GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 646 AIRFOIL (goe646-il) Reynolds number: 100,000 Max Cl/Cd: 46.39 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe646-il-100000-n5.txt Download as CSV file: xf-goe646-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 646 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6379 0.07507 0.06869 -0.0803 1.0000 0.0755
-13.250 -0.6998 0.06627 0.05968 -0.0834 1.0000 0.0757
-13.000 -0.7426 0.06071 0.05395 -0.0843 1.0000 0.0761
-12.750 -0.7583 0.05762 0.05083 -0.0844 0.9992 0.0768
-12.500 -0.7421 0.05546 0.04869 -0.0872 0.9950 0.0783
-12.250 -0.7380 0.05182 0.04494 -0.0916 0.9893 0.0801
-12.000 -0.7366 0.04779 0.04068 -0.0967 0.9822 0.0819
-11.750 -0.7393 0.04403 0.03662 -0.1008 0.9726 0.0837
-11.500 -0.7254 0.04201 0.03455 -0.1033 0.9654 0.0855
-11.250 -0.7144 0.04047 0.03298 -0.1039 0.9567 0.0874
-11.000 -0.7013 0.03874 0.03112 -0.1049 0.9493 0.0900
-10.750 -0.6885 0.03690 0.02902 -0.1056 0.9417 0.0928
-10.500 -0.6633 0.03571 0.02788 -0.1071 0.9371 0.0957
-10.250 -0.6521 0.03461 0.02672 -0.1060 0.9283 0.0984
-10.000 -0.6273 0.03319 0.02510 -0.1074 0.9235 0.1026
-9.750 -0.6097 0.03234 0.02428 -0.1069 0.9166 0.1056
-9.500 -0.5889 0.03137 0.02323 -0.1070 0.9100 0.1097
-9.250 -0.5597 0.03031 0.02208 -0.1084 0.9059 0.1144
-9.000 -0.5384 0.02955 0.02129 -0.1082 0.8997 0.1188
-8.750 -0.5186 0.02876 0.02036 -0.1076 0.8924 0.1241
-8.500 -0.4883 0.02797 0.01960 -0.1088 0.8883 0.1296
-8.250 -0.4535 0.02709 0.01860 -0.1107 0.8854 0.1370
-8.000 -0.4422 0.02668 0.01821 -0.1082 0.8752 0.1418
-7.750 -0.4120 0.02595 0.01738 -0.1091 0.8702 0.1498
-7.500 -0.3765 0.02527 0.01669 -0.1109 0.8668 0.1582
-7.250 -0.3584 0.02483 0.01621 -0.1095 0.8585 0.1652
-7.000 -0.3320 0.02433 0.01568 -0.1095 0.8518 0.1740
-6.750 -0.2965 0.02376 0.01510 -0.1111 0.8477 0.1838
-6.500 -0.2666 0.02329 0.01455 -0.1116 0.8421 0.1943
-6.250 -0.2477 0.02304 0.01431 -0.1100 0.8325 0.2026
-6.000 -0.2132 0.02261 0.01384 -0.1112 0.8278 0.2135
-5.750 -0.1831 0.02227 0.01338 -0.1116 0.8219 0.2247
-5.500 -0.1633 0.02212 0.01328 -0.1101 0.8124 0.2327
-5.250 -0.1279 0.02175 0.01280 -0.1114 0.8074 0.2442
-5.000 -0.1049 0.02162 0.01267 -0.1104 0.7987 0.2528
-4.750 -0.0771 0.02137 0.01233 -0.1102 0.7910 0.2627
-4.500 -0.0398 0.02109 0.01200 -0.1118 0.7862 0.2732
-4.250 -0.0228 0.02103 0.01188 -0.1097 0.7755 0.2813
-4.000 0.0099 0.02085 0.01167 -0.1104 0.7695 0.2915
-3.750 0.0369 0.02072 0.01148 -0.1101 0.7620 0.3016
-3.500 0.0620 0.02066 0.01139 -0.1094 0.7534 0.3113
-3.250 0.0978 0.02040 0.01105 -0.1106 0.7480 0.3214
-3.000 0.1169 0.02039 0.01104 -0.1089 0.7380 0.3287
-2.750 0.1487 0.02018 0.01069 -0.1095 0.7315 0.3378
-2.500 0.1765 0.02006 0.01059 -0.1093 0.7246 0.3447
-2.250 0.2010 0.02000 0.01049 -0.1085 0.7167 0.3527
-2.000 0.2342 0.01981 0.01021 -0.1093 0.7112 0.3608
-1.750 0.2579 0.01977 0.01019 -0.1084 0.7035 0.3680
-1.500 0.2853 0.01970 0.01004 -0.1082 0.6964 0.3767
-1.250 0.3189 0.01952 0.00983 -0.1091 0.6913 0.3846
-1.000 0.3406 0.01957 0.00989 -0.1079 0.6840 0.3926
-0.750 0.3678 0.01954 0.00981 -0.1077 0.6778 0.4010
-0.500 0.4004 0.01941 0.00968 -0.1083 0.6728 0.4099
-0.250 0.4234 0.01947 0.00970 -0.1074 0.6658 0.4189
0.000 0.4489 0.01942 0.00971 -0.1068 0.6587 0.4272
0.250 0.4834 0.01928 0.00947 -0.1077 0.6524 0.4381
0.500 0.5008 0.01934 0.00960 -0.1057 0.6426 0.4465
0.750 0.5311 0.01924 0.00946 -0.1059 0.6349 0.4578
1.000 0.5543 0.01929 0.00954 -0.1049 0.6272 0.4683
1.250 0.5786 0.01935 0.00963 -0.1041 0.6204 0.4807
1.500 0.6090 0.01933 0.00964 -0.1044 0.6150 0.4941
1.750 0.6316 0.01944 0.00981 -0.1033 0.6086 0.5087
2.000 0.6532 0.01956 0.01000 -0.1021 0.6018 0.5256
2.250 0.6818 0.01960 0.01007 -0.1020 0.5960 0.5456
2.500 0.7063 0.01972 0.01025 -0.1013 0.5900 0.5677
2.750 0.7256 0.01990 0.01054 -0.0996 0.5830 0.5915
3.000 0.7523 0.01997 0.01066 -0.0992 0.5770 0.6188
3.250 0.7775 0.02007 0.01081 -0.0985 0.5709 0.6475
3.500 0.7940 0.02027 0.01111 -0.0964 0.5634 0.6749
3.750 0.8194 0.02030 0.01121 -0.0957 0.5569 0.7047
4.000 0.8428 0.02037 0.01138 -0.0946 0.5506 0.7379
4.250 0.8586 0.02047 0.01169 -0.0923 0.5427 0.7790
4.750 0.9280 0.02062 0.01210 -0.0950 0.5267 1.0000
5.000 0.9477 0.02086 0.01228 -0.0935 0.5187 1.0000
5.250 0.9692 0.02109 0.01243 -0.0924 0.5112 1.0000
5.500 0.9793 0.02141 0.01276 -0.0893 0.5018 1.0000
5.750 1.0011 0.02158 0.01282 -0.0881 0.4933 1.0000
6.000 1.0074 0.02199 0.01327 -0.0844 0.4828 1.0000
6.250 1.0251 0.02223 0.01342 -0.0826 0.4734 1.0000
6.500 1.0337 0.02266 0.01388 -0.0795 0.4625 1.0000
6.750 1.0480 0.02303 0.01420 -0.0773 0.4526 1.0000
7.000 1.0603 0.02346 0.01461 -0.0749 0.4422 1.0000
7.250 1.0721 0.02396 0.01511 -0.0725 0.4319 1.0000
7.500 1.0868 0.02437 0.01546 -0.0706 0.4221 1.0000
7.750 1.0968 0.02501 0.01612 -0.0681 0.4115 1.0000
8.000 1.1125 0.02547 0.01650 -0.0664 0.4027 1.0000
8.250 1.1225 0.02619 0.01725 -0.0641 0.3925 1.0000
8.500 1.1373 0.02675 0.01773 -0.0624 0.3840 1.0000
8.750 1.1480 0.02752 0.01850 -0.0604 0.3746 1.0000
9.000 1.1630 0.02813 0.01904 -0.0588 0.3667 1.0000
9.250 1.1733 0.02901 0.01994 -0.0569 0.3579 1.0000
9.500 1.1890 0.02965 0.02049 -0.0555 0.3507 1.0000
9.750 1.1997 0.03060 0.02149 -0.0538 0.3433 1.0000
10.000 1.2129 0.03142 0.02229 -0.0523 0.3361 1.0000
10.250 1.2270 0.03225 0.02307 -0.0510 0.3293 1.0000
10.500 1.2355 0.03335 0.02423 -0.0492 0.3217 1.0000
10.750 1.2510 0.03409 0.02486 -0.0480 0.3146 1.0000
11.000 1.2560 0.03544 0.02631 -0.0461 0.3070 1.0000
11.250 1.2652 0.03655 0.02740 -0.0446 0.2995 1.0000
11.500 1.2751 0.03768 0.02852 -0.0432 0.2927 1.0000
11.750 1.2800 0.03916 0.03009 -0.0416 0.2858 1.0000
12.000 1.2917 0.04020 0.03110 -0.0405 0.2797 1.0000
12.250 1.2975 0.04171 0.03268 -0.0391 0.2735 1.0000
12.500 1.3012 0.04338 0.03444 -0.0377 0.2671 1.0000
12.750 1.3117 0.04455 0.03557 -0.0367 0.2614 1.0000
13.000 1.3131 0.04653 0.03767 -0.0354 0.2553 1.0000
13.250 1.3152 0.04848 0.03971 -0.0343 0.2491 1.0000
13.500 1.3243 0.04981 0.04100 -0.0334 0.2435 1.0000
13.750 1.3213 0.05240 0.04376 -0.0325 0.2373 1.0000
14.000 1.3224 0.05463 0.04606 -0.0317 0.2314 1.0000
14.250 1.3292 0.05632 0.04772 -0.0311 0.2264 1.0000
14.500 1.3256 0.05926 0.05085 -0.0306 0.2206 1.0000
14.750 1.3259 0.06177 0.05343 -0.0301 0.2152 1.0000
15.000 1.3297 0.06391 0.05557 -0.0297 0.2102 1.0000
15.250 1.3239 0.06734 0.05918 -0.0297 0.2044 1.0000
15.500 1.3232 0.07015 0.06205 -0.0296 0.1990 1.0000
15.750 1.3227 0.07299 0.06494 -0.0295 0.1939 1.0000
16.000 1.3146 0.07695 0.06905 -0.0299 0.1881 1.0000
16.250 1.3149 0.07973 0.07183 -0.0300 0.1826 1.0000
16.500 1.3065 0.08390 0.07613 -0.0307 0.1769 1.0000
16.750 1.2989 0.08797 0.08029 -0.0314 0.1710 1.0000
17.000 1.2971 0.09121 0.08354 -0.0319 0.1655 1.0000
17.250 1.2824 0.09656 0.08905 -0.0333 0.1592 1.0000
17.500 1.2841 0.09935 0.09179 -0.0338 0.1536 1.0000
17.750 1.2661 0.10544 0.09807 -0.0358 0.1473 1.0000
18.000 1.2628 0.10915 0.10179 -0.0368 0.1417 1.0000
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