GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.1 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe518-il-1000000-n5.txt Download as CSV file: xf-goe518-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-12.750 0.1452 0.09414 0.09187 -0.1450 0.9098 0.0165
-12.500 -0.2139 0.02761 0.02437 -0.1921 0.9031 0.0217
-12.250 -0.2268 0.02534 0.02185 -0.1888 0.8913 0.0218
-12.000 -0.2299 0.02412 0.02046 -0.1849 0.8797 0.0218
-11.750 -0.2312 0.02326 0.01949 -0.1806 0.8695 0.0219
-11.500 -0.2294 0.02254 0.01863 -0.1766 0.8582 0.0220
-11.250 -0.2226 0.02191 0.01786 -0.1732 0.8450 0.0221
-11.000 -0.2179 0.02119 0.01698 -0.1694 0.8296 0.0221
-10.750 -0.2078 0.02079 0.01647 -0.1663 0.8154 0.0222
-10.500 -0.1972 0.02032 0.01589 -0.1633 0.8040 0.0223
-10.250 -0.1873 0.01968 0.01512 -0.1602 0.7946 0.0224
-10.000 -0.1746 0.01916 0.01449 -0.1576 0.7866 0.0225
-9.750 -0.1627 0.01858 0.01380 -0.1547 0.7765 0.0225
-9.500 -0.1475 0.01822 0.01335 -0.1523 0.7679 0.0227
-9.250 -0.1351 0.01765 0.01265 -0.1494 0.7570 0.0228
-9.000 -0.1206 0.01728 0.01218 -0.1468 0.7446 0.0230
-8.750 -0.1087 0.01683 0.01159 -0.1437 0.7289 0.0231
-8.500 -0.0993 0.01653 0.01113 -0.1400 0.7052 0.0233
-8.250 -0.0935 0.01624 0.01063 -0.1355 0.6755 0.0234
-8.000 -0.0836 0.01600 0.01024 -0.1318 0.6545 0.0235
-7.750 -0.0730 0.01571 0.00980 -0.1282 0.6367 0.0237
-7.500 -0.0615 0.01548 0.00945 -0.1248 0.6230 0.0240
-7.250 -0.0523 0.01513 0.00897 -0.1209 0.6107 0.0241
-7.000 -0.0391 0.01480 0.00854 -0.1178 0.5993 0.0242
-6.750 -0.0261 0.01453 0.00816 -0.1147 0.5875 0.0244
-6.500 -0.0106 0.01425 0.00779 -0.1121 0.5774 0.0245
-6.250 0.0041 0.01395 0.00739 -0.1093 0.5663 0.0246
-6.000 0.0191 0.01376 0.00711 -0.1065 0.5548 0.0247
-5.750 0.0362 0.01354 0.00681 -0.1041 0.5449 0.0248
-5.500 0.0520 0.01335 0.00652 -0.1016 0.5336 0.0249
-5.250 0.0696 0.01320 0.00629 -0.0993 0.5215 0.0250
-5.000 0.0851 0.01294 0.00595 -0.0967 0.5098 0.0251
-4.750 0.1004 0.01274 0.00566 -0.0941 0.4969 0.0253
-4.500 0.1173 0.01260 0.00546 -0.0917 0.4834 0.0255
-4.250 0.1345 0.01252 0.00531 -0.0895 0.4703 0.0256
-4.000 0.1512 0.01249 0.00521 -0.0871 0.4565 0.0259
-3.750 0.1678 0.01247 0.00511 -0.0847 0.4431 0.0260
-3.500 0.1861 0.01244 0.00501 -0.0827 0.4315 0.0262
-3.250 0.2047 0.01243 0.00495 -0.0807 0.4217 0.0265
-3.000 0.2236 0.01240 0.00487 -0.0788 0.4120 0.0267
-2.750 0.2424 0.01237 0.00479 -0.0769 0.4042 0.0269
-2.500 0.2618 0.01236 0.00473 -0.0751 0.3965 0.0272
-2.250 0.2805 0.01239 0.00470 -0.0732 0.3888 0.0275
-2.000 0.3006 0.01234 0.00462 -0.0715 0.3830 0.0279
-1.750 0.3202 0.01235 0.00458 -0.0698 0.3760 0.0281
-1.500 0.3396 0.01235 0.00455 -0.0681 0.3697 0.0283
-1.250 0.3595 0.01233 0.00450 -0.0664 0.3643 0.0283
-1.000 0.3789 0.01240 0.00452 -0.0647 0.3577 0.0287
-0.750 0.3980 0.01243 0.00451 -0.0629 0.3526 0.0287
-0.500 0.4180 0.01238 0.00445 -0.0613 0.3492 0.0292
-0.250 0.4384 0.01239 0.00445 -0.0598 0.3452 0.0296
0.000 0.4584 0.01243 0.00447 -0.0583 0.3409 0.0300
0.250 0.4777 0.01250 0.00452 -0.0566 0.3366 0.0305
0.500 0.4979 0.01256 0.00457 -0.0551 0.3337 0.0308
0.750 0.5185 0.01261 0.00461 -0.0537 0.3313 0.0312
1.000 0.5392 0.01268 0.00467 -0.0523 0.3284 0.0318
1.250 0.5595 0.01275 0.00473 -0.0509 0.3253 0.0323
1.500 0.5796 0.01285 0.00482 -0.0495 0.3224 0.0332
1.750 0.5991 0.01295 0.00491 -0.0480 0.3197 0.0343
2.000 0.6187 0.01307 0.00503 -0.0465 0.3169 0.0354
2.250 0.6396 0.01316 0.00513 -0.0452 0.3154 0.0362
2.500 0.6605 0.01327 0.00523 -0.0440 0.3137 0.0371
2.750 0.6809 0.01337 0.00535 -0.0427 0.3111 0.0403
3.000 0.7009 0.01349 0.00548 -0.0414 0.3088 0.0479
3.250 0.7195 0.01356 0.00568 -0.0398 0.3070 0.0949
3.500 0.7383 0.01372 0.00587 -0.0383 0.3044 0.1152
3.750 0.7572 0.01388 0.00607 -0.0369 0.3019 0.1383
4.250 1.0320 0.01326 0.00752 -0.0854 0.2964 0.9989
4.500 1.0679 0.01350 0.00774 -0.0876 0.2947 1.0000
4.750 1.0840 0.01372 0.00795 -0.0857 0.2932 1.0000
5.000 1.1004 0.01395 0.00817 -0.0838 0.2917 1.0000
5.250 1.1173 0.01419 0.00839 -0.0821 0.2903 1.0000
5.500 1.1339 0.01445 0.00864 -0.0803 0.2890 1.0000
5.750 1.1497 0.01475 0.00892 -0.0785 0.2871 1.0000
6.000 1.1662 0.01505 0.00921 -0.0768 0.2856 1.0000
6.250 1.1826 0.01537 0.00952 -0.0751 0.2838 1.0000
6.500 1.2012 0.01561 0.00978 -0.0738 0.2830 1.0000
6.750 1.2192 0.01589 0.01006 -0.0724 0.2819 1.0000
7.000 1.2375 0.01617 0.01035 -0.0711 0.2804 1.0000
7.250 1.2557 0.01647 0.01065 -0.0699 0.2786 1.0000
7.500 1.2733 0.01679 0.01098 -0.0686 0.2768 1.0000
7.750 1.2904 0.01715 0.01134 -0.0672 0.2755 1.0000
8.000 1.3075 0.01753 0.01172 -0.0659 0.2740 1.0000
8.250 1.3246 0.01792 0.01211 -0.0646 0.2726 1.0000
8.500 1.3410 0.01836 0.01255 -0.0633 0.2712 1.0000
8.750 1.3569 0.01882 0.01302 -0.0619 0.2696 1.0000
9.000 1.3731 0.01929 0.01350 -0.0607 0.2681 1.0000
9.250 1.3915 0.01967 0.01391 -0.0597 0.2672 1.0000
9.500 1.4093 0.02008 0.01434 -0.0587 0.2661 1.0000
9.750 1.4270 0.02051 0.01480 -0.0578 0.2648 1.0000
10.000 1.4445 0.02095 0.01526 -0.0568 0.2636 1.0000
10.250 1.4612 0.02144 0.01578 -0.0558 0.2624 1.0000
10.500 1.4774 0.02198 0.01634 -0.0547 0.2611 1.0000
10.750 1.4937 0.02252 0.01690 -0.0537 0.2598 1.0000
11.000 1.5096 0.02309 0.01749 -0.0527 0.2584 1.0000
11.250 1.5242 0.02374 0.01816 -0.0516 0.2570 1.0000
11.500 1.5375 0.02449 0.01891 -0.0504 0.2541 1.0000
11.750 1.5531 0.02511 0.01956 -0.0495 0.2524 1.0000
12.000 1.5690 0.02573 0.02023 -0.0487 0.2515 1.0000
12.250 1.5853 0.02634 0.02087 -0.0479 0.2493 1.0000
12.500 1.6010 0.02699 0.02156 -0.0471 0.2471 1.0000
12.750 1.6136 0.02786 0.02243 -0.0461 0.2436 1.0000
13.000 1.6249 0.02883 0.02340 -0.0450 0.2404 1.0000
13.250 1.6380 0.02969 0.02430 -0.0441 0.2378 1.0000
13.500 1.6519 0.03052 0.02517 -0.0433 0.2353 1.0000
13.750 1.6635 0.03151 0.02617 -0.0424 0.2303 1.0000
14.000 1.6726 0.03271 0.02738 -0.0413 0.2271 1.0000
14.250 1.6828 0.03385 0.02855 -0.0404 0.2227 1.0000
14.500 1.6912 0.03515 0.02987 -0.0394 0.2167 1.0000
14.750 1.6959 0.03677 0.03148 -0.0382 0.2102 1.0000
15.000 1.6949 0.03887 0.03356 -0.0367 0.1995 1.0000
15.250 1.6908 0.04130 0.03596 -0.0352 0.1882 1.0000
15.500 1.6857 0.04390 0.03855 -0.0337 0.1782 1.0000
15.750 1.6659 0.04791 0.04250 -0.0317 0.1628 1.0000
16.000 1.6488 0.05184 0.04642 -0.0302 0.1511 1.0000
16.250 1.6421 0.05490 0.04951 -0.0293 0.1452 1.0000
16.500 1.6181 0.05980 0.05442 -0.0281 0.1343 1.0000
16.750 1.6114 0.06303 0.05770 -0.0276 0.1305 1.0000
17.000 1.5945 0.06744 0.06215 -0.0270 0.1249 1.0000
17.250 1.5869 0.07094 0.06572 -0.0267 0.1221 1.0000
17.500 1.5712 0.07544 0.07028 -0.0265 0.1180 1.0000
18.000 1.5429 0.08430 0.07928 -0.0266 0.1122 1.0000
18.250 1.5336 0.08826 0.08332 -0.0269 0.1106 1.0000
18.500 1.5102 0.09403 0.08916 -0.0273 0.1066 1.0000
18.750 1.4955 0.09875 0.09396 -0.0278 0.1047 1.0000
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