GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 562 AIRFOIL (goe562-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.28 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe562-il-1000000.txt Download as CSV file: xf-goe562-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 562 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0582 0.08527 0.08280 -0.1115 0.7833 0.0177
-11.000 0.0657 0.08160 0.07896 -0.1137 0.7484 0.0177
-10.750 0.0715 0.07805 0.07528 -0.1155 0.7216 0.0178
-10.500 0.0721 0.07369 0.07083 -0.1166 0.7013 0.0179
-10.250 0.0828 0.07138 0.06843 -0.1171 0.6806 0.0181
-10.000 0.0911 0.06894 0.06592 -0.1178 0.6660 0.0183
-9.750 0.0054 0.07803 0.07514 -0.1165 0.7128 0.0179
-9.500 0.0211 0.07693 0.07391 -0.1167 0.6871 0.0182
-9.250 0.0322 0.07458 0.07148 -0.1185 0.6701 0.0184
-9.000 0.0421 0.07173 0.06856 -0.1211 0.6566 0.0186
-8.750 0.0551 0.06962 0.06640 -0.1232 0.6450 0.0193
-8.250 0.0442 0.05939 0.05615 -0.1339 0.6298 0.0215
-8.000 0.0323 0.05527 0.05200 -0.1343 0.6232 0.0216
-7.750 0.0408 0.03471 0.03150 -0.1304 0.6059 0.0218
-7.500 0.0365 0.03211 0.02887 -0.1290 0.6006 0.0221
-7.250 0.0371 0.02971 0.02639 -0.1278 0.5953 0.0222
-7.000 0.0511 0.02929 0.02595 -0.1266 0.5894 0.0226
-6.750 0.0536 0.02672 0.02331 -0.1253 0.5847 0.0229
-6.500 0.0596 0.02467 0.02117 -0.1238 0.5798 0.0235
-6.250 0.0483 0.03460 0.03057 -0.1247 0.5849 0.0261
-6.000 0.0488 0.03142 0.02714 -0.1208 0.5803 0.0261
-5.250 0.0432 0.02121 0.01596 -0.1059 0.5679 0.0264
-5.000 0.0493 0.01879 0.01322 -0.1018 0.5632 0.0266
-4.750 0.1009 0.02337 0.01845 -0.1077 0.5561 0.0295
-4.500 0.1199 0.02306 0.01778 -0.1047 0.5512 0.0316
-4.250 0.1206 0.01925 0.01377 -0.1001 0.5473 0.0298
-4.000 0.1315 0.01714 0.01134 -0.0964 0.5432 0.0292
-3.750 0.1497 0.01607 0.01007 -0.0943 0.5380 0.0298
-3.500 0.1686 0.01499 0.00879 -0.0922 0.5330 0.0300
-3.250 0.1889 0.01413 0.00774 -0.0904 0.5269 0.0303
-3.000 0.2113 0.01343 0.00690 -0.0892 0.5221 0.0306
-2.750 0.2338 0.01303 0.00639 -0.0879 0.5166 0.0310
-2.500 0.2567 0.01317 0.00644 -0.0867 0.5120 0.0316
-2.250 0.2800 0.01212 0.00528 -0.0857 0.5076 0.0320
-2.000 0.3027 0.01145 0.00455 -0.0846 0.5021 0.0324
-1.750 0.3246 0.01108 0.00413 -0.0833 0.4972 0.0328
-1.500 0.3476 0.01078 0.00383 -0.0822 0.4933 0.0333
-1.250 0.3698 0.01055 0.00357 -0.0809 0.4889 0.0339
-1.000 0.3914 0.01038 0.00337 -0.0795 0.4843 0.0343
-0.750 0.4139 0.01027 0.00324 -0.0783 0.4802 0.0354
-0.500 0.4363 0.01010 0.00306 -0.0771 0.4760 0.0360
-0.250 0.4583 0.01000 0.00293 -0.0758 0.4712 0.0368
0.000 0.4795 0.00992 0.00280 -0.0743 0.4659 0.0376
0.250 0.5029 0.00984 0.00272 -0.0734 0.4623 0.0382
0.500 0.5246 0.00972 0.00256 -0.0720 0.4573 0.0388
0.750 0.5451 0.00959 0.00238 -0.0704 0.4524 0.0405
1.000 0.5681 0.00954 0.00233 -0.0694 0.4487 0.0419
1.250 0.5915 0.00950 0.00230 -0.0684 0.4448 0.0443
1.500 0.6143 0.00951 0.00228 -0.0673 0.4404 0.0464
1.750 0.6359 0.00951 0.00224 -0.0660 0.4363 0.0503
2.000 0.6592 0.00949 0.00224 -0.0651 0.4331 0.0563
2.250 0.6797 0.00923 0.00230 -0.0636 0.4297 0.1939
2.500 1.0062 0.00869 0.00348 -0.1322 0.4157 1.0000
2.750 1.0285 0.00877 0.00354 -0.1311 0.4118 1.0000
3.000 1.0500 0.00888 0.00361 -0.1299 0.4074 1.0000
3.250 1.0719 0.00897 0.00368 -0.1288 0.4037 1.0000
3.500 1.0945 0.00905 0.00375 -0.1278 0.3998 1.0000
3.750 1.1162 0.00914 0.00383 -0.1266 0.3955 1.0000
4.000 1.1369 0.00928 0.00393 -0.1253 0.3908 1.0000
4.250 1.1590 0.00936 0.00402 -0.1242 0.3869 1.0000
4.500 1.1806 0.00946 0.00412 -0.1230 0.3821 1.0000
4.750 1.2008 0.00961 0.00424 -0.1216 0.3769 1.0000
5.000 1.2218 0.00972 0.00435 -0.1203 0.3723 1.0000
5.250 1.2426 0.00984 0.00447 -0.1190 0.3660 1.0000
5.500 1.2615 0.01002 0.00461 -0.1173 0.3568 1.0000
5.750 1.2795 0.01021 0.00475 -0.1155 0.3471 1.0000
6.000 1.2966 0.01038 0.00490 -0.1134 0.3372 1.0000
6.250 1.3109 0.01062 0.00509 -0.1108 0.3239 1.0000
6.500 1.3233 0.01093 0.00531 -0.1078 0.3072 1.0000
6.750 1.3352 0.01126 0.00556 -0.1048 0.2918 1.0000
7.000 1.3456 0.01166 0.00587 -0.1016 0.2752 1.0000
7.250 1.3589 0.01196 0.00614 -0.0989 0.2656 1.0000
7.500 1.3709 0.01231 0.00644 -0.0959 0.2564 1.0000
7.750 1.3840 0.01263 0.00674 -0.0933 0.2482 1.0000
8.000 1.3977 0.01295 0.00704 -0.0908 0.2420 1.0000
8.250 1.4120 0.01324 0.00734 -0.0885 0.2363 1.0000
8.500 1.4234 0.01364 0.00772 -0.0856 0.2296 1.0000
8.750 1.4383 0.01394 0.00802 -0.0835 0.2246 1.0000
9.000 1.4503 0.01434 0.00841 -0.0808 0.2186 1.0000
9.250 1.4617 0.01476 0.00882 -0.0781 0.2103 1.0000
9.500 1.4717 0.01527 0.00931 -0.0753 0.2027 1.0000
9.750 1.4803 0.01583 0.00983 -0.0723 0.1907 1.0000
10.000 1.4764 0.01694 0.01077 -0.0674 0.1620 1.0000
10.250 1.4445 0.01942 0.01299 -0.0588 0.1092 1.0000
10.500 1.4170 0.02221 0.01563 -0.0522 0.0681 1.0000
10.750 1.4051 0.02451 0.01786 -0.0482 0.0466 1.0000
11.250 1.3916 0.02917 0.02245 -0.0430 0.0184 1.0000
11.500 1.3923 0.03117 0.02450 -0.0414 0.0162 1.0000
11.750 1.3955 0.03305 0.02645 -0.0402 0.0155 1.0000
12.000 1.3967 0.03519 0.02868 -0.0390 0.0147 1.0000
12.250 1.3975 0.03742 0.03097 -0.0380 0.0143 1.0000
12.500 1.3954 0.04001 0.03364 -0.0369 0.0137 1.0000
12.750 1.3897 0.04302 0.03674 -0.0359 0.0130 1.0000
13.000 1.3874 0.04572 0.03953 -0.0351 0.0126 1.0000
13.250 1.3855 0.04845 0.04233 -0.0344 0.0123 1.0000
13.500 1.3824 0.05136 0.04532 -0.0337 0.0118 1.0000
13.750 1.3773 0.05454 0.04859 -0.0332 0.0117 1.0000
14.000 1.3721 0.05779 0.05192 -0.0327 0.0114 1.0000
14.250 1.3675 0.06103 0.05524 -0.0324 0.0113 1.0000
14.500 1.3597 0.06474 0.05904 -0.0321 0.0109 1.0000
14.750 1.3510 0.06863 0.06302 -0.0319 0.0108 1.0000
15.000 1.3418 0.07264 0.06710 -0.0318 0.0105 1.0000
15.250 1.3322 0.07680 0.07135 -0.0319 0.0104 1.0000
15.500 1.3138 0.08222 0.07689 -0.0321 0.0101 1.0000
15.750 1.3030 0.08666 0.08143 -0.0324 0.0100 1.0000
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Polar data table (+)
Polar graphs
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