GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 515 AIRFOIL (goe515-il) Reynolds number: 50,000 Max Cl/Cd: 37.57 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe515-il-50000.txt Download as CSV file: xf-goe515-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 515 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4206 0.10523 0.09799 -0.0217 1.0000 0.2283
-8.500 -0.4059 0.10079 0.09355 -0.0205 1.0000 0.2392
-8.250 -0.4328 0.10088 0.09384 -0.0216 1.0000 0.2444
-8.000 -0.4120 0.09594 0.08886 -0.0200 1.0000 0.2575
-7.750 -0.4057 0.09236 0.08533 -0.0190 1.0000 0.2658
-7.500 -0.4300 0.09187 0.08504 -0.0182 1.0000 0.2741
-7.250 -0.4144 0.08766 0.08082 -0.0166 1.0000 0.2862
-7.000 -0.4148 0.08490 0.07812 -0.0147 1.0000 0.2980
-6.750 -0.4202 0.08255 0.07587 -0.0126 1.0000 0.3114
-6.500 -0.4233 0.08010 0.07353 -0.0106 1.0000 0.3265
-6.250 -0.4259 0.07772 0.07123 -0.0081 1.0000 0.3435
-6.000 -0.4310 0.07550 0.06910 -0.0055 1.0000 0.3608
-5.750 -0.4449 0.07394 0.06765 -0.0029 1.0000 0.3796
-5.500 -0.4418 0.07102 0.06479 0.0007 1.0000 0.3994
-5.250 -0.4529 0.06955 0.06340 0.0045 1.0000 0.4260
-5.000 -0.4512 0.06710 0.06102 0.0094 1.0000 0.4559
-4.500 -0.4181 0.04970 0.04223 -0.0266 1.0000 0.2158
-4.250 -0.4004 0.04513 0.03721 -0.0278 1.0000 0.2013
-4.000 -0.3821 0.04161 0.03330 -0.0279 1.0000 0.1949
-3.750 -0.3631 0.03841 0.02967 -0.0277 1.0000 0.1928
-3.500 -0.3429 0.03585 0.02647 -0.0274 1.0000 0.1983
-3.250 -0.3244 0.03397 0.02452 -0.0264 1.0000 0.2066
-3.000 -0.3018 0.03186 0.02174 -0.0259 1.0000 0.2138
-2.750 -0.2815 0.03048 0.02020 -0.0249 1.0000 0.2280
-2.500 -0.2605 0.02918 0.01870 -0.0240 1.0000 0.2422
-2.250 -0.2391 0.02814 0.01740 -0.0232 1.0000 0.2598
-2.000 -0.2177 0.02714 0.01627 -0.0224 1.0000 0.2760
-1.750 -0.1958 0.02630 0.01535 -0.0217 1.0000 0.2931
-1.500 -0.1740 0.02558 0.01454 -0.0210 1.0000 0.3089
-1.250 -0.1517 0.02500 0.01390 -0.0203 1.0000 0.3270
-1.000 -0.1253 0.02452 0.01328 -0.0203 1.0000 0.3454
-0.750 -0.0998 0.02408 0.01288 -0.0203 1.0000 0.3718
-0.500 -0.0747 0.02364 0.01258 -0.0203 1.0000 0.4053
-0.250 -0.0497 0.02293 0.01232 -0.0201 1.0000 0.4728
0.000 0.0006 0.02127 0.01175 -0.0241 1.0000 1.0000
0.250 0.0193 0.02172 0.01187 -0.0232 1.0000 1.0000
0.500 0.0375 0.02221 0.01212 -0.0224 1.0000 1.0000
0.750 0.0553 0.02273 0.01245 -0.0217 1.0000 1.0000
1.000 0.0728 0.02329 0.01286 -0.0210 1.0000 1.0000
1.250 0.0902 0.02390 0.01334 -0.0203 1.0000 1.0000
1.500 0.1072 0.02455 0.01390 -0.0197 1.0000 1.0000
1.750 0.1240 0.02526 0.01452 -0.0192 1.0000 1.0000
2.000 0.1699 0.02662 0.01582 -0.0244 0.9868 1.0000
2.250 0.2245 0.02814 0.01729 -0.0309 0.9694 1.0000
2.500 0.2685 0.02924 0.01841 -0.0353 0.9507 1.0000
2.750 0.3131 0.03033 0.01953 -0.0395 0.9319 1.0000
3.000 0.3595 0.03138 0.02066 -0.0438 0.9134 1.0000
3.250 0.4030 0.03231 0.02166 -0.0474 0.8944 1.0000
3.500 0.4383 0.03311 0.02256 -0.0494 0.8737 1.0000
3.750 0.4817 0.03387 0.02347 -0.0525 0.8543 1.0000
4.000 0.5237 0.03454 0.02430 -0.0551 0.8348 1.0000
4.250 0.5547 0.03523 0.02513 -0.0559 0.8132 1.0000
4.500 0.6014 0.03555 0.02570 -0.0585 0.7935 1.0000
4.750 0.6444 0.03532 0.02569 -0.0595 0.7672 1.0000
5.000 0.7150 0.03307 0.02384 -0.0618 0.7371 1.0000
5.250 0.7645 0.03154 0.02259 -0.0618 0.7113 1.0000
5.500 0.8167 0.02969 0.02109 -0.0616 0.6862 1.0000
5.750 0.8546 0.02835 0.02000 -0.0598 0.6556 1.0000
6.000 0.8911 0.02682 0.01866 -0.0572 0.6163 1.0000
6.250 0.9182 0.02547 0.01733 -0.0530 0.5606 1.0000
6.500 0.9354 0.02490 0.01646 -0.0480 0.4875 1.0000
6.750 0.9464 0.02563 0.01654 -0.0432 0.4028 1.0000
7.000 0.9549 0.02721 0.01754 -0.0391 0.3275 1.0000
7.250 0.9641 0.02897 0.01885 -0.0356 0.2665 1.0000
7.500 0.9768 0.03091 0.02035 -0.0328 0.2177 1.0000
7.750 0.9962 0.03330 0.02249 -0.0311 0.1803 1.0000
8.000 1.0211 0.03619 0.02521 -0.0303 0.1539 1.0000
8.250 1.0434 0.03907 0.02822 -0.0292 0.1369 1.0000
8.500 1.0647 0.04221 0.03153 -0.0280 0.1261 1.0000
8.750 1.0844 0.04510 0.03452 -0.0268 0.1168 1.0000
9.000 1.0970 0.04880 0.03872 -0.0247 0.1134 1.0000
9.250 1.1024 0.05232 0.04283 -0.0219 0.1110 1.0000
9.500 1.1048 0.05588 0.04685 -0.0191 0.1084 1.0000
9.750 1.1066 0.05940 0.05070 -0.0167 0.1059 1.0000
10.000 1.1143 0.06313 0.05457 -0.0151 0.1033 1.0000
10.250 1.0965 0.06729 0.05923 -0.0116 0.1044 1.0000
10.500 1.0705 0.07173 0.06407 -0.0084 0.1063 1.0000
10.750 1.0402 0.07600 0.06858 -0.0054 0.1081 1.0000
11.000 1.0098 0.08093 0.07368 -0.0043 0.1103 1.0000
11.250 0.9835 0.08658 0.07943 -0.0049 0.1122 1.0000
11.500 0.9621 0.09280 0.08569 -0.0067 0.1137 1.0000
11.750 0.9541 0.09891 0.09183 -0.0081 0.1150 1.0000
12.000 0.8403 0.12600 0.11871 -0.0323 0.1507 1.0000
12.250 0.7938 0.14966 0.14223 -0.0520 0.2866 1.0000
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Polar data table (+)
Polar graphs
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