GOE 420 AIRFOIL (goe420-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 420 AIRFOIL (goe420-il) Reynolds number: 500,000 Max Cl/Cd: 89.91 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe420-il-500000.txt Download as CSV file: xf-goe420-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 420 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7217 0.07173 0.06788 -0.0994 1.0000 0.0355
-16.000 -0.7483 0.06564 0.06163 -0.1030 1.0000 0.0355
-15.750 -0.7685 0.06090 0.05676 -0.1052 1.0000 0.0355
-15.500 -0.7874 0.05704 0.05279 -0.1065 1.0000 0.0354
-15.250 -0.8020 0.05370 0.04938 -0.1072 0.9993 0.0355
-15.000 -0.7927 0.04973 0.04528 -0.1120 0.9962 0.0357
-14.750 -0.7817 0.04638 0.04184 -0.1160 0.9893 0.0358
-14.500 -0.7681 0.04349 0.03886 -0.1197 0.9837 0.0360
-14.250 -0.7518 0.04074 0.03601 -0.1236 0.9795 0.0362
-14.000 -0.7368 0.03829 0.03348 -0.1268 0.9722 0.0364
-13.750 -0.7158 0.03597 0.03105 -0.1308 0.9677 0.0368
-13.500 -0.6919 0.03374 0.02872 -0.1349 0.9634 0.0370
-13.250 -0.6660 0.03182 0.02671 -0.1389 0.9574 0.0374
-13.000 -0.6366 0.02996 0.02473 -0.1432 0.9520 0.0378
-12.750 -0.6104 0.02835 0.02300 -0.1466 0.9439 0.0383
-12.500 -0.5856 0.02691 0.02144 -0.1491 0.9354 0.0386
-12.250 -0.5693 0.02575 0.02015 -0.1496 0.9252 0.0389
-12.000 -0.5535 0.02474 0.01901 -0.1496 0.9160 0.0392
-11.750 -0.5445 0.02392 0.01809 -0.1480 0.9065 0.0394
-11.500 -0.5337 0.02319 0.01722 -0.1465 0.8981 0.0396
-11.250 -0.5235 0.02222 0.01622 -0.1446 0.8904 0.0400
-11.000 -0.5147 0.02139 0.01536 -0.1424 0.8826 0.0403
-10.750 -0.5047 0.02071 0.01461 -0.1402 0.8756 0.0407
-10.500 -0.4974 0.02020 0.01409 -0.1372 0.8685 0.0410
-10.250 -0.4850 0.01965 0.01349 -0.1352 0.8621 0.0414
-10.000 -0.4689 0.01915 0.01292 -0.1337 0.8565 0.0419
-9.750 -0.4544 0.01865 0.01239 -0.1318 0.8506 0.0424
-9.500 -0.4378 0.01815 0.01184 -0.1302 0.8446 0.0429
-9.250 -0.4192 0.01769 0.01130 -0.1290 0.8393 0.0436
-9.000 -0.4002 0.01728 0.01082 -0.1277 0.8338 0.0441
-8.750 -0.3818 0.01680 0.01030 -0.1263 0.8276 0.0448
-8.500 -0.3646 0.01618 0.00966 -0.1248 0.8217 0.0457
-8.250 -0.3439 0.01576 0.00919 -0.1238 0.8160 0.0466
-8.000 -0.3235 0.01535 0.00876 -0.1226 0.8095 0.0476
-7.750 -0.3016 0.01497 0.00832 -0.1216 0.8031 0.0487
-7.500 -0.2777 0.01466 0.00791 -0.1209 0.7973 0.0498
-7.250 -0.2583 0.01412 0.00740 -0.1196 0.7906 0.0513
-7.000 -0.2353 0.01376 0.00700 -0.1188 0.7841 0.0532
-6.750 -0.2102 0.01349 0.00664 -0.1183 0.7783 0.0554
-6.500 -0.1884 0.01306 0.00624 -0.1173 0.7716 0.0584
-6.250 -0.1643 0.01273 0.00587 -0.1166 0.7648 0.0627
-6.000 -0.1402 0.01236 0.00548 -0.1160 0.7583 0.0697
-5.750 -0.1178 0.01189 0.00509 -0.1151 0.7515 0.0827
-5.500 -0.0952 0.01136 0.00473 -0.1144 0.7454 0.1167
-5.250 -0.0697 0.01108 0.00450 -0.1140 0.7400 0.1450
-5.000 -0.0446 0.01083 0.00432 -0.1135 0.7339 0.1617
-4.750 -0.0190 0.01061 0.00412 -0.1131 0.7277 0.1771
-4.500 0.0071 0.01041 0.00393 -0.1128 0.7220 0.1957
-4.250 0.0325 0.01019 0.00382 -0.1123 0.7158 0.2206
-4.000 0.0586 0.01003 0.00373 -0.1120 0.7096 0.2474
-3.750 0.0858 0.00996 0.00365 -0.1117 0.7041 0.2679
-3.500 0.1127 0.00989 0.00361 -0.1115 0.6985 0.2839
-3.250 0.1396 0.00982 0.00356 -0.1112 0.6926 0.2974
-3.000 0.1672 0.00981 0.00350 -0.1110 0.6871 0.3091
-2.750 0.1944 0.00979 0.00348 -0.1108 0.6817 0.3235
-2.500 0.2210 0.00974 0.00347 -0.1105 0.6758 0.3369
-2.250 0.2484 0.00976 0.00343 -0.1102 0.6697 0.3478
-2.000 0.2755 0.00974 0.00341 -0.1100 0.6641 0.3581
-1.750 0.3025 0.00974 0.00339 -0.1097 0.6581 0.3659
-1.500 0.3291 0.00969 0.00336 -0.1094 0.6522 0.3737
-1.250 0.3566 0.00973 0.00333 -0.1092 0.6465 0.3818
-1.000 0.3832 0.00970 0.00332 -0.1088 0.6408 0.3891
-0.750 0.4096 0.00967 0.00331 -0.1084 0.6345 0.3971
-0.500 0.4367 0.00972 0.00329 -0.1082 0.6285 0.4057
-0.250 0.4626 0.00968 0.00331 -0.1077 0.6221 0.4153
0.000 0.4888 0.00969 0.00331 -0.1073 0.6151 0.4250
0.250 0.5149 0.00972 0.00331 -0.1068 0.6082 0.4350
0.500 0.5405 0.00971 0.00334 -0.1063 0.6010 0.4472
0.750 0.5657 0.00971 0.00336 -0.1057 0.5936 0.4606
1.000 0.5911 0.00973 0.00339 -0.1051 0.5862 0.4737
1.250 0.6158 0.00973 0.00342 -0.1044 0.5777 0.4878
1.500 0.6398 0.00976 0.00345 -0.1036 0.5693 0.5028
1.750 0.6635 0.00974 0.00350 -0.1027 0.5596 0.5212
2.000 0.6864 0.00977 0.00355 -0.1017 0.5504 0.5435
2.250 0.7090 0.00977 0.00363 -0.1006 0.5403 0.5703
2.500 0.7307 0.00980 0.00373 -0.0994 0.5307 0.6021
3.000 0.7723 0.00991 0.00394 -0.0965 0.5096 0.6696
3.250 0.7913 0.01001 0.00404 -0.0947 0.4993 0.6994
3.500 0.8108 0.01002 0.00416 -0.0930 0.4901 0.7328
3.750 0.8258 0.01001 0.00432 -0.0903 0.4824 0.7880
4.000 0.8403 0.00997 0.00454 -0.0872 0.4761 0.8991
4.250 0.8875 0.01018 0.00479 -0.0913 0.4689 0.9635
4.500 0.9354 0.01052 0.00503 -0.0957 0.4620 1.0000
4.750 0.9529 0.01064 0.00516 -0.0937 0.4570 1.0000
5.000 0.9703 0.01082 0.00530 -0.0918 0.4517 1.0000
5.250 0.9879 0.01105 0.00546 -0.0899 0.4469 1.0000
5.500 1.0076 0.01128 0.00565 -0.0884 0.4425 1.0000
5.750 1.0278 0.01144 0.00583 -0.0870 0.4385 1.0000
6.000 1.0475 0.01165 0.00603 -0.0856 0.4342 1.0000
6.250 1.0672 0.01190 0.00624 -0.0842 0.4300 1.0000
6.500 1.0887 0.01220 0.00647 -0.0832 0.4256 1.0000
6.750 1.1081 0.01239 0.00670 -0.0817 0.4220 1.0000
7.000 1.1269 0.01261 0.00694 -0.0802 0.4173 1.0000
7.250 1.1453 0.01289 0.00719 -0.0787 0.4123 1.0000
7.500 1.1633 0.01323 0.00748 -0.0772 0.4063 1.0000
7.750 1.1792 0.01347 0.00777 -0.0753 0.4003 1.0000
8.000 1.1951 0.01380 0.00808 -0.0735 0.3940 1.0000
8.250 1.2125 0.01419 0.00843 -0.0719 0.3886 1.0000
8.500 1.2302 0.01447 0.00876 -0.0705 0.3839 1.0000
8.750 1.2472 0.01481 0.00912 -0.0690 0.3784 1.0000
9.000 1.2620 0.01527 0.00954 -0.0672 0.3726 1.0000
9.250 1.2791 0.01564 0.00996 -0.0658 0.3668 1.0000
9.500 1.2950 0.01606 0.01040 -0.0642 0.3606 1.0000
9.750 1.3082 0.01663 0.01093 -0.0624 0.3543 1.0000
10.000 1.3252 0.01706 0.01141 -0.0611 0.3479 1.0000
10.250 1.3397 0.01761 0.01197 -0.0596 0.3411 1.0000
10.500 1.3530 0.01825 0.01260 -0.0579 0.3346 1.0000
10.750 1.3681 0.01882 0.01320 -0.0566 0.3269 1.0000
11.000 1.3784 0.01964 0.01400 -0.0547 0.3191 1.0000
11.250 1.3925 0.02032 0.01470 -0.0534 0.3101 1.0000
11.500 1.4018 0.02126 0.01562 -0.0515 0.3015 1.0000
11.750 1.4123 0.02218 0.01653 -0.0500 0.2913 1.0000
12.000 1.4214 0.02322 0.01756 -0.0483 0.2823 1.0000
12.250 1.4283 0.02442 0.01874 -0.0465 0.2728 1.0000
12.500 1.4377 0.02553 0.01985 -0.0451 0.2637 1.0000
12.750 1.4418 0.02701 0.02129 -0.0433 0.2547 1.0000
13.000 1.4507 0.02823 0.02253 -0.0419 0.2454 1.0000
13.250 1.4548 0.02982 0.02410 -0.0404 0.2364 1.0000
13.500 1.4585 0.03151 0.02577 -0.0389 0.2263 1.0000
13.750 1.4631 0.03320 0.02745 -0.0376 0.2159 1.0000
14.000 1.4643 0.03520 0.02943 -0.0362 0.2062 1.0000
14.250 1.4648 0.03734 0.03155 -0.0349 0.1948 1.0000
14.500 1.4641 0.03965 0.03384 -0.0337 0.1812 1.0000
14.750 1.4595 0.04239 0.03652 -0.0325 0.1663 1.0000
15.000 1.4514 0.04553 0.03960 -0.0314 0.1502 1.0000
15.250 1.4414 0.04896 0.04297 -0.0303 0.1359 1.0000
15.500 1.4317 0.05246 0.04644 -0.0295 0.1253 1.0000
15.750 1.4243 0.05583 0.04979 -0.0289 0.1175 1.0000
16.000 1.4199 0.05897 0.05296 -0.0284 0.1122 1.0000
16.250 1.4135 0.06241 0.05642 -0.0281 0.1072 1.0000
16.500 1.4084 0.06579 0.05983 -0.0279 0.1031 1.0000
16.750 1.4077 0.06871 0.06281 -0.0278 0.1001 1.0000
17.000 1.4031 0.07216 0.06628 -0.0279 0.0972 1.0000
17.250 1.3958 0.07598 0.07013 -0.0280 0.0946 1.0000
17.500 1.3978 0.07874 0.07296 -0.0282 0.0928 1.0000
17.750 1.3983 0.08169 0.07598 -0.0285 0.0910 1.0000
18.000 1.3968 0.08494 0.07928 -0.0288 0.0891 1.0000
18.250 1.3945 0.08830 0.08268 -0.0293 0.0875 1.0000
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