GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 500,000 Max Cl/Cd: 96.02 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe376-il-500000-n5.txt Download as CSV file: xf-goe376-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3132 0.09273 0.09058 -0.0209 1.0000 0.0089
-7.750 -0.3144 0.09032 0.08820 -0.0204 1.0000 0.0089
-7.500 -0.3135 0.08772 0.08564 -0.0208 0.9993 0.0088
-7.250 -0.2942 0.08333 0.08125 -0.0268 0.9935 0.0088
-6.750 -0.2540 0.07399 0.07190 -0.0392 0.9749 0.0092
-6.500 -0.2339 0.07022 0.06811 -0.0441 0.9601 0.0099
-6.250 -0.2047 0.06656 0.06442 -0.0503 0.9469 0.0104
-6.000 -0.1642 0.06170 0.05948 -0.0600 0.9361 0.0115
-5.750 -0.1110 0.05358 0.05119 -0.0749 0.9237 0.0124
-5.500 -0.0697 0.05082 0.04831 -0.0816 0.9089 0.0129
-5.250 -0.0352 0.04782 0.04517 -0.0869 0.8904 0.0144
-5.000 -0.0073 0.04395 0.04113 -0.0907 0.8718 0.0150
-4.750 0.0198 0.03968 0.03662 -0.0938 0.8539 0.0159
-4.500 0.0414 0.03812 0.03495 -0.0943 0.8360 0.0164
-4.250 0.0643 0.03624 0.03292 -0.0949 0.8173 0.0173
-3.750 0.1161 0.03008 0.02620 -0.0961 0.7802 0.0200
-3.500 0.1366 0.02918 0.02520 -0.0958 0.7635 0.0207
-3.250 0.1670 0.02800 0.02372 -0.0954 0.7492 0.0242
-3.000 0.1913 0.02589 0.02134 -0.0948 0.7358 0.0243
-2.750 0.2149 0.02400 0.01918 -0.0941 0.7226 0.0243
-2.500 0.2388 0.02237 0.01727 -0.0934 0.7100 0.0244
-2.250 0.2597 0.01980 0.01448 -0.0928 0.6986 0.0251
-2.000 0.2827 0.01895 0.01356 -0.0924 0.6865 0.0258
-1.750 0.3068 0.01807 0.01253 -0.0919 0.6738 0.0266
-1.500 0.3315 0.01703 0.01128 -0.0911 0.6604 0.0273
-1.250 0.3562 0.01609 0.01011 -0.0902 0.6440 0.0282
-1.000 0.3806 0.01520 0.00896 -0.0892 0.6241 0.0286
-0.750 0.4048 0.01438 0.00788 -0.0882 0.5991 0.0282
-0.500 0.4290 0.01376 0.00701 -0.0872 0.5732 0.0283
-0.250 0.4537 0.01341 0.00644 -0.0863 0.5489 0.0293
0.250 0.5030 0.01220 0.00482 -0.0846 0.5059 0.0270
0.500 0.5280 0.01182 0.00426 -0.0839 0.4883 0.0265
1.000 0.5782 0.01128 0.00351 -0.0825 0.4596 0.0268
1.250 0.6033 0.01109 0.00325 -0.0819 0.4471 0.0272
1.500 0.6284 0.01094 0.00305 -0.0813 0.4363 0.0276
1.750 0.6535 0.01084 0.00289 -0.0806 0.4272 0.0281
2.000 0.6788 0.01073 0.00277 -0.0800 0.4187 0.0284
2.250 0.7040 0.01074 0.00275 -0.0795 0.4099 0.0298
2.500 0.7289 0.01073 0.00270 -0.0789 0.3987 0.0302
2.750 0.7539 0.01068 0.00264 -0.0782 0.3876 0.0302
3.000 0.7787 0.01068 0.00260 -0.0776 0.3753 0.0301
3.250 0.8036 0.01070 0.00260 -0.0770 0.3639 0.0302
3.500 0.8287 0.01075 0.00263 -0.0764 0.3535 0.0303
3.750 0.8538 0.01080 0.00267 -0.0759 0.3420 0.0307
4.000 0.8786 0.01089 0.00273 -0.0753 0.3287 0.0313
4.250 0.9032 0.01101 0.00278 -0.0747 0.3137 0.0326
4.500 0.9277 0.01117 0.00289 -0.0740 0.2984 0.0342
4.750 0.9519 0.01136 0.00303 -0.0734 0.2835 0.0368
5.000 0.9761 0.01156 0.00319 -0.0727 0.2701 0.0398
5.250 0.9997 0.01182 0.00341 -0.0720 0.2537 0.0439
5.750 1.0841 0.01129 0.00431 -0.0798 0.2093 1.0000
6.000 1.1063 0.01166 0.00461 -0.0788 0.1921 1.0000
6.250 1.1285 0.01203 0.00489 -0.0779 0.1758 1.0000
6.500 1.1500 0.01246 0.00521 -0.0769 0.1529 1.0000
6.750 1.1701 0.01300 0.00560 -0.0756 0.1269 1.0000
7.000 1.1884 0.01370 0.00612 -0.0741 0.0959 1.0000
7.250 1.1972 0.01529 0.00724 -0.0712 0.0220 1.0000
7.500 1.2168 0.01586 0.00780 -0.0698 0.0150 1.0000
7.750 1.2376 0.01629 0.00831 -0.0687 0.0134 1.0000
8.000 1.2576 0.01680 0.00889 -0.0674 0.0120 1.0000
8.250 1.2761 0.01742 0.00961 -0.0658 0.0105 1.0000
8.500 1.2946 0.01801 0.01029 -0.0643 0.0096 1.0000
8.750 1.3133 0.01855 0.01091 -0.0629 0.0089 1.0000
9.000 1.3307 0.01918 0.01162 -0.0613 0.0084 1.0000
9.250 1.3471 0.01985 0.01237 -0.0596 0.0079 1.0000
9.500 1.3618 0.02060 0.01321 -0.0576 0.0074 1.0000
9.750 1.3731 0.02155 0.01425 -0.0552 0.0070 1.0000
10.000 1.3785 0.02266 0.01546 -0.0517 0.0066 1.0000
10.250 1.3901 0.02333 0.01622 -0.0493 0.0064 1.0000
10.500 1.3992 0.02418 0.01716 -0.0467 0.0061 1.0000
10.750 1.4061 0.02520 0.01827 -0.0439 0.0058 1.0000
11.000 1.4107 0.02641 0.01961 -0.0411 0.0056 1.0000
11.250 1.4179 0.02751 0.02079 -0.0389 0.0054 1.0000
11.500 1.4191 0.02911 0.02251 -0.0364 0.0053 1.0000
11.750 1.4231 0.03063 0.02411 -0.0345 0.0051 1.0000
12.000 1.4247 0.03245 0.02604 -0.0327 0.0050 1.0000
12.250 1.4232 0.03471 0.02842 -0.0311 0.0049 1.0000
12.500 1.4231 0.03702 0.03083 -0.0301 0.0047 1.0000
12.750 1.4202 0.03980 0.03373 -0.0293 0.0047 1.0000
13.000 1.4145 0.04309 0.03715 -0.0289 0.0046 1.0000
13.250 1.4088 0.04656 0.04074 -0.0289 0.0046 1.0000
13.500 1.3947 0.05124 0.04556 -0.0292 0.0044 1.0000
13.750 1.3903 0.05487 0.04931 -0.0297 0.0044 1.0000
14.000 1.3840 0.05887 0.05344 -0.0303 0.0044 1.0000
14.250 1.3774 0.06303 0.05773 -0.0312 0.0043 1.0000
14.500 1.3707 0.06731 0.06213 -0.0322 0.0043 1.0000
14.750 1.3630 0.07183 0.06678 -0.0333 0.0043 1.0000
15.000 1.3563 0.07631 0.07138 -0.0346 0.0042 1.0000
15.250 1.3486 0.08104 0.07623 -0.0360 0.0041 1.0000
15.500 1.3408 0.08581 0.08112 -0.0374 0.0041 1.0000
15.750 1.3331 0.09072 0.08615 -0.0390 0.0040 1.0000
16.000 1.3263 0.09560 0.09116 -0.0408 0.0039 1.0000
16.250 1.3186 0.10066 0.09634 -0.0426 0.0038 1.0000
16.500 1.3105 0.10579 0.10158 -0.0444 0.0039 1.0000
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Polar data table (+)
Polar graphs
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