GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 500,000 Max Cl/Cd: 105.95 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe373-il-500000.txt Download as CSV file: xf-goe373-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3042 0.09778 0.09558 -0.0237 1.0000 0.0159
-8.000 -0.3083 0.09597 0.09382 -0.0238 1.0000 0.0159
-7.750 -0.3137 0.09418 0.09208 -0.0231 1.0000 0.0159
-7.500 -0.3109 0.09066 0.08860 -0.0221 1.0000 0.0160
-7.250 -0.3063 0.08752 0.08548 -0.0198 1.0000 0.0162
-7.000 -0.3058 0.08522 0.08322 -0.0185 1.0000 0.0164
-6.750 -0.3053 0.08310 0.08114 -0.0182 0.9998 0.0165
-6.500 -0.2768 0.07888 0.07689 -0.0252 0.9962 0.0170
-6.250 -0.2468 0.07459 0.07259 -0.0326 0.9914 0.0177
-6.000 -0.2126 0.07014 0.06810 -0.0411 0.9859 0.0188
-5.750 -0.1605 0.06508 0.06294 -0.0561 0.9785 0.0194
-5.500 -0.1115 0.05977 0.05750 -0.0681 0.9720 0.0195
-5.250 -0.0868 0.05483 0.05254 -0.0718 0.9646 0.0197
-5.000 -0.0595 0.05132 0.04901 -0.0751 0.9568 0.0199
-4.750 -0.0276 0.04803 0.04565 -0.0795 0.9446 0.0203
-4.500 0.0084 0.04469 0.04222 -0.0847 0.9298 0.0209
-4.250 0.0440 0.04155 0.03893 -0.0893 0.9098 0.0219
-4.000 0.0823 0.03856 0.03568 -0.0932 0.8860 0.0233
-3.750 0.1200 0.03584 0.03258 -0.0957 0.8648 0.0237
-3.500 0.1480 0.03342 0.02986 -0.0966 0.8464 0.0237
-3.250 0.1680 0.03005 0.02639 -0.0973 0.8299 0.0240
-3.000 0.1895 0.02820 0.02445 -0.0975 0.8141 0.0244
-2.750 0.2132 0.02659 0.02269 -0.0978 0.7991 0.0248
-2.500 0.2387 0.02497 0.02089 -0.0979 0.7849 0.0254
-2.250 0.2651 0.02338 0.01910 -0.0980 0.7712 0.0262
-2.000 0.2927 0.02184 0.01734 -0.0978 0.7581 0.0275
-1.750 0.3249 0.02139 0.01636 -0.0968 0.7451 0.0289
-1.500 0.3493 0.01873 0.01354 -0.0969 0.7318 0.0295
-1.250 0.3741 0.01749 0.01220 -0.0969 0.7173 0.0301
-1.000 0.3996 0.01658 0.01116 -0.0966 0.7017 0.0310
-0.750 -0.4998 0.04168 0.03862 0.0631 0.7888 0.0237
-0.500 0.4534 0.01549 0.00962 -0.0955 0.6679 0.0348
1.500 -0.1826 0.01408 0.01011 -0.0189 0.7019 0.0246
2.000 0.7130 0.01074 0.00364 -0.0914 0.5055 0.0969
2.250 0.7408 0.01068 0.00345 -0.0905 0.4937 0.0655
2.500 0.7671 0.01045 0.00316 -0.0899 0.4812 0.0545
2.750 0.7929 0.01015 0.00284 -0.0893 0.4679 0.0488
3.000 0.8192 0.01017 0.00280 -0.0888 0.4548 0.0448
3.250 0.8453 0.01016 0.00277 -0.0884 0.4412 0.0432
3.500 0.8713 0.01016 0.00273 -0.0880 0.4276 0.0424
3.750 0.8973 0.01023 0.00274 -0.0875 0.4136 0.0424
4.000 0.9231 0.01034 0.00278 -0.0871 0.3997 0.0431
4.250 0.9486 0.01048 0.00285 -0.0866 0.3826 0.0461
4.500 0.9736 0.01070 0.00297 -0.0861 0.3608 0.0473
4.750 0.9985 0.01093 0.00312 -0.0856 0.3437 0.0494
5.000 1.0277 0.00970 0.00352 -0.0865 0.3292 1.0000
5.250 1.0526 0.00996 0.00372 -0.0859 0.3141 1.0000
5.500 1.0774 0.01023 0.00392 -0.0854 0.2978 1.0000
5.750 1.1021 0.01052 0.00412 -0.0849 0.2755 1.0000
6.000 1.1254 0.01094 0.00436 -0.0842 0.2406 1.0000
6.250 1.1438 0.01192 0.00488 -0.0830 0.1698 1.0000
6.500 1.1644 0.01265 0.00540 -0.0820 0.1359 1.0000
6.750 1.1848 0.01341 0.00590 -0.0809 0.0967 1.0000
7.000 1.2015 0.01457 0.00672 -0.0794 0.0463 1.0000
7.250 1.2205 0.01545 0.00746 -0.0780 0.0201 1.0000
7.500 1.2422 0.01600 0.00809 -0.0770 0.0182 1.0000
7.750 1.2634 0.01660 0.00876 -0.0760 0.0165 1.0000
8.000 1.2841 0.01723 0.00950 -0.0748 0.0155 1.0000
8.250 1.3042 0.01787 0.01024 -0.0736 0.0151 1.0000
8.500 1.3232 0.01860 0.01107 -0.0723 0.0147 1.0000
8.750 1.3407 0.01943 0.01200 -0.0707 0.0143 1.0000
9.000 1.3564 0.02035 0.01301 -0.0690 0.0139 1.0000
9.250 1.3701 0.02137 0.01412 -0.0669 0.0136 1.0000
9.500 1.3811 0.02251 0.01535 -0.0646 0.0131 1.0000
9.750 1.3884 0.02374 0.01666 -0.0617 0.0127 1.0000
10.000 1.3909 0.02501 0.01800 -0.0581 0.0124 1.0000
10.250 1.3888 0.02663 0.01970 -0.0542 0.0121 1.0000
10.500 1.3876 0.02836 0.02150 -0.0509 0.0119 1.0000
10.750 1.3866 0.03029 0.02351 -0.0480 0.0118 1.0000
11.000 1.3871 0.03241 0.02568 -0.0456 0.0117 1.0000
11.250 1.3916 0.03452 0.02784 -0.0437 0.0116 1.0000
11.500 1.4003 0.03646 0.02984 -0.0421 0.0116 1.0000
11.750 1.4138 0.03849 0.03191 -0.0409 0.0115 1.0000
12.000 1.4274 0.04032 0.03381 -0.0398 0.0116 1.0000
12.250 1.4395 0.04215 0.03573 -0.0386 0.0116 1.0000
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Polar data table (+)
Polar graphs
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