GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 500,000 Max Cl/Cd: 105.18 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe376-il-500000.txt Download as CSV file: xf-goe376-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3231 0.09544 0.09328 -0.0215 1.0000 0.0157
-7.750 -0.3299 0.09364 0.09153 -0.0210 1.0000 0.0157
-7.500 -0.3317 0.09136 0.08929 -0.0216 1.0000 0.0157
-7.250 -0.3305 0.08878 0.08674 -0.0231 1.0000 0.0157
-7.000 -0.3289 0.08487 0.08286 -0.0192 1.0000 0.0160
-6.750 -0.3302 0.08264 0.08067 -0.0177 1.0000 0.0161
-6.500 -0.3104 0.07906 0.07709 -0.0214 0.9979 0.0165
-6.250 -0.2793 0.07470 0.07271 -0.0290 0.9943 0.0170
-6.000 -0.2482 0.07028 0.06826 -0.0363 0.9891 0.0177
-5.750 -0.2053 0.06537 0.06327 -0.0471 0.9844 0.0192
-5.500 -0.1572 0.06021 0.05796 -0.0591 0.9761 0.0195
-5.000 -0.1057 0.05125 0.04891 -0.0667 0.9623 0.0200
-4.750 -0.0773 0.04804 0.04565 -0.0700 0.9554 0.0204
-4.500 -0.0445 0.04477 0.04230 -0.0742 0.9469 0.0212
-4.250 -0.0044 0.04121 0.03862 -0.0796 0.9397 0.0225
-4.000 0.0548 0.03761 0.03460 -0.0863 0.9314 0.0242
-3.750 0.0892 0.03276 0.02955 -0.0903 0.9199 0.0246
-3.500 0.1195 0.03019 0.02690 -0.0929 0.9060 0.0250
-3.250 0.1480 0.02824 0.02480 -0.0943 0.8900 0.0257
-3.000 0.1744 0.02646 0.02284 -0.0946 0.8733 0.0267
-2.750 0.2003 0.02480 0.02095 -0.0944 0.8564 0.0282
-2.500 0.2321 0.02412 0.01982 -0.0931 0.8395 0.0301
-2.250 0.2526 0.02098 0.01640 -0.0923 0.8226 0.0308
-2.000 0.2744 0.01952 0.01485 -0.0917 0.8054 0.0315
-1.750 0.2976 0.01847 0.01366 -0.0910 0.7881 0.0324
-1.500 0.3215 0.01752 0.01251 -0.0901 0.7708 0.0338
-1.250 0.3470 0.01696 0.01167 -0.0890 0.7528 0.0366
-1.000 0.3711 0.01579 0.01009 -0.0877 0.7347 0.0389
-0.750 0.3942 0.01479 0.00902 -0.0870 0.7156 0.0403
-0.500 0.4184 0.01418 0.00827 -0.0862 0.6983 0.0423
-0.250 0.4442 0.01411 0.00801 -0.0853 0.6823 0.0468
0.000 0.4352 0.01646 0.01234 -0.1195 0.6454 0.0371
1.750 0.6414 0.01042 0.00325 -0.0783 0.5220 0.0557
2.250 0.6899 0.01011 0.00274 -0.0763 0.4867 0.0448
2.500 0.7140 0.01003 0.00258 -0.0753 0.4713 0.0436
2.750 0.7384 0.01002 0.00250 -0.0745 0.4567 0.0437
3.000 0.7629 0.01005 0.00247 -0.0738 0.4429 0.0441
3.250 0.7878 0.01010 0.00249 -0.0731 0.4314 0.0461
3.500 0.8127 0.01018 0.00253 -0.0725 0.4206 0.0463
3.750 0.8378 0.01028 0.00257 -0.0719 0.4095 0.0466
4.000 0.8631 0.01037 0.00264 -0.0713 0.3985 0.0474
4.250 0.8882 0.01049 0.00274 -0.0707 0.3878 0.0510
4.500 0.9582 0.00917 0.00317 -0.0810 0.3699 1.0000
4.750 0.9826 0.00936 0.00331 -0.0803 0.3572 1.0000
5.000 1.0066 0.00957 0.00346 -0.0795 0.3413 1.0000
5.250 1.0299 0.00983 0.00363 -0.0787 0.3200 1.0000
5.500 1.0526 0.01014 0.00382 -0.0777 0.2943 1.0000
5.750 1.0749 0.01050 0.00406 -0.0767 0.2721 1.0000
6.000 1.0973 0.01084 0.00432 -0.0758 0.2533 1.0000
6.250 1.1197 0.01119 0.00461 -0.0748 0.2373 1.0000
6.500 1.1421 0.01154 0.00491 -0.0739 0.2229 1.0000
6.750 1.1642 0.01190 0.00521 -0.0729 0.2071 1.0000
7.000 1.1856 0.01233 0.00554 -0.0718 0.1878 1.0000
7.250 1.2071 0.01274 0.00588 -0.0708 0.1656 1.0000
7.500 1.2262 0.01337 0.00631 -0.0694 0.1342 1.0000
7.750 1.2424 0.01426 0.00693 -0.0676 0.0936 1.0000
8.250 1.2666 0.01675 0.00896 -0.0627 0.0192 1.0000
8.500 1.2849 0.01742 0.00975 -0.0610 0.0172 1.0000
8.750 1.3031 0.01806 0.01049 -0.0594 0.0165 1.0000
9.000 1.3200 0.01877 0.01131 -0.0576 0.0158 1.0000
9.250 1.3354 0.01957 0.01221 -0.0557 0.0153 1.0000
9.500 1.3479 0.02054 0.01327 -0.0533 0.0143 1.0000
9.750 1.3584 0.02156 0.01441 -0.0507 0.0137 1.0000
10.000 1.3624 0.02282 0.01577 -0.0471 0.0131 1.0000
10.250 1.3602 0.02427 0.01733 -0.0426 0.0127 1.0000
10.500 1.3578 0.02585 0.01903 -0.0385 0.0125 1.0000
10.750 1.3578 0.02742 0.02071 -0.0352 0.0123 1.0000
11.000 1.3625 0.02877 0.02216 -0.0327 0.0121 1.0000
11.250 1.3665 0.03028 0.02377 -0.0305 0.0119 1.0000
11.500 1.3690 0.03203 0.02563 -0.0285 0.0117 1.0000
11.750 1.3700 0.03404 0.02776 -0.0266 0.0117 1.0000
12.000 1.3714 0.03617 0.02999 -0.0251 0.0116 1.0000
12.250 1.3733 0.03835 0.03229 -0.0238 0.0114 1.0000
12.500 1.3743 0.04075 0.03479 -0.0227 0.0112 1.0000
12.750 1.3757 0.04319 0.03734 -0.0218 0.0110 1.0000
13.000 1.3762 0.04582 0.04009 -0.0209 0.0109 1.0000
13.250 1.3773 0.04840 0.04277 -0.0205 0.0106 1.0000
13.500 1.3768 0.05131 0.04579 -0.0199 0.0104 1.0000
13.750 1.3768 0.05408 0.04864 -0.0199 0.0100 1.0000
14.000 1.3763 0.05706 0.05172 -0.0196 0.0099 1.0000
14.250 1.3744 0.06032 0.05512 -0.0193 0.0099 1.0000
14.500 1.3721 0.06359 0.05849 -0.0195 0.0097 1.0000
14.750 1.3690 0.06717 0.06220 -0.0195 0.0097 1.0000
15.000 1.3638 0.07110 0.06629 -0.0201 0.0097 1.0000
15.250 1.3585 0.07509 0.07040 -0.0208 0.0096 1.0000
15.500 1.3444 0.08084 0.07641 -0.0227 0.0099 1.0000
15.750 1.3315 0.08651 0.08229 -0.0247 0.0100 1.0000
16.000 1.3192 0.09224 0.08820 -0.0271 0.0101 1.0000
16.250 1.3058 0.09841 0.09455 -0.0299 0.0101 1.0000
16.500 1.2860 0.10613 0.10250 -0.0336 0.0104 1.0000
16.750 1.2696 0.11337 0.10992 -0.0373 0.0107 1.0000
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Polar data table (+)
Polar graphs
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