GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 496 AIRFOIL (goe496-il) Reynolds number: 100,000 Max Cl/Cd: 64.97 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe496-il-100000-n5.txt Download as CSV file: xf-goe496-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 496 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3418 0.09605 0.09115 -0.0372 1.0000 0.0517
-8.250 -0.3520 0.09390 0.08908 -0.0357 1.0000 0.0516
-8.000 -0.3657 0.09188 0.08715 -0.0338 1.0000 0.0514
-7.750 -0.3581 0.08694 0.08222 -0.0392 0.9938 0.0510
-7.500 -0.3473 0.08090 0.07617 -0.0469 0.9854 0.0503
-7.250 -0.3296 0.07564 0.07088 -0.0540 0.9769 0.0510
-7.000 -0.3102 0.07108 0.06630 -0.0607 0.9686 0.0529
-6.750 -0.2907 0.06398 0.05913 -0.0713 0.9594 0.0536
-6.500 -0.2641 0.04635 0.04108 -0.0964 0.9484 0.0531
-6.250 -0.2248 0.03458 0.02821 -0.1127 0.9427 0.0550
-6.000 -0.1933 0.03042 0.02332 -0.1172 0.9359 0.0572
-5.750 -0.1573 0.02752 0.01978 -0.1207 0.9314 0.0584
-5.500 -0.1221 0.02550 0.01732 -0.1231 0.9270 0.0594
-5.250 -0.0924 0.02410 0.01576 -0.1241 0.9202 0.0609
-5.000 -0.0559 0.02311 0.01467 -0.1262 0.9163 0.0635
-4.750 -0.0258 0.02230 0.01371 -0.1269 0.9096 0.0665
-4.500 0.0083 0.02131 0.01250 -0.1282 0.9043 0.0693
-4.250 0.0455 0.02037 0.01144 -0.1301 0.9008 0.0719
-4.000 0.0731 0.01986 0.01092 -0.1302 0.8925 0.0751
-3.750 0.1078 0.01925 0.01021 -0.1314 0.8875 0.0802
-3.500 0.1406 0.01878 0.00971 -0.1324 0.8817 0.0879
-3.250 0.1710 0.01836 0.00925 -0.1328 0.8743 0.0998
-3.000 0.2070 0.01782 0.00866 -0.1343 0.8698 0.1176
-2.750 0.2352 0.01751 0.00831 -0.1343 0.8613 0.1357
-2.500 0.2687 0.01714 0.00793 -0.1354 0.8554 0.1557
-2.250 0.2994 0.01687 0.00768 -0.1359 0.8483 0.1739
-2.000 0.3303 0.01662 0.00746 -0.1364 0.8409 0.1947
-1.750 0.3630 0.01636 0.00726 -0.1372 0.8346 0.2201
-1.500 0.3914 0.01619 0.00716 -0.1372 0.8259 0.2468
-1.250 0.4249 0.01592 0.00693 -0.1380 0.8198 0.2782
-1.000 0.4518 0.01582 0.00688 -0.1377 0.8104 0.3092
-0.750 0.4843 0.01562 0.00672 -0.1383 0.8039 0.3445
-0.500 0.5109 0.01558 0.00673 -0.1379 0.7942 0.3764
-0.250 0.5421 0.01547 0.00664 -0.1382 0.7870 0.4110
0.000 0.5695 0.01544 0.00666 -0.1380 0.7776 0.4457
0.250 0.5987 0.01536 0.00662 -0.1380 0.7695 0.4831
0.500 0.6265 0.01527 0.00664 -0.1377 0.7607 0.5227
0.750 0.6532 0.01515 0.00671 -0.1372 0.7519 0.5790
1.000 0.6787 0.01485 0.00672 -0.1363 0.7436 0.6923
1.250 0.7036 0.01442 0.00668 -0.1350 0.7344 1.0000
1.500 0.7338 0.01452 0.00665 -0.1352 0.7265 1.0000
1.750 0.7600 0.01472 0.00678 -0.1348 0.7165 1.0000
2.000 0.7885 0.01485 0.00682 -0.1347 0.7075 1.0000
2.250 0.8157 0.01498 0.00688 -0.1343 0.6964 1.0000
2.500 0.8416 0.01513 0.00697 -0.1337 0.6837 1.0000
2.750 0.8677 0.01525 0.00702 -0.1331 0.6699 1.0000
3.000 0.8936 0.01537 0.00709 -0.1324 0.6554 1.0000
3.250 0.9196 0.01552 0.00718 -0.1317 0.6421 1.0000
3.500 0.9463 0.01568 0.00729 -0.1313 0.6307 1.0000
3.750 0.9714 0.01591 0.00753 -0.1306 0.6188 1.0000
4.000 0.9967 0.01613 0.00776 -0.1300 0.6071 1.0000
4.250 1.0223 0.01635 0.00797 -0.1293 0.5955 1.0000
4.500 1.0480 0.01657 0.00819 -0.1287 0.5838 1.0000
4.750 1.0723 0.01683 0.00847 -0.1279 0.5705 1.0000
5.000 1.0965 0.01709 0.00878 -0.1271 0.5572 1.0000
5.250 1.1206 0.01737 0.00908 -0.1262 0.5434 1.0000
5.500 1.1441 0.01767 0.00942 -0.1253 0.5286 1.0000
5.750 1.1671 0.01798 0.00976 -0.1242 0.5128 1.0000
6.000 1.1896 0.01831 0.01013 -0.1231 0.4962 1.0000
6.250 1.2114 0.01867 0.01054 -0.1219 0.4782 1.0000
6.500 1.2324 0.01906 0.01093 -0.1205 0.4584 1.0000
6.750 1.2523 0.01949 0.01141 -0.1190 0.4363 1.0000
7.000 1.2713 0.01998 0.01188 -0.1174 0.4130 1.0000
7.250 1.2885 0.02054 0.01241 -0.1155 0.3856 1.0000
7.500 1.3028 0.02124 0.01300 -0.1131 0.3535 1.0000
7.750 1.3151 0.02207 0.01366 -0.1106 0.3217 1.0000
8.000 1.3271 0.02296 0.01442 -0.1082 0.2944 1.0000
8.250 1.3394 0.02386 0.01524 -0.1058 0.2742 1.0000
8.500 1.3506 0.02476 0.01610 -0.1034 0.2565 1.0000
8.750 1.3607 0.02569 0.01704 -0.1007 0.2380 1.0000
9.000 1.3692 0.02671 0.01803 -0.0980 0.2181 1.0000
9.250 1.3762 0.02783 0.01910 -0.0953 0.1975 1.0000
9.500 1.3841 0.02895 0.02022 -0.0928 0.1753 1.0000
9.750 1.3904 0.03021 0.02146 -0.0903 0.1510 1.0000
10.000 1.3944 0.03173 0.02287 -0.0877 0.1219 1.0000
10.250 1.3944 0.03367 0.02462 -0.0850 0.0946 1.0000
10.500 1.3939 0.03580 0.02666 -0.0824 0.0764 1.0000
10.750 1.3939 0.03801 0.02884 -0.0801 0.0649 1.0000
11.000 1.3929 0.04039 0.03123 -0.0780 0.0569 1.0000
11.250 1.3926 0.04280 0.03372 -0.0762 0.0506 1.0000
11.500 1.3908 0.04545 0.03644 -0.0745 0.0462 1.0000
11.750 1.3903 0.04807 0.03921 -0.0731 0.0426 1.0000
12.000 1.3872 0.05105 0.04228 -0.0719 0.0401 1.0000
12.250 1.3834 0.05423 0.04556 -0.0709 0.0381 1.0000
12.500 1.3825 0.05721 0.04872 -0.0702 0.0358 1.0000
12.750 1.3805 0.06040 0.05205 -0.0697 0.0339 1.0000
13.000 1.3771 0.06386 0.05564 -0.0694 0.0325 1.0000
13.250 1.3717 0.06767 0.05953 -0.0693 0.0314 1.0000
13.500 1.3708 0.07106 0.06308 -0.0692 0.0303 1.0000
13.750 1.3705 0.07447 0.06666 -0.0691 0.0293 1.0000
14.000 1.3702 0.07796 0.07031 -0.0692 0.0283 1.0000
14.250 1.3694 0.08156 0.07405 -0.0695 0.0273 1.0000
14.500 1.3682 0.08531 0.07791 -0.0700 0.0263 1.0000
14.750 1.3666 0.08914 0.08181 -0.0707 0.0255 1.0000
15.000 1.3662 0.09282 0.08554 -0.0712 0.0247 1.0000
15.250 1.3652 0.09687 0.08984 -0.0720 0.0240 1.0000
15.500 1.3638 0.10104 0.09423 -0.0730 0.0234 1.0000
15.750 1.3617 0.10540 0.09880 -0.0741 0.0230 1.0000
16.000 1.3581 0.11014 0.10377 -0.0757 0.0225 1.0000
16.250 1.3530 0.11520 0.10904 -0.0776 0.0222 1.0000
16.500 1.3465 0.12069 0.11474 -0.0801 0.0219 1.0000
16.750 1.3383 0.12664 0.12091 -0.0831 0.0216 1.0000
17.000 1.3286 0.13310 0.12757 -0.0866 0.0214 1.0000
17.250 1.3174 0.14017 0.13486 -0.0909 0.0213 1.0000
17.500 1.3037 0.14811 0.14301 -0.0959 0.0212 1.0000
17.750 1.2862 0.15751 0.15264 -0.1022 0.0212 1.0000
18.000 1.2602 0.17021 0.16557 -0.1111 0.0216 1.0000
18.250 1.2052 0.19508 0.19067 -0.1279 0.0227 1.0000
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Polar data table (+)
Polar graphs
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