GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 767 AIRFOIL (goe767-il) Reynolds number: 500,000 Max Cl/Cd: 74.66 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe767-il-500000-n5.txt Download as CSV file: xf-goe767-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 767 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
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9728 0.13231 0.12908 0.0145 1.0000 0.0251
-17.750 -1.0217 0.11766 0.11422 0.0053 1.0000 0.0254
-17.500 -1.0533 0.10724 0.10366 -0.0012 1.0000 0.0255
-17.250 -1.0853 0.09724 0.09350 -0.0074 1.0000 0.0256
-17.000 -1.1155 0.08804 0.08417 -0.0131 1.0000 0.0257
-16.750 -1.1450 0.07912 0.07510 -0.0187 1.0000 0.0257
-16.500 -1.1725 0.07068 0.06649 -0.0242 1.0000 0.0257
-16.250 -1.1955 0.06295 0.05861 -0.0293 1.0000 0.0258
-16.000 -1.2138 0.05606 0.05156 -0.0341 1.0000 0.0259
-15.750 -1.2274 0.05015 0.04550 -0.0382 1.0000 0.0260
-15.500 -1.2371 0.04530 0.04049 -0.0414 1.0000 0.0261
-15.250 -1.2444 0.04130 0.03635 -0.0435 1.0000 0.0262
-15.000 -1.2488 0.03813 0.03305 -0.0445 1.0000 0.0263
-14.750 -1.2509 0.03561 0.03041 -0.0447 1.0000 0.0265
-14.500 -1.2517 0.03352 0.02820 -0.0440 1.0000 0.0267
-14.250 -1.2503 0.03184 0.02641 -0.0427 1.0000 0.0268
-14.000 -1.2473 0.03044 0.02490 -0.0409 1.0000 0.0270
-13.750 -1.2427 0.02926 0.02361 -0.0387 1.0000 0.0272
-13.500 -1.2357 0.02830 0.02253 -0.0363 1.0000 0.0274
-13.250 -1.2303 0.02722 0.02138 -0.0336 1.0000 0.0276
-13.000 -1.2208 0.02612 0.02023 -0.0316 1.0000 0.0279
-12.750 -1.2080 0.02515 0.01922 -0.0298 1.0000 0.0281
-12.500 -1.1931 0.02428 0.01829 -0.0281 1.0000 0.0284
-12.250 -1.1768 0.02347 0.01742 -0.0266 1.0000 0.0286
-12.000 -1.1592 0.02271 0.01660 -0.0252 1.0000 0.0289
-11.750 -1.1408 0.02199 0.01583 -0.0239 1.0000 0.0292
-11.500 -1.1216 0.02130 0.01508 -0.0226 1.0000 0.0295
-11.250 -1.1016 0.02065 0.01438 -0.0214 1.0000 0.0299
-11.000 -1.0810 0.02004 0.01371 -0.0202 1.0000 0.0303
-10.750 -1.0598 0.01947 0.01307 -0.0191 1.0000 0.0307
-10.500 -1.0382 0.01891 0.01245 -0.0180 1.0000 0.0311
-10.250 -1.0164 0.01837 0.01185 -0.0169 1.0000 0.0314
-10.000 -0.9956 0.01770 0.01116 -0.0157 1.0000 0.0318
-9.750 -0.9739 0.01712 0.01056 -0.0146 1.0000 0.0323
-9.500 -0.9515 0.01660 0.01002 -0.0135 1.0000 0.0328
-9.250 -0.9286 0.01613 0.00951 -0.0125 1.0000 0.0333
-9.000 -0.9055 0.01568 0.00904 -0.0115 1.0000 0.0338
-8.750 -0.8822 0.01526 0.00859 -0.0105 1.0000 0.0344
-8.500 -0.8587 0.01486 0.00816 -0.0095 1.0000 0.0350
-8.250 -0.8351 0.01448 0.00775 -0.0084 1.0000 0.0358
-8.000 -0.8119 0.01403 0.00731 -0.0074 1.0000 0.0367
-7.750 -0.7885 0.01365 0.00691 -0.0063 1.0000 0.0378
-7.500 -0.7648 0.01330 0.00656 -0.0053 1.0000 0.0389
-7.250 -0.7409 0.01298 0.00622 -0.0042 1.0000 0.0402
-7.000 -0.7174 0.01260 0.00587 -0.0032 1.0000 0.0422
-6.750 -0.6937 0.01228 0.00556 -0.0021 1.0000 0.0447
-6.500 -0.6635 0.01190 0.00523 -0.0024 0.9937 0.0496
-6.250 -0.6261 0.01152 0.00492 -0.0043 0.9788 0.0587
-6.000 -0.5770 0.01120 0.00466 -0.0085 0.9400 0.0702
-5.750 -0.5336 0.01117 0.00439 -0.0112 0.8231 0.0780
-5.500 -0.5139 0.01147 0.00420 -0.0090 0.6782 0.0818
-5.250 -0.4896 0.01156 0.00404 -0.0080 0.6122 0.0859
-5.000 -0.4636 0.01158 0.00388 -0.0073 0.5720 0.0890
-4.750 -0.4375 0.01151 0.00372 -0.0067 0.5419 0.0922
-4.500 -0.4108 0.01143 0.00357 -0.0061 0.5199 0.0954
-4.250 -0.3837 0.01137 0.00343 -0.0056 0.5015 0.0986
-4.000 -0.3568 0.01128 0.00329 -0.0051 0.4847 0.1022
-3.500 -0.3027 0.01110 0.00303 -0.0042 0.4548 0.1095
-3.250 -0.2753 0.01105 0.00290 -0.0037 0.4413 0.1120
-3.000 -0.2484 0.01094 0.00277 -0.0032 0.4279 0.1163
-2.750 -0.2212 0.01086 0.00267 -0.0028 0.4144 0.1210
-2.500 -0.1938 0.01080 0.00257 -0.0024 0.4027 0.1250
-2.250 -0.1667 0.01071 0.00247 -0.0019 0.3918 0.1312
-2.000 -0.1392 0.01064 0.00238 -0.0015 0.3815 0.1370
-1.750 -0.1119 0.01057 0.00231 -0.0011 0.3716 0.1439
-1.500 -0.0844 0.01051 0.00224 -0.0006 0.3615 0.1533
-1.250 -0.0572 0.01043 0.00218 -0.0002 0.3522 0.1646
-1.000 -0.0298 0.01037 0.00213 0.0002 0.3424 0.1773
-0.750 -0.0024 0.01031 0.00208 0.0006 0.3335 0.1914
-0.500 0.0248 0.01023 0.00204 0.0010 0.3238 0.2090
-0.250 0.0516 0.01011 0.00200 0.0015 0.3145 0.2392
0.000 0.0778 0.00991 0.00198 0.0020 0.3047 0.2982
0.250 0.1044 0.00978 0.00197 0.0025 0.2966 0.3462
0.500 0.1308 0.00964 0.00197 0.0030 0.2882 0.3952
0.750 0.1569 0.00949 0.00198 0.0035 0.2803 0.4524
1.000 0.1823 0.00929 0.00200 0.0042 0.2716 0.5243
1.250 0.2070 0.00910 0.00204 0.0051 0.2635 0.6033
1.500 0.2319 0.00896 0.00210 0.0061 0.2555 0.6721
1.750 0.2572 0.00891 0.00216 0.0069 0.2481 0.7192
2.000 0.2826 0.00883 0.00224 0.0078 0.2419 0.7672
2.250 0.3071 0.00876 0.00234 0.0090 0.2359 0.8271
2.500 0.3352 0.00873 0.00249 0.0096 0.2314 0.8918
2.750 0.3735 0.00882 0.00263 0.0080 0.2266 0.9350
3.000 0.4117 0.00897 0.00275 0.0062 0.2213 0.9547
3.250 0.4493 0.00915 0.00288 0.0044 0.2166 0.9663
3.500 0.4875 0.00927 0.00300 0.0026 0.2132 0.9748
3.750 0.5275 0.00942 0.00313 0.0003 0.2087 0.9850
4.000 0.5684 0.00960 0.00326 -0.0022 0.2035 0.9930
4.250 0.6065 0.00974 0.00337 -0.0041 0.1988 0.9973
4.500 0.6417 0.00985 0.00348 -0.0054 0.1946 1.0000
4.750 0.6656 0.00998 0.00360 -0.0045 0.1902 1.0000
5.000 0.6894 0.01016 0.00374 -0.0035 0.1854 1.0000
5.250 0.7137 0.01029 0.00388 -0.0025 0.1807 1.0000
5.500 0.7379 0.01045 0.00401 -0.0016 0.1743 1.0000
5.750 0.7621 0.01063 0.00417 -0.0007 0.1683 1.0000
6.000 0.7865 0.01081 0.00434 0.0002 0.1610 1.0000
6.250 0.8106 0.01103 0.00451 0.0010 0.1534 1.0000
6.750 0.8585 0.01154 0.00495 0.0028 0.1371 1.0000
7.000 0.8822 0.01185 0.00521 0.0037 0.1303 1.0000
7.250 0.9061 0.01214 0.00549 0.0046 0.1248 1.0000
7.500 0.9295 0.01249 0.00580 0.0055 0.1194 1.0000
7.750 0.9534 0.01277 0.00608 0.0063 0.1150 1.0000
8.000 0.9767 0.01313 0.00642 0.0072 0.1103 1.0000
8.250 1.0003 0.01345 0.00675 0.0080 0.1069 1.0000
8.500 1.0243 0.01374 0.00706 0.0088 0.1043 1.0000
8.750 1.0479 0.01407 0.00741 0.0097 0.1017 1.0000
9.000 1.0711 0.01444 0.00778 0.0105 0.0991 1.0000
9.250 1.0944 0.01481 0.00816 0.0113 0.0968 1.0000
9.500 1.1183 0.01511 0.00852 0.0121 0.0946 1.0000
9.750 1.1417 0.01546 0.00889 0.0128 0.0919 1.0000
10.000 1.1644 0.01586 0.00930 0.0137 0.0893 1.0000
10.250 1.1869 0.01629 0.00975 0.0145 0.0869 1.0000
10.500 1.2101 0.01663 0.01015 0.0152 0.0847 1.0000
10.750 1.2327 0.01703 0.01058 0.0161 0.0821 1.0000
11.000 1.2543 0.01750 0.01106 0.0169 0.0793 1.0000
11.250 1.2761 0.01795 0.01155 0.0178 0.0769 1.0000
11.500 1.2977 0.01839 0.01203 0.0186 0.0739 1.0000
11.750 1.3178 0.01894 0.01259 0.0196 0.0706 1.0000
12.000 1.3381 0.01945 0.01315 0.0206 0.0676 1.0000
12.250 1.3571 0.02004 0.01375 0.0216 0.0641 1.0000
12.500 1.3751 0.02068 0.01442 0.0228 0.0611 1.0000
12.750 1.3920 0.02135 0.01514 0.0241 0.0578 1.0000
13.000 1.4070 0.02212 0.01593 0.0255 0.0551 1.0000
13.250 1.4209 0.02290 0.01676 0.0270 0.0525 1.0000
13.500 1.4307 0.02381 0.01771 0.0289 0.0503 1.0000
13.750 1.4364 0.02474 0.01870 0.0315 0.0486 1.0000
14.000 1.4401 0.02583 0.01985 0.0338 0.0471 1.0000
14.250 1.4405 0.02728 0.02138 0.0357 0.0456 1.0000
14.500 1.4380 0.02925 0.02342 0.0369 0.0447 1.0000
14.750 1.4338 0.03188 0.02617 0.0367 0.0438 1.0000
15.000 1.4285 0.03545 0.02987 0.0349 0.0431 1.0000
15.250 1.4197 0.04004 0.03460 0.0321 0.0423 1.0000
15.500 1.4064 0.04524 0.03994 0.0292 0.0419 1.0000
15.750 1.3883 0.05096 0.04579 0.0262 0.0415 1.0000
16.000 1.3667 0.05706 0.05202 0.0232 0.0412 1.0000
16.250 1.3421 0.06353 0.05861 0.0201 0.0409 1.0000
16.500 1.3187 0.06990 0.06509 0.0170 0.0406 1.0000
16.750 1.2959 0.07630 0.07159 0.0139 0.0404 1.0000
17.000 1.2750 0.08273 0.07812 0.0107 0.0400 1.0000
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