GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 500,000 Max Cl/Cd: 91.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe503-il-500000-n5.txt Download as CSV file: xf-goe503-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.2740 0.09815 0.09545 -0.0953 0.9753 0.0101
-14.000 -0.2927 0.09030 0.08751 -0.0998 0.9711 0.0102
-13.750 -0.3017 0.08429 0.08144 -0.1038 0.9662 0.0102
-13.500 -0.3107 0.07772 0.07479 -0.1089 0.9629 0.0103
-13.250 -0.3185 0.07267 0.06969 -0.1122 0.9559 0.0102
-13.000 -0.3310 0.06556 0.06248 -0.1185 0.9506 0.0104
-12.750 -0.3465 0.05859 0.05543 -0.1252 0.9421 0.0104
-12.500 -0.3808 0.04676 0.04345 -0.1412 0.9292 0.0102
-12.250 -0.4271 0.03536 0.03166 -0.1512 0.9063 0.0101
-12.000 -0.4315 0.02969 0.02566 -0.1535 0.8903 0.0101
-11.750 -0.4194 0.02624 0.02192 -0.1547 0.8750 0.0102
-11.500 -0.4053 0.02450 0.01993 -0.1542 0.8587 0.0104
-11.250 -0.3927 0.02314 0.01835 -0.1529 0.8411 0.0105
-11.000 -0.3827 0.02184 0.01683 -0.1508 0.8230 0.0107
-10.750 -0.3712 0.02077 0.01556 -0.1487 0.8054 0.0110
-10.500 -0.3576 0.01991 0.01451 -0.1467 0.7899 0.0112
-10.250 -0.3429 0.01914 0.01356 -0.1447 0.7765 0.0115
-10.000 -0.3265 0.01849 0.01276 -0.1429 0.7646 0.0118
-9.750 -0.3091 0.01790 0.01201 -0.1412 0.7542 0.0122
-9.500 -0.2909 0.01737 0.01133 -0.1396 0.7449 0.0127
-9.250 -0.2715 0.01687 0.01068 -0.1382 0.7366 0.0132
-9.000 -0.2520 0.01639 0.01006 -0.1368 0.7292 0.0137
-8.750 -0.2327 0.01579 0.00934 -0.1353 0.7224 0.0144
-8.500 -0.2122 0.01531 0.00876 -0.1340 0.7155 0.0152
-8.250 -0.1908 0.01493 0.00824 -0.1328 0.7091 0.0160
-8.000 -0.1687 0.01455 0.00776 -0.1317 0.7027 0.0168
-7.750 -0.1472 0.01411 0.00723 -0.1305 0.6968 0.0185
-7.500 -0.1247 0.01376 0.00680 -0.1295 0.6915 0.0204
-7.250 -0.1024 0.01335 0.00638 -0.1284 0.6855 0.0250
-7.000 -0.0797 0.01305 0.00608 -0.1274 0.6795 0.0343
-6.750 -0.0558 0.01286 0.00586 -0.1266 0.6736 0.0403
-6.500 -0.0318 0.01269 0.00564 -0.1258 0.6676 0.0439
-6.250 -0.0080 0.01255 0.00544 -0.1250 0.6620 0.0473
-6.000 0.0165 0.01242 0.00525 -0.1242 0.6562 0.0498
-5.750 0.0401 0.01225 0.00504 -0.1233 0.6497 0.0531
-5.500 0.0634 0.01212 0.00485 -0.1223 0.6436 0.0561
-5.250 0.0875 0.01199 0.00467 -0.1215 0.6369 0.0585
-5.000 0.1110 0.01189 0.00450 -0.1205 0.6305 0.0609
-4.750 0.1344 0.01172 0.00431 -0.1196 0.6244 0.0643
-4.500 0.1576 0.01161 0.00416 -0.1186 0.6171 0.0680
-4.000 0.2040 0.01139 0.00389 -0.1166 0.6037 0.0767
-3.750 0.2263 0.01132 0.00377 -0.1154 0.5970 0.0811
-3.500 0.2496 0.01123 0.00366 -0.1144 0.5903 0.0865
-3.250 0.2721 0.01117 0.00356 -0.1133 0.5834 0.0928
-3.000 0.2948 0.01113 0.00347 -0.1122 0.5774 0.0981
-2.750 0.3175 0.01106 0.00339 -0.1111 0.5708 0.1046
-2.250 0.3619 0.01099 0.00327 -0.1087 0.5586 0.1171
-2.000 0.3837 0.01097 0.00322 -0.1074 0.5527 0.1237
-1.750 0.4046 0.01096 0.00317 -0.1060 0.5474 0.1295
-1.500 0.4263 0.01092 0.00314 -0.1047 0.5419 0.1370
-1.250 0.4471 0.01092 0.00311 -0.1032 0.5365 0.1445
-1.000 0.4676 0.01093 0.00311 -0.1017 0.5319 0.1536
-0.750 0.4897 0.01091 0.00311 -0.1005 0.5269 0.1642
-0.500 0.5112 0.01093 0.00312 -0.0992 0.5220 0.1742
-0.250 0.5318 0.01097 0.00315 -0.0977 0.5174 0.1841
0.000 0.5538 0.01100 0.00317 -0.0966 0.5132 0.1922
0.250 0.5759 0.01102 0.00321 -0.0954 0.5090 0.2010
0.500 0.5972 0.01108 0.00324 -0.0941 0.5043 0.2085
0.750 0.6178 0.01115 0.00331 -0.0927 0.5001 0.2169
1.000 0.6406 0.01120 0.00335 -0.0917 0.4964 0.2232
1.250 0.6624 0.01124 0.00342 -0.0906 0.4924 0.2301
1.500 0.6835 0.01131 0.00349 -0.0893 0.4881 0.2368
1.750 0.7035 0.01142 0.00357 -0.0878 0.4837 0.2436
2.000 0.7260 0.01147 0.00365 -0.0868 0.4802 0.2523
2.250 0.7477 0.01153 0.00373 -0.0857 0.4761 0.2609
2.500 0.7679 0.01162 0.00384 -0.0843 0.4717 0.2725
2.750 0.7875 0.01173 0.00396 -0.0828 0.4677 0.2865
3.000 0.8091 0.01178 0.00407 -0.0817 0.4643 0.3068
3.250 0.8297 0.01182 0.00421 -0.0804 0.4602 0.3380
3.500 0.8483 0.01187 0.00435 -0.0788 0.4559 0.3789
4.250 1.0301 0.01150 0.00538 -0.1016 0.4401 0.9862
4.500 1.0597 0.01178 0.00561 -0.1024 0.4354 0.9956
4.750 1.0975 0.01201 0.00584 -0.1050 0.4295 1.0000
5.000 1.1111 0.01219 0.00599 -0.1024 0.4238 1.0000
5.250 1.1245 0.01240 0.00617 -0.0998 0.4185 1.0000
5.500 1.1404 0.01258 0.00636 -0.0977 0.4123 1.0000
5.750 1.1541 0.01283 0.00658 -0.0953 0.4062 1.0000
6.000 1.1695 0.01307 0.00680 -0.0932 0.4001 1.0000
6.250 1.1842 0.01335 0.00706 -0.0910 0.3929 1.0000
6.500 1.1988 0.01366 0.00735 -0.0889 0.3876 1.0000
6.750 1.2161 0.01391 0.00761 -0.0873 0.3827 1.0000
7.000 1.2320 0.01422 0.00792 -0.0855 0.3773 1.0000
7.250 1.2466 0.01460 0.00828 -0.0835 0.3725 1.0000
7.500 1.2640 0.01490 0.00861 -0.0820 0.3676 1.0000
7.750 1.2794 0.01529 0.00899 -0.0803 0.3620 1.0000
8.000 1.2934 0.01574 0.00944 -0.0784 0.3568 1.0000
8.250 1.3098 0.01613 0.00985 -0.0769 0.3507 1.0000
8.500 1.3230 0.01666 0.01038 -0.0750 0.3446 1.0000
8.750 1.3374 0.01718 0.01090 -0.0733 0.3381 1.0000
9.000 1.3493 0.01781 0.01152 -0.0714 0.3300 1.0000
9.250 1.3605 0.01852 0.01221 -0.0694 0.3202 1.0000
9.500 1.3701 0.01933 0.01301 -0.0673 0.3121 1.0000
9.750 1.3827 0.02004 0.01373 -0.0657 0.3041 1.0000
10.000 1.3906 0.02102 0.01469 -0.0636 0.2945 1.0000
10.250 1.3985 0.02206 0.01570 -0.0616 0.2834 1.0000
10.500 1.4086 0.02302 0.01668 -0.0599 0.2758 1.0000
10.750 1.4127 0.02439 0.01801 -0.0578 0.2631 1.0000
11.000 1.4209 0.02557 0.01919 -0.0562 0.2546 1.0000
11.250 1.4245 0.02710 0.02070 -0.0543 0.2425 1.0000
11.500 1.4289 0.02864 0.02224 -0.0526 0.2328 1.0000
11.750 1.4284 0.03061 0.02417 -0.0506 0.2186 1.0000
12.000 1.4261 0.03279 0.02630 -0.0486 0.2043 1.0000
12.250 1.4219 0.03522 0.02867 -0.0467 0.1895 1.0000
12.500 1.4187 0.03764 0.03106 -0.0451 0.1779 1.0000
13.000 1.4102 0.04287 0.03625 -0.0420 0.1549 1.0000
13.250 1.4057 0.04564 0.03901 -0.0407 0.1432 1.0000
13.500 1.3906 0.04950 0.04278 -0.0391 0.1236 1.0000
13.750 1.3712 0.05392 0.04709 -0.0376 0.0977 1.0000
14.000 1.3416 0.05963 0.05267 -0.0361 0.0664 1.0000
14.250 1.3198 0.06469 0.05768 -0.0350 0.0455 1.0000
14.500 1.2934 0.07052 0.06343 -0.0343 0.0193 1.0000
14.750 1.2898 0.07382 0.06678 -0.0340 0.0163 1.0000
15.000 1.2892 0.07680 0.06984 -0.0338 0.0150 1.0000
15.250 1.2871 0.08000 0.07312 -0.0337 0.0138 1.0000
15.500 1.2855 0.08317 0.07636 -0.0337 0.0130 1.0000
15.750 1.2842 0.08636 0.07963 -0.0338 0.0123 1.0000
16.000 1.2841 0.08940 0.08276 -0.0339 0.0120 1.0000
16.250 1.2828 0.09262 0.08606 -0.0341 0.0114 1.0000
16.500 1.2807 0.09597 0.08949 -0.0343 0.0109 1.0000
16.750 1.2775 0.09950 0.09310 -0.0346 0.0104 1.0000
17.000 1.2730 0.10327 0.09696 -0.0351 0.0100 1.0000
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