GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.76 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe549-il-1000000-n5.txt Download as CSV file: xf-goe549-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9029 0.03461 0.03185 -0.0977 1.0000 0.0104
-14.000 -0.9146 0.03023 0.02725 -0.1017 0.9827 0.0105
-13.750 -0.8906 0.02753 0.02434 -0.1065 0.9629 0.0106
-13.500 -0.8536 0.02519 0.02178 -0.1124 0.9479 0.0106
-13.250 -0.8197 0.02341 0.01976 -0.1166 0.9243 0.0107
-13.000 -0.8026 0.02230 0.01842 -0.1164 0.8973 0.0108
-12.750 -0.7891 0.02141 0.01735 -0.1149 0.8793 0.0108
-12.500 -0.7746 0.02054 0.01632 -0.1135 0.8663 0.0109
-12.250 -0.7584 0.01975 0.01538 -0.1122 0.8543 0.0110
-12.000 -0.7407 0.01900 0.01449 -0.1111 0.8446 0.0111
-11.750 -0.7220 0.01831 0.01367 -0.1100 0.8351 0.0112
-11.500 -0.7023 0.01765 0.01289 -0.1090 0.8254 0.0113
-11.250 -0.6818 0.01704 0.01216 -0.1081 0.8165 0.0114
-11.000 -0.6607 0.01646 0.01148 -0.1072 0.8071 0.0117
-10.750 -0.6384 0.01597 0.01090 -0.1065 0.7975 0.0119
-10.500 -0.6155 0.01557 0.01042 -0.1058 0.7863 0.0122
-10.250 -0.5919 0.01526 0.01004 -0.1051 0.7727 0.0125
-10.000 -0.5684 0.01493 0.00962 -0.1044 0.7565 0.0128
-9.750 -0.5447 0.01464 0.00922 -0.1037 0.7357 0.0132
-9.500 -0.5218 0.01439 0.00882 -0.1029 0.7060 0.0137
-9.250 -0.4991 0.01413 0.00839 -0.1020 0.6763 0.0141
-9.000 -0.4757 0.01382 0.00794 -0.1013 0.6573 0.0145
-8.750 -0.4502 0.01369 0.00775 -0.1008 0.6448 0.0149
-8.500 -0.4241 0.01359 0.00760 -0.1005 0.6353 0.0154
-8.250 -0.3978 0.01346 0.00742 -0.1002 0.6282 0.0159
-8.000 -0.3716 0.01332 0.00722 -0.0999 0.6214 0.0165
-7.750 -0.3457 0.01311 0.00695 -0.0995 0.6160 0.0172
-7.500 -0.3195 0.01289 0.00666 -0.0992 0.6115 0.0177
-7.250 -0.2933 0.01268 0.00638 -0.0989 0.6068 0.0180
-6.750 -0.2410 0.01223 0.00585 -0.0983 0.5987 0.0189
-6.500 -0.2139 0.01210 0.00570 -0.0981 0.5952 0.0193
-6.250 -0.1871 0.01195 0.00552 -0.0979 0.5913 0.0197
-6.000 -0.1605 0.01179 0.00532 -0.0976 0.5875 0.0201
-5.750 -0.1337 0.01162 0.00511 -0.0974 0.5843 0.0206
-5.500 -0.1069 0.01141 0.00486 -0.0972 0.5812 0.0210
-5.250 -0.0799 0.01123 0.00465 -0.0969 0.5777 0.0215
-5.000 -0.0530 0.01107 0.00445 -0.0967 0.5742 0.0219
-4.750 -0.0264 0.01090 0.00423 -0.0964 0.5709 0.0222
-4.500 0.0009 0.01077 0.00407 -0.0963 0.5678 0.0224
-4.250 0.0281 0.01060 0.00387 -0.0961 0.5645 0.0227
-4.000 0.0540 0.01026 0.00350 -0.0957 0.5609 0.0236
-3.750 0.0807 0.01009 0.00331 -0.0955 0.5568 0.0241
-3.500 0.1078 0.00997 0.00317 -0.0953 0.5528 0.0248
-3.250 0.1351 0.00981 0.00299 -0.0951 0.5487 0.0252
-3.000 0.1622 0.00966 0.00281 -0.0949 0.5445 0.0255
-2.750 0.1892 0.00954 0.00265 -0.0947 0.5404 0.0259
-2.500 0.2164 0.00942 0.00249 -0.0945 0.5369 0.0263
-2.250 0.2440 0.00930 0.00236 -0.0944 0.5333 0.0268
-2.000 0.2714 0.00920 0.00225 -0.0942 0.5290 0.0273
-1.750 0.2986 0.00912 0.00213 -0.0940 0.5249 0.0277
-1.500 0.3260 0.00905 0.00204 -0.0939 0.5211 0.0280
-1.250 0.3537 0.00898 0.00196 -0.0938 0.5168 0.0282
-1.000 0.3810 0.00890 0.00185 -0.0936 0.5122 0.0289
-0.750 0.4081 0.00885 0.00177 -0.0934 0.5077 0.0300
-0.500 0.4358 0.00880 0.00171 -0.0933 0.5031 0.0311
-0.250 0.4632 0.00877 0.00167 -0.0932 0.4979 0.0324
0.000 0.4904 0.00876 0.00164 -0.0930 0.4929 0.0342
0.250 0.5178 0.00872 0.00161 -0.0929 0.4882 0.0399
0.500 0.5439 0.00853 0.00159 -0.0926 0.4820 0.1084
0.750 0.5685 0.00820 0.00159 -0.0922 0.4764 0.2383
1.000 0.5945 0.00801 0.00161 -0.0919 0.4711 0.3167
1.250 0.6201 0.00787 0.00165 -0.0916 0.4649 0.3919
1.500 0.6457 0.00775 0.00170 -0.0912 0.4588 0.4632
1.750 0.6714 0.00768 0.00177 -0.0908 0.4516 0.5260
2.000 0.6971 0.00766 0.00185 -0.0904 0.4453 0.5744
2.250 0.7229 0.00763 0.00192 -0.0900 0.4388 0.6200
2.750 0.7684 0.00756 0.00212 -0.0880 0.4115 0.7588
3.000 0.8249 0.00740 0.00235 -0.0944 0.3907 0.9717
3.250 0.8664 0.00756 0.00245 -0.0976 0.3814 0.9927
3.750 0.9180 0.00793 0.00269 -0.0969 0.3601 1.0000
4.000 0.9406 0.00816 0.00283 -0.0960 0.3450 1.0000
4.250 0.9633 0.00839 0.00298 -0.0950 0.3316 1.0000
4.500 0.9858 0.00863 0.00315 -0.0941 0.3184 1.0000
4.750 1.0084 0.00886 0.00331 -0.0932 0.3065 1.0000
5.000 1.0307 0.00912 0.00349 -0.0922 0.2943 1.0000
5.250 1.0550 0.00926 0.00363 -0.0916 0.2898 1.0000
5.500 1.0781 0.00946 0.00379 -0.0908 0.2823 1.0000
5.750 1.1011 0.00967 0.00397 -0.0900 0.2741 1.0000
6.000 1.1229 0.00994 0.00418 -0.0889 0.2629 1.0000
6.250 1.1449 0.01019 0.00439 -0.0880 0.2528 1.0000
6.500 1.1667 0.01045 0.00460 -0.0870 0.2429 1.0000
6.750 1.1883 0.01071 0.00482 -0.0860 0.2356 1.0000
7.000 1.2084 0.01103 0.00509 -0.0847 0.2230 1.0000
7.250 1.2259 0.01146 0.00543 -0.0830 0.2054 1.0000
7.500 1.2442 0.01183 0.00574 -0.0815 0.1932 1.0000
8.000 1.2732 0.01274 0.00650 -0.0770 0.1621 1.0000
8.250 1.2580 0.01425 0.00765 -0.0699 0.0992 1.0000
8.500 1.2689 0.01484 0.00819 -0.0673 0.0870 1.0000
8.750 1.2810 0.01542 0.00874 -0.0650 0.0783 1.0000
9.000 1.2962 0.01588 0.00921 -0.0632 0.0737 1.0000
9.250 1.3114 0.01637 0.00971 -0.0616 0.0703 1.0000
9.500 1.3237 0.01703 0.01036 -0.0597 0.0643 1.0000
9.750 1.3392 0.01756 0.01092 -0.0582 0.0620 1.0000
10.000 1.3505 0.01834 0.01168 -0.0564 0.0554 1.0000
10.250 1.3477 0.02002 0.01321 -0.0532 0.0304 1.0000
10.500 1.3547 0.02122 0.01440 -0.0514 0.0226 1.0000
10.750 1.3653 0.02227 0.01547 -0.0500 0.0200 1.0000
11.000 1.3770 0.02328 0.01652 -0.0488 0.0188 1.0000
11.250 1.3869 0.02446 0.01773 -0.0476 0.0171 1.0000
11.500 1.3981 0.02560 0.01890 -0.0466 0.0168 1.0000
11.750 1.4077 0.02690 0.02025 -0.0456 0.0156 1.0000
12.000 1.4182 0.02818 0.02157 -0.0447 0.0154 1.0000
12.250 1.4276 0.02960 0.02305 -0.0439 0.0148 1.0000
12.500 1.4355 0.03118 0.02467 -0.0432 0.0141 1.0000
12.750 1.4431 0.03285 0.02639 -0.0425 0.0137 1.0000
13.000 1.4480 0.03483 0.02842 -0.0418 0.0126 1.0000
13.250 1.4547 0.03669 0.03033 -0.0413 0.0125 1.0000
13.500 1.4616 0.03854 0.03224 -0.0409 0.0119 1.0000
13.750 1.4674 0.04056 0.03434 -0.0405 0.0118 1.0000
14.000 1.4721 0.04272 0.03655 -0.0401 0.0110 1.0000
14.250 1.4758 0.04498 0.03887 -0.0398 0.0105 1.0000
14.500 1.4777 0.04744 0.04138 -0.0395 0.0097 1.0000
14.750 1.4801 0.04991 0.04391 -0.0392 0.0095 1.0000
15.000 1.4809 0.05255 0.04660 -0.0390 0.0091 1.0000
15.250 1.4815 0.05525 0.04937 -0.0388 0.0089 1.0000
15.500 1.4807 0.05815 0.05232 -0.0387 0.0085 1.0000
15.750 1.4797 0.06112 0.05534 -0.0386 0.0082 1.0000
16.000 1.4793 0.06404 0.05834 -0.0386 0.0081 1.0000
16.250 1.4775 0.06715 0.06152 -0.0386 0.0079 1.0000
16.500 1.4748 0.07043 0.06486 -0.0388 0.0077 1.0000
16.750 1.4721 0.07378 0.06829 -0.0390 0.0076 1.0000
17.000 1.4702 0.07704 0.07161 -0.0393 0.0075 1.0000
17.250 1.4665 0.08056 0.07521 -0.0396 0.0074 1.0000
17.500 1.4616 0.08428 0.07901 -0.0400 0.0072 1.0000
17.750 1.4563 0.08812 0.08293 -0.0406 0.0071 1.0000
18.000 1.4530 0.09172 0.08660 -0.0412 0.0071 1.0000
18.250 1.4475 0.09566 0.09062 -0.0419 0.0069 1.0000
18.500 1.4409 0.09980 0.09483 -0.0427 0.0067 1.0000
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