GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 100,000 Max Cl/Cd: 43.45 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe614-il-100000-n5.txt Download as CSV file: xf-goe614-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2370 0.07575 0.07019 -0.1089 0.9411 0.0470
-11.000 -0.3048 0.06081 0.05492 -0.1214 0.9280 0.0464
-10.750 -0.3349 0.05290 0.04670 -0.1296 0.9153 0.0461
-10.500 -0.3523 0.04769 0.04118 -0.1350 0.9041 0.0460
-10.250 -0.3599 0.04465 0.03786 -0.1354 0.8929 0.0460
-10.000 -0.3612 0.04229 0.03525 -0.1347 0.8820 0.0461
-9.750 -0.3474 0.03983 0.03251 -0.1358 0.8753 0.0463
-9.500 -0.3383 0.03808 0.03052 -0.1349 0.8660 0.0466
-9.250 -0.3200 0.03630 0.02848 -0.1352 0.8588 0.0469
-9.000 -0.2899 0.03462 0.02673 -0.1369 0.8547 0.0476
-8.750 -0.2812 0.03369 0.02575 -0.1345 0.8434 0.0481
-8.500 -0.2525 0.03231 0.02427 -0.1356 0.8382 0.0489
-8.250 -0.2380 0.03137 0.02324 -0.1341 0.8286 0.0496
-8.000 -0.2125 0.03022 0.02195 -0.1343 0.8216 0.0504
-7.750 -0.1882 0.02920 0.02080 -0.1342 0.8145 0.0510
-7.500 -0.1695 0.02839 0.01989 -0.1330 0.8052 0.0515
-7.250 -0.1374 0.02735 0.01868 -0.1342 0.7996 0.0523
-6.750 -0.0956 0.02587 0.01703 -0.1324 0.7819 0.0538
-6.500 -0.0795 0.02531 0.01641 -0.1306 0.7716 0.0546
-6.250 -0.0520 0.02456 0.01553 -0.1308 0.7641 0.0560
-6.000 -0.0324 0.02404 0.01491 -0.1295 0.7544 0.0574
-5.750 -0.0064 0.02341 0.01418 -0.1293 0.7462 0.0593
-5.500 0.0152 0.02286 0.01358 -0.1284 0.7370 0.0626
-5.250 0.0398 0.02232 0.01299 -0.1279 0.7282 0.0672
-5.000 0.0635 0.02182 0.01252 -0.1273 0.7195 0.0764
-4.750 0.0874 0.02140 0.01205 -0.1265 0.7104 0.0946
-4.500 0.1135 0.02102 0.01158 -0.1262 0.7021 0.1127
-4.250 0.1359 0.02065 0.01126 -0.1253 0.6927 0.1321
-4.000 0.1628 0.02037 0.01100 -0.1251 0.6846 0.1532
-3.750 0.1858 0.02026 0.01087 -0.1241 0.6751 0.1715
-3.500 0.2155 0.02013 0.01062 -0.1244 0.6680 0.1902
-3.250 0.2368 0.02011 0.01054 -0.1231 0.6585 0.2050
-3.000 0.2669 0.02001 0.01029 -0.1234 0.6513 0.2223
-2.750 0.2871 0.01999 0.01029 -0.1219 0.6421 0.2344
-2.500 0.3144 0.01991 0.01011 -0.1217 0.6348 0.2483
-2.250 0.3386 0.01993 0.01002 -0.1210 0.6271 0.2624
-2.000 0.3622 0.01992 0.01002 -0.1202 0.6196 0.2785
-1.750 0.3914 0.01987 0.00990 -0.1203 0.6135 0.2965
-1.500 0.4110 0.01994 0.00999 -0.1188 0.6054 0.3112
-1.250 0.4371 0.01993 0.00990 -0.1184 0.5988 0.3254
-1.000 0.4628 0.01994 0.00985 -0.1180 0.5926 0.3385
-0.750 0.4845 0.02000 0.00994 -0.1168 0.5856 0.3518
-0.500 0.5111 0.02002 0.00991 -0.1165 0.5800 0.3678
-0.250 0.5371 0.02007 0.00991 -0.1162 0.5745 0.3841
0.250 0.5835 0.02022 0.01008 -0.1144 0.5623 0.4228
0.500 0.6115 0.02026 0.01010 -0.1144 0.5575 0.4469
0.750 0.6309 0.02041 0.01034 -0.1129 0.5515 0.4698
1.000 0.6552 0.02051 0.01047 -0.1123 0.5463 0.4951
1.250 0.6836 0.02058 0.01050 -0.1124 0.5418 0.5234
1.500 0.7066 0.02070 0.01069 -0.1115 0.5368 0.5529
1.750 0.7265 0.02084 0.01093 -0.1101 0.5313 0.5867
2.000 0.7505 0.02088 0.01108 -0.1094 0.5266 0.6302
2.250 0.7787 0.02081 0.01117 -0.1092 0.5227 0.6988
2.500 0.8446 0.02083 0.01164 -0.1169 0.5166 1.0000
2.750 0.8636 0.02115 0.01187 -0.1155 0.5115 1.0000
3.000 0.8876 0.02141 0.01199 -0.1149 0.5071 1.0000
3.250 0.9165 0.02164 0.01204 -0.1152 0.5032 1.0000
3.500 0.9261 0.02206 0.01248 -0.1121 0.4974 1.0000
3.750 0.9431 0.02234 0.01269 -0.1102 0.4913 1.0000
4.000 0.9688 0.02249 0.01267 -0.1099 0.4858 1.0000
4.250 0.9756 0.02289 0.01307 -0.1063 0.4794 1.0000
4.500 0.9888 0.02320 0.01334 -0.1038 0.4733 1.0000
4.750 1.0117 0.02340 0.01341 -0.1030 0.4682 1.0000
5.000 1.0236 0.02382 0.01382 -0.1004 0.4630 1.0000
5.250 1.0340 0.02427 0.01429 -0.0976 0.4574 1.0000
5.500 1.0524 0.02459 0.01455 -0.0962 0.4526 1.0000
5.750 1.0785 0.02482 0.01465 -0.0960 0.4487 1.0000
6.000 1.0830 0.02548 0.01540 -0.0925 0.4435 1.0000
6.250 1.0949 0.02602 0.01596 -0.0903 0.4387 1.0000
6.500 1.1129 0.02640 0.01630 -0.0889 0.4343 1.0000
6.750 1.1367 0.02665 0.01644 -0.0884 0.4302 1.0000
7.000 1.1375 0.02753 0.01745 -0.0848 0.4247 1.0000
7.250 1.1475 0.02816 0.01810 -0.0825 0.4193 1.0000
7.500 1.1659 0.02854 0.01842 -0.0813 0.4149 1.0000
7.750 1.1780 0.02917 0.01906 -0.0794 0.4102 1.0000
8.000 1.1803 0.03020 0.02019 -0.0764 0.4047 1.0000
8.250 1.1918 0.03089 0.02089 -0.0746 0.3998 1.0000
8.500 1.2127 0.03121 0.02115 -0.0739 0.3958 1.0000
8.750 1.2118 0.03255 0.02259 -0.0709 0.3905 1.0000
9.000 1.2153 0.03375 0.02388 -0.0686 0.3853 1.0000
9.250 1.2283 0.03446 0.02458 -0.0672 0.3807 1.0000
9.500 1.2429 0.03516 0.02527 -0.0660 0.3766 1.0000
9.750 1.2346 0.03723 0.02749 -0.0630 0.3708 1.0000
10.000 1.2401 0.03853 0.02884 -0.0613 0.3659 1.0000
10.250 1.2577 0.03906 0.02935 -0.0605 0.3621 1.0000
10.500 1.2489 0.04148 0.03189 -0.0581 0.3564 1.0000
10.750 1.2450 0.04369 0.03420 -0.0562 0.3510 1.0000
11.000 1.2574 0.04465 0.03516 -0.0553 0.3469 1.0000
11.250 1.2596 0.04651 0.03707 -0.0539 0.3422 1.0000
11.500 1.2396 0.05043 0.04116 -0.0519 0.3353 1.0000
11.750 1.2503 0.05164 0.04238 -0.0511 0.3310 1.0000
12.000 1.2520 0.05378 0.04457 -0.0502 0.3264 1.0000
12.250 1.2224 0.05935 0.05031 -0.0489 0.3189 1.0000
12.500 1.2360 0.06036 0.05133 -0.0484 0.3151 1.0000
12.750 1.2603 0.06023 0.05117 -0.0479 0.3129 1.0000
13.000 1.1942 0.07071 0.06191 -0.0474 0.3025 1.0000
13.250 1.2097 0.07159 0.06281 -0.0470 0.2997 1.0000
13.500 1.2328 0.07151 0.06274 -0.0465 0.2978 1.0000
14.000 1.1746 0.08507 0.07657 -0.0471 0.2840 1.0000
14.250 1.1976 0.08491 0.07642 -0.0467 0.2825 1.0000
14.750 1.1410 0.09932 0.09106 -0.0485 0.2679 1.0000
15.000 1.1667 0.09861 0.09037 -0.0480 0.2666 1.0000
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