.0410 0.01014 0.00366 -0.1141 0.3379 1.0000
4.500 1.0684 0.01032 0.00384 -0.1141 0.3326 1.0000
4.750 1.0957 0.01051 0.00403 -0.1140 0.3254 1.0000
5.000 1.1225 0.01076 0.00423 -0.1140 0.3119 1.0000
5.250 1.1490 0.01103 0.00445 -0.1139 0.2965 1.0000
5.500 1.1753 0.01133 0.00469 -0.1138 0.2806 1.0000
5.750 1.2011 0.01168 0.00497 -0.1136 0.2607 1.0000
6.000 1.2261 0.01215 0.00530 -0.1133 0.2300 1.0000
6.250 1.2435 0.01378 0.00628 -0.1123 0.1176 1.0000
6.500 1.2631 0.01503 0.00720 -0.1114 0.0540 1.0000
6.750 1.2849 0.01589 0.00793 -0.1106 0.0266 1.0000
7.000 1.3083 0.01647 0.00852 -0.1101 0.0173 1.0000
7.250 1.3316 0.01703 0.00910 -0.1095 0.0142 1.0000
7.500 1.3538 0.01773 0.00986 -0.1087 0.0114 1.0000
7.750 1.3765 0.01828 0.01048 -0.1080 0.0106 1.0000
8.000 1.3984 0.01891 0.01119 -0.1072 0.0098 1.0000
8.250 1.4193 0.01958 0.01196 -0.1063 0.0089 1.0000
8.500 1.4385 0.02040 0.01283 -0.1052 0.0081 1.0000
8.750 1.4558 0.02136 0.01389 -0.1037 0.0074 1.0000
9.000 1.4738 0.02217 0.01479 -0.1024 0.0070 1.0000
9.250 1.4900 0.02308 0.01580 -0.1008 0.0067 1.0000
9.500 1.5044 0.02406 0.01687 -0.0990 0.0063 1.0000
9.750 1.5170 0.02507 0.01797 -0.0969 0.0060 1.0000
10.000 1.5270 0.02614 0.01913 -0.0945 0.0058 1.0000
10.250 1.5319 0.02732 0.02042 -0.0913 0.0056 1.0000
10.500 1.5345 0.02876 0.02195 -0.0881 0.0054 1.0000
10.750 1.5327 0.03068 0.02398 -0.0848 0.0052 1.0000
11.000 1.5315 0.03275 0.02617 -0.0820 0.0051 1.0000
11.250 1.5352 0.03458 0.02813 -0.0801 0.0049 1.0000
11.500 1.5382 0.03660 0.03028 -0.0784 0.0048 1.0000
11.750 1.5398 0.03890 0.03271 -0.0770 0.0046 1.0000
12.000 1.5403 0.04146 0.03540 -0.0758 0.0044 1.0000
12.250 1.5394 0.04432 0.03838 -0.0749 0.0043 1.0000
12.500 1.5376 0.04741 0.04161 -0.0742 0.0042 1.0000
12.750 1.5354 0.05070 0.04502 -0.0738 0.0041 1.0000
13.000 1.5332 0.05411 0.04856 -0.0736 0.0040 1.0000
13.250 1.5300 0.05772 0.05230 -0.0736 0.0040 1.0000
13.500 1.5268 0.06141 0.05610 -0.0737 0.0039 1.0000
13.750 1.5229 0.06524 0.06008 -0.0740 0.0038 1.0000
14.000 1.5182 0.06921 0.06417 -0.0744 0.0038 1.0000
14.250 1.5130 0.07333 0.06841 -0.0749 0.0037 1.0000
14.500 1.5078 0.07756 0.07276 -0.0756 0.0037 1.0000
14.750 1.5020 0.08196 0.07727 -0.0764 0.0036 1.0000
15.000 1.4953 0.08653 0.08196 -0.0773 0.0036 1.0000
15.250 1.4882 0.09127 0.08682 -0.0784 0.0035 1.0000
15.500 1.4802 0.09623 0.09191 -0.0796 0.0035 1.0000
15.750 1.4711 0.10141 0.09723 -0.0809 0.0034 1.0000
16.000 1.4604 0.10694 0.10291 -0.0825 0.0034 1.0000
16.250 1.4489 0.11281 0.10893 -0.0844 0.0034 1.0000
16.500 1.4396 0.11855 0.11484 -0.0866 0.0033 1.0000
16.750 1.4297 0.12452 0.12097 -0.0890 0.0033 1.0000
17.000 1.4191 0.13078 0.12738 -0.0918 0.0033 1.0000
17.250 1.4078 0.13738 0.13416 -0.0950 0.0033 1.0000
17.500 1.3967 0.14416 0.14110 -0.0985 0.0033 1.0000
17.750 1.3846 0.15144 0.14854 -0.1025 0.0033 1.0000
18.000 1.3722 0.15901 0.15627 -0.1069 0.0033 1.0000
18.250 1.3595 0.16698 0.16439 -0.1116 0.0033 1.0000
18.500 1.3461 0.17556 0.17313 -0.1170 0.0033 1.0000
18.750 1.3325 0.18469 0.18240 -0.1229 0.0033 1.0000
19.000 1.3182 0.19474 0.19260 -0.1294 0.0033 1.0000
19.250 1.3018 0.20653 0.20453 -0.1370 0.0033 1.0000
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Polar data table (+)
Polar graphs
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