GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 797 AIRFOIL (goe797-il) Reynolds number: 100,000 Max Cl/Cd: 50.33 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe797-il-100000-n5.txt Download as CSV file: xf-goe797-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 797 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3105 0.14241 0.13677 -0.0530 1.0000 0.0619
-12.750 -0.3050 0.14025 0.13464 -0.0517 1.0000 0.0615
-12.500 -0.3043 0.13803 0.13247 -0.0507 1.0000 0.0611
-12.250 -0.3072 0.13574 0.13022 -0.0497 1.0000 0.0608
-12.000 -0.3143 0.13327 0.12781 -0.0489 1.0000 0.0608
-11.750 -0.3127 0.12863 0.12316 -0.0522 0.9973 0.0612
-11.500 -0.3058 0.12337 0.11788 -0.0567 0.9939 0.0614
-11.250 -0.2969 0.11852 0.11301 -0.0605 0.9899 0.0613
-11.000 -0.2889 0.11350 0.10797 -0.0645 0.9857 0.0612
-10.750 -0.2822 0.10799 0.10245 -0.0692 0.9823 0.0613
-10.500 -0.2886 0.10057 0.09500 -0.0749 0.9760 0.0619
-10.250 -0.2735 0.09704 0.09147 -0.0784 0.9721 0.0628
-10.000 -0.2589 0.09390 0.08832 -0.0814 0.9668 0.0636
-9.750 -0.2515 0.08901 0.08343 -0.0858 0.9612 0.0641
-9.500 -0.2516 0.08315 0.07756 -0.0907 0.9540 0.0645
-9.250 -0.2578 0.07605 0.07045 -0.0969 0.9460 0.0650
-9.000 -0.3687 0.05209 0.04603 -0.1144 0.9198 0.0654
-8.750 -0.3798 0.04627 0.03977 -0.1161 0.9091 0.0668
-8.500 -0.3784 0.04147 0.03444 -0.1170 0.9008 0.0686
-8.250 -0.3747 0.03767 0.03005 -0.1163 0.8911 0.0704
-8.000 -0.3577 0.03482 0.02671 -0.1165 0.8848 0.0719
-7.750 -0.3326 0.03375 0.02559 -0.1168 0.8795 0.0732
-7.500 -0.3116 0.03300 0.02478 -0.1162 0.8714 0.0747
-7.250 -0.2846 0.03193 0.02354 -0.1167 0.8666 0.0770
-7.000 -0.2634 0.03072 0.02206 -0.1162 0.8594 0.0796
-6.750 -0.2404 0.02928 0.02023 -0.1160 0.8529 0.0823
-6.500 -0.2121 0.02821 0.01906 -0.1165 0.8488 0.0847
-6.250 -0.1887 0.02780 0.01864 -0.1160 0.8419 0.0871
-6.000 -0.1628 0.02722 0.01795 -0.1159 0.8359 0.0903
-5.750 -0.1335 0.02631 0.01681 -0.1163 0.8318 0.0944
-5.500 -0.1092 0.02560 0.01591 -0.1159 0.8255 0.0979
-5.250 -0.0834 0.02523 0.01557 -0.1157 0.8197 0.1014
-5.000 -0.0540 0.02472 0.01497 -0.1161 0.8157 0.1061
-4.750 -0.0263 0.02417 0.01420 -0.1161 0.8109 0.1116
-4.500 -0.0020 0.02381 0.01385 -0.1156 0.8045 0.1160
-4.250 0.0267 0.02343 0.01342 -0.1158 0.8001 0.1217
-4.000 0.0580 0.02296 0.01272 -0.1163 0.7969 0.1288
-3.750 0.0807 0.02276 0.01261 -0.1157 0.7905 0.1340
-3.500 0.1080 0.02247 0.01225 -0.1156 0.7856 0.1411
-3.250 0.1379 0.02207 0.01179 -0.1160 0.7818 0.1482
-3.000 0.1659 0.02181 0.01151 -0.1161 0.7777 0.1558
-2.750 0.1900 0.02167 0.01135 -0.1155 0.7719 0.1630
-2.500 0.2179 0.02142 0.01111 -0.1156 0.7675 0.1711
-2.250 0.2483 0.02110 0.01077 -0.1160 0.7641 0.1800
-2.000 0.2739 0.02099 0.01068 -0.1157 0.7592 0.1889
-1.750 0.2985 0.02089 0.01063 -0.1152 0.7538 0.1977
-1.500 0.3270 0.02072 0.01044 -0.1153 0.7497 0.2086
-1.250 0.3577 0.02042 0.01019 -0.1158 0.7463 0.2201
-1.000 0.3807 0.02043 0.01026 -0.1150 0.7399 0.2329
-0.750 0.4073 0.02027 0.01015 -0.1147 0.7338 0.2503
-0.500 0.4390 0.01988 0.00982 -0.1152 0.7289 0.2760
-0.250 0.4613 0.01980 0.00988 -0.1142 0.7205 0.3098
0.250 0.5139 0.01875 0.00963 -0.1134 0.7069 0.5284
0.500 0.5305 0.01827 0.00987 -0.1104 0.6996 0.7351
0.750 0.5754 0.01799 0.00982 -0.1125 0.6948 0.9263
1.000 0.6259 0.01805 0.00979 -0.1172 0.6891 1.0000
1.250 0.6460 0.01827 0.00993 -0.1158 0.6823 1.0000
1.500 0.6728 0.01833 0.00985 -0.1156 0.6771 1.0000
1.750 0.6967 0.01849 0.00992 -0.1148 0.6714 1.0000
2.000 0.7171 0.01873 0.01013 -0.1135 0.6643 1.0000
2.250 0.7450 0.01877 0.01005 -0.1134 0.6587 1.0000
2.500 0.7665 0.01899 0.01024 -0.1123 0.6517 1.0000
2.750 0.7895 0.01916 0.01036 -0.1114 0.6444 1.0000
3.000 0.8192 0.01915 0.01024 -0.1116 0.6389 1.0000
3.250 0.8359 0.01950 0.01063 -0.1097 0.6300 1.0000
3.500 0.8633 0.01956 0.01061 -0.1095 0.6236 1.0000
3.750 0.8830 0.01983 0.01089 -0.1081 0.6152 1.0000
4.000 0.9079 0.01994 0.01095 -0.1075 0.6075 1.0000
4.250 0.9285 0.02017 0.01118 -0.1062 0.5985 1.0000
4.500 0.9528 0.02027 0.01124 -0.1055 0.5899 1.0000
4.750 0.9718 0.02054 0.01153 -0.1040 0.5797 1.0000
5.000 0.9981 0.02058 0.01151 -0.1035 0.5712 1.0000
5.250 1.0144 0.02095 0.01191 -0.1016 0.5599 1.0000
5.500 1.0363 0.02115 0.01209 -0.1005 0.5499 1.0000
5.750 1.0578 0.02135 0.01226 -0.0994 0.5394 1.0000
6.000 1.0752 0.02169 0.01261 -0.0976 0.5276 1.0000
6.250 1.0954 0.02195 0.01284 -0.0963 0.5164 1.0000
6.500 1.1163 0.02218 0.01302 -0.0951 0.5052 1.0000
6.750 1.1310 0.02259 0.01343 -0.0929 0.4928 1.0000
7.000 1.1475 0.02298 0.01378 -0.0910 0.4812 1.0000
7.250 1.1661 0.02333 0.01406 -0.0895 0.4698 1.0000
7.500 1.1814 0.02382 0.01450 -0.0875 0.4578 1.0000
7.750 1.1963 0.02436 0.01502 -0.0856 0.4461 1.0000
8.000 1.2132 0.02487 0.01547 -0.0840 0.4354 1.0000
8.250 1.2289 0.02546 0.01603 -0.0823 0.4251 1.0000
8.500 1.2441 0.02610 0.01666 -0.0806 0.4154 1.0000
8.750 1.2612 0.02668 0.01718 -0.0792 0.4064 1.0000
9.000 1.2749 0.02744 0.01798 -0.0774 0.3974 1.0000
9.250 1.2929 0.02804 0.01854 -0.0762 0.3900 1.0000
9.500 1.3073 0.02883 0.01938 -0.0747 0.3826 1.0000
9.750 1.3233 0.02955 0.02012 -0.0734 0.3755 1.0000
10.000 1.3393 0.03029 0.02087 -0.0721 0.3686 1.0000
10.250 1.3517 0.03120 0.02185 -0.0704 0.3611 1.0000
10.500 1.3694 0.03188 0.02247 -0.0693 0.3544 1.0000
10.750 1.3786 0.03297 0.02372 -0.0675 0.3470 1.0000
11.000 1.3929 0.03382 0.02457 -0.0661 0.3401 1.0000
11.250 1.4035 0.03490 0.02573 -0.0645 0.3330 1.0000
11.500 1.4127 0.03605 0.02695 -0.0628 0.3253 1.0000
11.750 1.4239 0.03711 0.02804 -0.0613 0.3181 1.0000
12.000 1.4292 0.03855 0.02961 -0.0595 0.3100 1.0000
12.250 1.4398 0.03966 0.03071 -0.0581 0.3027 1.0000
12.500 1.4414 0.04145 0.03268 -0.0562 0.2941 1.0000
12.750 1.4484 0.04283 0.03406 -0.0547 0.2862 1.0000
13.000 1.4479 0.04491 0.03632 -0.0529 0.2768 1.0000
13.250 1.4512 0.04668 0.03814 -0.0515 0.2683 1.0000
13.500 1.4507 0.04889 0.04048 -0.0500 0.2587 1.0000
13.750 1.4510 0.05114 0.04281 -0.0487 0.2493 1.0000
14.000 1.4511 0.05341 0.04511 -0.0475 0.2402 1.0000
14.250 1.4495 0.05604 0.04788 -0.0465 0.2306 1.0000
14.500 1.4491 0.05856 0.05042 -0.0456 0.2221 1.0000
14.750 1.4476 0.06129 0.05321 -0.0447 0.2135 1.0000
15.000 1.4467 0.06402 0.05598 -0.0440 0.2060 1.0000
15.250 1.4454 0.06681 0.05880 -0.0433 0.1990 1.0000
15.500 1.4448 0.06961 0.06164 -0.0428 0.1927 1.0000
15.750 1.4437 0.07252 0.06461 -0.0423 0.1867 1.0000
16.000 1.4448 0.07511 0.06717 -0.0419 0.1816 1.0000
16.250 1.4429 0.07828 0.07047 -0.0416 0.1761 1.0000
16.500 1.4437 0.08099 0.07319 -0.0413 0.1712 1.0000
16.750 1.4447 0.08375 0.07599 -0.0411 0.1664 1.0000
17.000 1.4413 0.08724 0.07961 -0.0412 0.1614 1.0000
17.250 1.4433 0.08983 0.08218 -0.0411 0.1565 1.0000
17.500 1.4404 0.09329 0.08577 -0.0414 0.1519 1.0000
17.750 1.4346 0.09728 0.08989 -0.0420 0.1470 1.0000
18.000 1.4355 0.10010 0.09270 -0.0423 0.1422 1.0000
18.250 1.4282 0.10447 0.09722 -0.0432 0.1377 1.0000
18.500 1.4193 0.10917 0.10208 -0.0445 0.1330 1.0000
18.750 1.4170 0.11270 0.10563 -0.0455 0.1284 1.0000
19.000 1.4096 0.11725 0.11030 -0.0470 0.1241 1.0000
19.250 1.3977 0.12274 0.11599 -0.0491 0.1195 1.0000
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