GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 500,000 Max Cl/Cd: 107.19 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe480-il-500000-n5.txt Download as CSV file: xf-goe480-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 480 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2841 0.10382 0.10131 -0.0530 0.9884 0.0259
-11.000 -0.2708 0.10072 0.09820 -0.0559 0.9817 0.0265
-10.750 -0.2772 0.09258 0.09004 -0.0621 0.9732 0.0289
-10.500 -0.2582 0.08994 0.08738 -0.0656 0.9641 0.0292
-10.250 -0.2325 0.08766 0.08508 -0.0698 0.9552 0.0297
-10.000 -0.2056 0.08394 0.08132 -0.0763 0.9466 0.0304
-9.750 -0.1991 0.07343 0.07073 -0.0901 0.9316 0.0334
-9.500 -0.1627 0.07096 0.06818 -0.0969 0.9140 0.0339
-9.250 -0.1370 0.06802 0.06512 -0.1025 0.8886 0.0343
-9.000 -0.1259 0.06556 0.06252 -0.1048 0.8609 0.0348
-8.750 -0.1265 0.06275 0.05961 -0.1059 0.8373 0.0353
-8.500 -0.2211 0.04272 0.03932 -0.1207 0.8072 0.0387
-8.250 -0.2129 0.03895 0.03538 -0.1228 0.7961 0.0392
-8.000 -0.2083 0.03358 0.02975 -0.1248 0.7860 0.0400
-7.750 -0.2089 0.02741 0.02304 -0.1257 0.7775 0.0412
-7.500 -0.1988 0.02383 0.01897 -0.1253 0.7695 0.0422
-7.250 -0.1820 0.02167 0.01639 -0.1246 0.7627 0.0432
-7.000 -0.1617 0.02016 0.01458 -0.1240 0.7562 0.0438
-6.750 -0.1392 0.01918 0.01335 -0.1234 0.7497 0.0441
-6.500 -0.1159 0.01835 0.01230 -0.1228 0.7441 0.0444
-6.250 -0.0929 0.01725 0.01106 -0.1223 0.7381 0.0448
-6.000 -0.0681 0.01667 0.01039 -0.1219 0.7324 0.0452
-5.750 -0.0427 0.01627 0.00992 -0.1215 0.7272 0.0456
-5.500 -0.0170 0.01582 0.00939 -0.1211 0.7216 0.0460
-5.250 0.0086 0.01535 0.00883 -0.1207 0.7161 0.0463
-4.750 0.0605 0.01447 0.00775 -0.1199 0.7058 0.0470
-4.500 0.0866 0.01405 0.00724 -0.1196 0.7002 0.0474
-4.250 0.1127 0.01368 0.00677 -0.1191 0.6948 0.0478
-4.000 0.1392 0.01331 0.00633 -0.1188 0.6898 0.0482
-3.750 0.1657 0.01296 0.00592 -0.1184 0.6841 0.0486
-3.500 0.1921 0.01266 0.00554 -0.1180 0.6784 0.0491
-3.250 0.2187 0.01238 0.00520 -0.1177 0.6731 0.0496
-3.000 0.2455 0.01213 0.00490 -0.1174 0.6670 0.0501
-2.750 0.2721 0.01195 0.00466 -0.1170 0.6608 0.0506
-2.500 0.2989 0.01174 0.00440 -0.1166 0.6551 0.0510
-2.250 0.3256 0.01154 0.00416 -0.1162 0.6482 0.0513
-2.000 0.3520 0.01139 0.00396 -0.1158 0.6416 0.0515
-1.750 0.3781 0.01102 0.00358 -0.1154 0.6348 0.0521
-1.500 0.4041 0.01078 0.00332 -0.1149 0.6272 0.0528
-1.250 0.4304 0.01062 0.00314 -0.1145 0.6199 0.0534
-1.000 0.4567 0.01049 0.00299 -0.1140 0.6118 0.0540
-0.750 0.4829 0.01039 0.00287 -0.1136 0.6040 0.0546
-0.500 0.5092 0.01030 0.00277 -0.1131 0.5953 0.0554
-0.250 0.5353 0.01024 0.00268 -0.1127 0.5870 0.0563
0.000 0.5613 0.01020 0.00261 -0.1122 0.5776 0.0574
0.250 0.5874 0.01017 0.00256 -0.1117 0.5690 0.0583
0.500 0.6131 0.01016 0.00251 -0.1112 0.5595 0.0591
0.750 0.6391 0.01015 0.00247 -0.1107 0.5506 0.0598
1.000 0.6646 0.01018 0.00246 -0.1101 0.5412 0.0603
1.250 0.6905 0.01015 0.00242 -0.1096 0.5322 0.0619
1.500 0.7155 0.01019 0.00242 -0.1089 0.5225 0.0636
1.750 0.7413 0.01022 0.00244 -0.1084 0.5128 0.0656
2.000 0.7664 0.01028 0.00248 -0.1078 0.5039 0.0678
2.250 0.7919 0.01034 0.00252 -0.1073 0.4945 0.0709
2.500 0.8170 0.01039 0.00259 -0.1066 0.4864 0.0800
2.750 0.8416 0.01029 0.00271 -0.1060 0.4783 0.1632
3.000 0.8660 0.01033 0.00282 -0.1054 0.4704 0.2067
3.250 0.8897 0.01018 0.00297 -0.1046 0.4618 0.3294
3.500 0.9081 0.00970 0.00318 -0.1030 0.4544 0.6284
4.000 0.9921 0.00943 0.00356 -0.1092 0.4362 1.0000
4.250 1.0158 0.00959 0.00369 -0.1083 0.4273 1.0000
4.500 1.0388 0.00978 0.00384 -0.1074 0.4193 1.0000
4.750 1.0624 0.00995 0.00399 -0.1065 0.4113 1.0000
5.000 1.0850 0.01016 0.00416 -0.1055 0.4037 1.0000
5.250 1.1083 0.01034 0.00432 -0.1045 0.3953 1.0000
5.500 1.1301 0.01057 0.00451 -0.1034 0.3862 1.0000
5.750 1.1516 0.01082 0.00471 -0.1022 0.3745 1.0000
6.000 1.1729 0.01106 0.00493 -0.1010 0.3627 1.0000
6.250 1.1934 0.01134 0.00516 -0.0996 0.3523 1.0000
6.500 1.2145 0.01158 0.00539 -0.0984 0.3432 1.0000
6.750 1.2349 0.01185 0.00564 -0.0970 0.3342 1.0000
7.000 1.2535 0.01218 0.00592 -0.0953 0.3232 1.0000
7.250 1.2727 0.01246 0.00618 -0.0938 0.3126 1.0000
7.500 1.2895 0.01277 0.00648 -0.0918 0.3043 1.0000
7.750 1.3063 0.01309 0.00678 -0.0898 0.2944 1.0000
8.000 1.3220 0.01346 0.00712 -0.0877 0.2839 1.0000
8.250 1.3365 0.01388 0.00750 -0.0854 0.2728 1.0000
8.500 1.3504 0.01435 0.00793 -0.0831 0.2597 1.0000
8.750 1.3638 0.01486 0.00838 -0.0808 0.2455 1.0000
9.000 1.3760 0.01545 0.00891 -0.0784 0.2306 1.0000
9.250 1.3892 0.01601 0.00944 -0.0763 0.2188 1.0000
9.500 1.4011 0.01666 0.01005 -0.0740 0.2060 1.0000
9.750 1.4120 0.01738 0.01072 -0.0717 0.1922 1.0000
10.000 1.4225 0.01816 0.01145 -0.0695 0.1784 1.0000
10.250 1.4316 0.01905 0.01228 -0.0672 0.1629 1.0000
10.500 1.4365 0.02023 0.01336 -0.0645 0.1408 1.0000
10.750 1.4384 0.02168 0.01468 -0.0618 0.1171 1.0000
11.000 1.4357 0.02351 0.01636 -0.0588 0.0916 1.0000
11.250 1.4390 0.02506 0.01785 -0.0566 0.0789 1.0000
11.500 1.4445 0.02650 0.01929 -0.0548 0.0710 1.0000
11.750 1.4498 0.02803 0.02082 -0.0531 0.0647 1.0000
12.000 1.4578 0.02941 0.02224 -0.0518 0.0603 1.0000
12.250 1.4630 0.03103 0.02388 -0.0503 0.0561 1.0000
12.500 1.4709 0.03250 0.02539 -0.0491 0.0527 1.0000
12.750 1.4760 0.03423 0.02715 -0.0479 0.0488 1.0000
13.000 1.4819 0.03594 0.02890 -0.0468 0.0458 1.0000
13.250 1.4871 0.03774 0.03075 -0.0458 0.0420 1.0000
13.500 1.4908 0.03974 0.03279 -0.0448 0.0388 1.0000
13.750 1.4943 0.04181 0.03490 -0.0439 0.0356 1.0000
14.000 1.4962 0.04409 0.03721 -0.0431 0.0329 1.0000
14.250 1.4988 0.04637 0.03955 -0.0424 0.0307 1.0000
14.500 1.4998 0.04889 0.04211 -0.0418 0.0288 1.0000
14.750 1.5004 0.05150 0.04478 -0.0413 0.0272 1.0000
15.000 1.5016 0.05412 0.04748 -0.0409 0.0259 1.0000
15.250 1.5014 0.05697 0.05040 -0.0406 0.0248 1.0000
15.500 1.4993 0.06012 0.05362 -0.0405 0.0236 1.0000
15.750 1.4979 0.06325 0.05683 -0.0405 0.0228 1.0000
16.000 1.4971 0.06636 0.06002 -0.0405 0.0220 1.0000
16.250 1.4949 0.06971 0.06346 -0.0407 0.0210 1.0000
16.500 1.4916 0.07329 0.06712 -0.0411 0.0203 1.0000
16.750 1.4878 0.07698 0.07090 -0.0415 0.0198 1.0000
17.000 1.4820 0.08100 0.07499 -0.0421 0.0192 1.0000
17.250 1.4788 0.08473 0.07882 -0.0427 0.0187 1.0000
17.500 1.4749 0.08862 0.08280 -0.0435 0.0183 1.0000
17.750 1.4704 0.09264 0.08693 -0.0443 0.0178 1.0000
18.000 1.4652 0.09682 0.09119 -0.0453 0.0173 1.0000
18.250 1.4598 0.10107 0.09554 -0.0465 0.0169 1.0000
18.500 1.4537 0.10551 0.10005 -0.0478 0.0165 1.0000
18.750 1.4470 0.11011 0.10474 -0.0492 0.0161 1.0000
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