GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 500,000 Max Cl/Cd: 93.04 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe387-il-500000-n5.txt Download as CSV file: xf-goe387-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0325 0.08553 0.08230 -0.1106 0.8459 0.0258
-10.500 -0.0109 0.08590 0.08258 -0.1098 0.8281 0.0250
-10.250 -0.0065 0.08299 0.07960 -0.1109 0.8131 0.0245
-10.000 -0.0067 0.07941 0.07595 -0.1123 0.7992 0.0251
-9.750 -0.0051 0.07637 0.07287 -0.1132 0.7867 0.0247
-9.500 -0.0062 0.07296 0.06941 -0.1143 0.7761 0.0244
-9.250 -0.0104 0.06915 0.06557 -0.1156 0.7655 0.0246
-8.750 -0.1879 0.03711 0.03310 -0.1291 0.7426 0.0232
-8.500 -0.2063 0.03277 0.02839 -0.1268 0.7342 0.0233
-8.250 -0.2011 0.03085 0.02624 -0.1251 0.7260 0.0235
-8.000 -0.1948 0.02875 0.02389 -0.1232 0.7189 0.0237
-7.750 -0.1846 0.02696 0.02184 -0.1215 0.7118 0.0239
-7.250 -0.1586 0.02360 0.01795 -0.1181 0.6991 0.0241
-7.000 -0.1419 0.02228 0.01639 -0.1166 0.6926 0.0243
-6.500 -0.1037 0.02012 0.01380 -0.1140 0.6811 0.0246
-6.250 -0.0828 0.01921 0.01270 -0.1128 0.6750 0.0248
-5.750 -0.0386 0.01768 0.01082 -0.1108 0.6638 0.0251
-5.500 -0.0154 0.01704 0.01003 -0.1099 0.6578 0.0253
-5.250 0.0080 0.01646 0.00930 -0.1090 0.6521 0.0255
-5.000 0.0322 0.01595 0.00868 -0.1082 0.6459 0.0256
-4.750 0.0565 0.01553 0.00814 -0.1074 0.6386 0.0258
-4.500 0.0806 0.01515 0.00763 -0.1065 0.6318 0.0259
-4.250 0.1049 0.01452 0.00699 -0.1059 0.6261 0.0263
-4.000 0.1297 0.01412 0.00657 -0.1052 0.6205 0.0266
-3.750 0.1544 0.01380 0.00619 -0.1045 0.6155 0.0269
-3.500 0.1796 0.01346 0.00582 -0.1038 0.6112 0.0271
-3.250 0.2049 0.01314 0.00549 -0.1032 0.6064 0.0273
-3.000 0.2299 0.01287 0.00518 -0.1025 0.6010 0.0276
-2.500 0.2801 0.01238 0.00463 -0.1012 0.5911 0.0282
-2.250 0.3053 0.01216 0.00438 -0.1005 0.5860 0.0286
-2.000 0.3303 0.01197 0.00416 -0.0998 0.5810 0.0289
-1.750 0.3554 0.01180 0.00397 -0.0991 0.5762 0.0293
-1.500 0.3809 0.01163 0.00379 -0.0985 0.5706 0.0296
-1.250 0.4060 0.01152 0.00364 -0.0978 0.5645 0.0299
-1.000 0.4303 0.01133 0.00344 -0.0970 0.5584 0.0304
-0.750 0.4556 0.01118 0.00330 -0.0963 0.5521 0.0311
-0.500 0.4804 0.01110 0.00320 -0.0956 0.5456 0.0320
-0.250 0.5056 0.01103 0.00311 -0.0949 0.5395 0.0329
0.000 0.5308 0.01097 0.00303 -0.0943 0.5322 0.0336
0.250 0.5553 0.01095 0.00297 -0.0935 0.5251 0.0342
0.500 0.5803 0.01089 0.00290 -0.0928 0.5169 0.0352
0.750 0.6039 0.01089 0.00285 -0.0918 0.5076 0.0367
1.000 0.6280 0.01090 0.00283 -0.0909 0.4965 0.0384
1.250 0.6512 0.01093 0.00282 -0.0899 0.4850 0.0416
1.500 0.6720 0.01079 0.00283 -0.0885 0.4742 0.1141
1.750 0.6928 0.01058 0.00290 -0.0872 0.4637 0.2213
2.000 0.7135 0.01047 0.00300 -0.0858 0.4548 0.3130
2.250 0.7343 0.01040 0.00310 -0.0844 0.4451 0.3875
2.500 0.7476 0.00997 0.00325 -0.0817 0.4362 0.6077
3.000 0.9133 0.01002 0.00393 -0.1058 0.4044 1.0000
3.250 0.9341 0.01019 0.00405 -0.1044 0.3966 1.0000
3.500 0.9536 0.01040 0.00419 -0.1027 0.3894 1.0000
3.750 0.9746 0.01056 0.00431 -0.1013 0.3827 1.0000
4.000 0.9944 0.01076 0.00447 -0.0997 0.3763 1.0000
4.250 1.0142 0.01096 0.00462 -0.0981 0.3711 1.0000
4.500 1.0348 0.01113 0.00477 -0.0967 0.3660 1.0000
4.750 1.0541 0.01133 0.00494 -0.0950 0.3606 1.0000
5.000 1.0722 0.01157 0.00513 -0.0932 0.3555 1.0000
5.250 1.0921 0.01175 0.00530 -0.0917 0.3505 1.0000
5.500 1.1104 0.01195 0.00549 -0.0898 0.3458 1.0000
5.750 1.1253 0.01219 0.00569 -0.0873 0.3409 1.0000
6.000 1.1415 0.01240 0.00589 -0.0851 0.3368 1.0000
6.250 1.1589 0.01260 0.00609 -0.0832 0.3320 1.0000
6.500 1.1758 0.01283 0.00632 -0.0812 0.3278 1.0000
6.750 1.1916 0.01312 0.00658 -0.0790 0.3236 1.0000
7.000 1.2091 0.01337 0.00684 -0.0773 0.3196 1.0000
7.250 1.2277 0.01361 0.00710 -0.0757 0.3158 1.0000
7.500 1.2453 0.01390 0.00739 -0.0740 0.3116 1.0000
7.750 1.2619 0.01424 0.00772 -0.0723 0.3077 1.0000
8.000 1.2786 0.01459 0.00807 -0.0706 0.3041 1.0000
8.250 1.2974 0.01488 0.00840 -0.0692 0.3000 1.0000
8.500 1.3147 0.01524 0.00877 -0.0677 0.2951 1.0000
8.750 1.3284 0.01576 0.00925 -0.0658 0.2887 1.0000
9.000 1.3460 0.01614 0.00966 -0.0644 0.2821 1.0000
9.250 1.3597 0.01671 0.01021 -0.0626 0.2742 1.0000
9.500 1.3758 0.01721 0.01072 -0.0612 0.2682 1.0000
9.750 1.3908 0.01777 0.01129 -0.0597 0.2611 1.0000
10.000 1.4047 0.01842 0.01194 -0.0582 0.2543 1.0000
10.250 1.4172 0.01917 0.01268 -0.0565 0.2448 1.0000
10.500 1.4288 0.02001 0.01350 -0.0549 0.2336 1.0000
10.750 1.4385 0.02100 0.01445 -0.0532 0.2219 1.0000
11.000 1.4457 0.02219 0.01560 -0.0513 0.2085 1.0000
11.250 1.4505 0.02359 0.01694 -0.0494 0.1953 1.0000
11.500 1.4564 0.02498 0.01830 -0.0477 0.1866 1.0000
11.750 1.4651 0.02622 0.01955 -0.0464 0.1810 1.0000
12.000 1.4729 0.02756 0.02090 -0.0450 0.1761 1.0000
12.250 1.4806 0.02894 0.02231 -0.0437 0.1722 1.0000
12.500 1.4895 0.03026 0.02367 -0.0426 0.1681 1.0000
12.750 1.4956 0.03183 0.02526 -0.0415 0.1637 1.0000
13.000 1.5020 0.03341 0.02687 -0.0404 0.1606 1.0000
13.250 1.5088 0.03501 0.02851 -0.0394 0.1565 1.0000
13.500 1.5175 0.03648 0.03003 -0.0386 0.1534 1.0000
13.750 1.5232 0.03822 0.03181 -0.0377 0.1495 1.0000
14.000 1.5273 0.04016 0.03379 -0.0368 0.1462 1.0000
14.250 1.5329 0.04201 0.03569 -0.0361 0.1431 1.0000
14.500 1.5414 0.04360 0.03734 -0.0355 0.1401 1.0000
14.750 1.5455 0.04564 0.03942 -0.0348 0.1348 1.0000
15.000 1.5465 0.04804 0.04185 -0.0342 0.1304 1.0000
15.250 1.5527 0.04994 0.04381 -0.0337 0.1257 1.0000
15.500 1.5516 0.05263 0.04651 -0.0332 0.1184 1.0000
15.750 1.5500 0.05543 0.04932 -0.0328 0.1091 1.0000
16.000 1.5456 0.05858 0.05247 -0.0324 0.1006 1.0000
16.250 1.5365 0.06235 0.05622 -0.0322 0.0921 1.0000
16.500 1.5304 0.06584 0.05974 -0.0320 0.0871 1.0000
16.750 1.5241 0.06940 0.06334 -0.0320 0.0828 1.0000
17.000 1.5170 0.07316 0.06715 -0.0321 0.0794 1.0000
17.250 1.5117 0.07678 0.07083 -0.0323 0.0768 1.0000
17.500 1.5086 0.08013 0.07426 -0.0325 0.0750 1.0000
17.750 1.5033 0.08379 0.07798 -0.0328 0.0727 1.0000
18.000 1.4959 0.08779 0.08205 -0.0333 0.0705 1.0000
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