GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 460 AIRFOIL (goe460-il) Reynolds number: 500,000 Max Cl/Cd: 54.37 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe460-il-500000.txt Download as CSV file: xf-goe460-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 460 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
------ -------- --------- --------- -------- -------- --------
-19.500 -1.0918 0.08601 0.08092 -0.0555 1.0000 0.0570
-19.250 -1.0990 0.08216 0.07704 -0.0566 1.0000 0.0580
-19.000 -1.1050 0.07848 0.07332 -0.0576 1.0000 0.0591
-18.750 -1.1090 0.07512 0.06990 -0.0584 1.0000 0.0601
-18.500 -1.1129 0.07179 0.06650 -0.0592 1.0000 0.0613
-18.250 -1.1159 0.06858 0.06321 -0.0598 1.0000 0.0627
-18.000 -1.1238 0.06493 0.05953 -0.0605 1.0000 0.0639
-17.750 -1.1307 0.06146 0.05602 -0.0610 1.0000 0.0655
-17.500 -1.1342 0.05843 0.05294 -0.0613 1.0000 0.0670
-17.250 -1.1358 0.05565 0.05010 -0.0615 1.0000 0.0687
-17.000 -1.1401 0.05267 0.04708 -0.0616 1.0000 0.0707
-16.750 -1.1433 0.04988 0.04427 -0.0615 1.0000 0.0730
-16.500 -1.1434 0.04747 0.04181 -0.0613 1.0000 0.0759
-16.250 -1.1448 0.04501 0.03933 -0.0609 1.0000 0.0789
-16.000 -1.1433 0.04289 0.03719 -0.0605 1.0000 0.0828
-15.750 -1.1413 0.04089 0.03516 -0.0599 1.0000 0.0866
-15.500 -1.1392 0.03896 0.03322 -0.0591 1.0000 0.0910
-15.250 -1.1350 0.03729 0.03150 -0.0582 1.0000 0.0954
-15.000 -1.1344 0.03542 0.02963 -0.0571 1.0000 0.0993
-14.750 -1.1256 0.03426 0.02839 -0.0561 1.0000 0.1035
-14.500 -1.1275 0.03241 0.02654 -0.0544 1.0000 0.1070
-14.250 -1.1251 0.03096 0.02508 -0.0528 1.0000 0.1108
-14.000 -1.1175 0.02994 0.02398 -0.0513 1.0000 0.1140
-13.750 -1.1187 0.02847 0.02251 -0.0490 1.0000 0.1174
-13.500 -1.1181 0.02722 0.02126 -0.0466 1.0000 0.1209
-13.250 -1.1142 0.02626 0.02027 -0.0442 1.0000 0.1240
-13.000 -1.1120 0.02531 0.01929 -0.0415 1.0000 0.1270
-12.750 -1.1144 0.02426 0.01824 -0.0382 1.0000 0.1305
-12.500 -1.1148 0.02342 0.01740 -0.0349 1.0000 0.1339
-12.250 -1.1141 0.02272 0.01667 -0.0314 1.0000 0.1371
-12.000 -1.1182 0.02195 0.01591 -0.0273 1.0000 0.1411
-11.750 -1.1230 0.02129 0.01527 -0.0229 1.0000 0.1453
-11.500 -1.1066 0.02059 0.01459 -0.0223 0.9986 0.1525
-11.250 -1.0756 0.01990 0.01394 -0.0244 0.9957 0.1631
-11.000 -1.0439 0.01927 0.01335 -0.0265 0.9928 0.1743
-10.750 -1.0143 0.01868 0.01278 -0.0280 0.9894 0.1834
-10.500 -0.9825 0.01827 0.01234 -0.0296 0.9859 0.1924
-10.250 -0.9531 0.01769 0.01180 -0.0310 0.9827 0.2001
-10.000 -0.9190 0.01733 0.01140 -0.0330 0.9806 0.2074
-9.750 -0.8861 0.01684 0.01092 -0.0349 0.9788 0.2141
-9.500 -0.8623 0.01637 0.01046 -0.0349 0.9730 0.2197
-9.250 -0.8295 0.01606 0.01009 -0.0364 0.9698 0.2250
-9.000 -0.7982 0.01552 0.00959 -0.0379 0.9672 0.2312
-8.750 -0.7639 0.01507 0.00915 -0.0399 0.9654 0.2371
-8.500 -0.7265 0.01474 0.00877 -0.0423 0.9641 0.2422
-8.250 -0.7053 0.01428 0.00834 -0.0415 0.9567 0.2473
-8.000 -0.6720 0.01382 0.00791 -0.0432 0.9535 0.2537
-7.750 -0.6331 0.01347 0.00753 -0.0459 0.9513 0.2598
-7.500 -0.5961 0.01295 0.00707 -0.0484 0.9488 0.2677
-7.250 -0.5713 0.01261 0.00674 -0.0481 0.9404 0.2740
-7.000 -0.5386 0.01221 0.00635 -0.0495 0.9347 0.2820
-6.750 -0.5096 0.01183 0.00600 -0.0502 0.9276 0.2919
-6.500 -0.4876 0.01147 0.00569 -0.0493 0.9178 0.3033
-6.250 -0.4646 0.01114 0.00539 -0.0487 0.9088 0.3181
-6.000 -0.4450 0.01081 0.00512 -0.0473 0.8986 0.3354
-5.750 -0.4276 0.01054 0.00489 -0.0454 0.8884 0.3531
-5.500 -0.4071 0.01029 0.00465 -0.0440 0.8788 0.3704
-5.250 -0.3909 0.01011 0.00448 -0.0417 0.8679 0.3854
-5.000 -0.3708 0.00990 0.00427 -0.0402 0.8583 0.3995
-4.750 -0.3555 0.00976 0.00415 -0.0376 0.8474 0.4116
-4.500 -0.3333 0.00964 0.00398 -0.0364 0.8382 0.4240
-4.250 -0.3202 0.00951 0.00390 -0.0334 0.8271 0.4350
-4.000 -0.2995 0.00943 0.00377 -0.0319 0.8172 0.4466
-3.750 -0.2859 0.00935 0.00371 -0.0288 0.8047 0.4573
-3.500 -0.2685 0.00929 0.00363 -0.0265 0.7932 0.4674
-3.250 -0.2521 0.00924 0.00356 -0.0240 0.7804 0.4781
-3.000 -0.2349 0.00918 0.00350 -0.0218 0.7673 0.4879
-2.750 -0.2153 0.00914 0.00343 -0.0199 0.7554 0.4981
-2.500 -0.1974 0.00907 0.00337 -0.0178 0.7417 0.5084
-2.250 -0.1787 0.00905 0.00332 -0.0158 0.7275 0.5195
-2.000 -0.1604 0.00900 0.00326 -0.0137 0.7131 0.5302
-1.500 -0.1214 0.00896 0.00318 -0.0100 0.6853 0.5504
-1.250 -0.1011 0.00898 0.00314 -0.0083 0.6713 0.5599
-1.000 -0.0817 0.00897 0.00311 -0.0065 0.6571 0.5692
-0.750 -0.0614 0.00900 0.00308 -0.0048 0.6438 0.5789
-0.500 -0.0410 0.00898 0.00307 -0.0032 0.6317 0.5884
-0.250 -0.0206 0.00903 0.00306 -0.0016 0.6196 0.5983
0.000 0.0000 0.00899 0.00306 0.0000 0.6083 0.6083
0.250 0.0206 0.00903 0.00306 0.0016 0.5983 0.6197
0.500 0.0409 0.00898 0.00307 0.0032 0.5883 0.6318
0.750 0.0615 0.00900 0.00308 0.0048 0.5789 0.6437
1.000 0.0818 0.00897 0.00311 0.0065 0.5692 0.6570
1.250 0.1012 0.00898 0.00314 0.0083 0.5599 0.6709
1.500 0.1214 0.00896 0.00318 0.0100 0.5503 0.6852
2.000 0.1603 0.00900 0.00326 0.0137 0.5302 0.7134
2.250 0.1787 0.00905 0.00332 0.0158 0.5195 0.7275
2.500 0.1975 0.00907 0.00337 0.0177 0.5086 0.7417
2.750 0.2153 0.00914 0.00343 0.0199 0.4983 0.7554
3.000 0.2349 0.00918 0.00350 0.0218 0.4879 0.7675
3.250 0.2522 0.00924 0.00356 0.0240 0.4781 0.7804
3.500 0.2686 0.00929 0.00363 0.0265 0.4674 0.7930
3.750 0.2859 0.00935 0.00371 0.0288 0.4573 0.8048
4.000 0.2997 0.00943 0.00377 0.0318 0.4466 0.8170
4.250 0.3203 0.00951 0.00390 0.0334 0.4351 0.8271
4.500 0.3334 0.00964 0.00398 0.0364 0.4239 0.8382
4.750 0.3556 0.00976 0.00415 0.0376 0.4117 0.8475
5.000 0.3709 0.00989 0.00427 0.0402 0.3996 0.8583
5.250 0.3910 0.01011 0.00448 0.0417 0.3855 0.8680
5.500 0.4071 0.01029 0.00465 0.0440 0.3702 0.8788
5.750 0.4276 0.01055 0.00489 0.0453 0.3528 0.8882
6.000 0.4448 0.01082 0.00511 0.0473 0.3350 0.8985
6.250 0.4644 0.01114 0.00539 0.0487 0.3178 0.9090
6.500 0.4877 0.01147 0.00568 0.0493 0.3032 0.9178
6.750 0.5097 0.01183 0.00600 0.0502 0.2916 0.9276
7.000 0.5388 0.01221 0.00635 0.0495 0.2821 0.9347
7.250 0.5716 0.01261 0.00674 0.0481 0.2740 0.9405
7.500 0.5965 0.01295 0.00707 0.0483 0.2674 0.9489
7.750 0.6334 0.01347 0.00753 0.0458 0.2598 0.9513
8.000 0.6725 0.01382 0.00791 0.0431 0.2539 0.9535
8.250 0.7057 0.01428 0.00833 0.0415 0.2473 0.9567
8.500 0.7270 0.01473 0.00877 0.0422 0.2422 0.9641
8.750 0.7646 0.01507 0.00914 0.0398 0.2372 0.9655
9.000 0.7988 0.01551 0.00958 0.0378 0.2312 0.9673
9.250 0.8300 0.01605 0.01008 0.0363 0.2249 0.9699
9.500 0.8628 0.01637 0.01046 0.0348 0.2194 0.9731
9.750 0.8867 0.01684 0.01091 0.0348 0.2137 0.9789
10.000 0.9198 0.01732 0.01139 0.0329 0.2073 0.9806
10.250 0.9538 0.01768 0.01179 0.0309 0.2001 0.9828
10.500 0.9833 0.01826 0.01232 0.0294 0.1924 0.9859
10.750 1.0150 0.01867 0.01276 0.0278 0.1832 0.9895
11.000 1.0449 0.01925 0.01334 0.0263 0.1743 0.9928
11.250 1.0768 0.01988 0.01392 0.0242 0.1631 0.9958
11.500 1.1074 0.02058 0.01457 0.0222 0.1521 0.9987
11.750 1.1232 0.02126 0.01524 0.0229 0.1453 1.0000
12.000 1.1182 0.02192 0.01588 0.0273 0.1410 1.0000
12.250 1.1142 0.02269 0.01664 0.0314 0.1370 1.0000
12.500 1.1151 0.02338 0.01736 0.0348 0.1339 1.0000
12.750 1.1143 0.02424 0.01822 0.0382 0.1303 1.0000
13.000 1.1121 0.02529 0.01926 0.0415 0.1269 1.0000
13.250 1.1149 0.02621 0.02022 0.0442 0.1239 1.0000
13.500 1.1184 0.02720 0.02123 0.0466 0.1205 1.0000
13.750 1.1191 0.02844 0.02248 0.0489 0.1173 1.0000
14.000 1.1184 0.02989 0.02393 0.0512 0.1141 1.0000
14.250 1.1261 0.03091 0.02502 0.0527 0.1108 1.0000
14.500 1.1289 0.03234 0.02647 0.0543 0.1072 1.0000
14.750 1.1269 0.03419 0.02832 0.0560 0.1035 1.0000
15.000 1.1357 0.03536 0.02956 0.0570 0.0994 1.0000
15.250 1.1365 0.03722 0.03142 0.0581 0.0954 1.0000
15.500 1.1410 0.03887 0.03312 0.0589 0.0909 1.0000
15.750 1.1432 0.04079 0.03506 0.0597 0.0867 1.0000
16.000 1.1455 0.04277 0.03707 0.0603 0.0826 1.0000
16.250 1.1470 0.04490 0.03921 0.0607 0.0788 1.0000
16.500 1.1459 0.04734 0.04168 0.0611 0.0757 1.0000
16.750 1.1460 0.04974 0.04412 0.0613 0.0730 1.0000
17.000 1.1431 0.05251 0.04691 0.0613 0.0707 1.0000
17.250 1.1380 0.05557 0.05001 0.0612 0.0688 1.0000
17.500 1.1375 0.05825 0.05275 0.0610 0.0670 1.0000
17.750 1.1336 0.06133 0.05588 0.0607 0.0654 1.0000
18.000 1.1259 0.06491 0.05949 0.0601 0.0637 1.0000
18.250 1.1177 0.06860 0.06322 0.0595 0.0625 1.0000
18.500 1.1160 0.07166 0.06636 0.0588 0.0614 1.0000
18.750 1.1128 0.07491 0.06968 0.0581 0.0602 1.0000
19.000 1.1085 0.07834 0.07317 0.0572 0.0590 1.0000
19.250 1.1017 0.08212 0.07700 0.0562 0.0578 1.0000
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