GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 50,000 Max Cl/Cd: 35.42 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe315-il-50000.txt Download as CSV file: xf-goe315-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3856 0.11354 0.10643 -0.0113 1.0000 0.1293
-9.000 -0.3865 0.11168 0.10463 -0.0130 1.0000 0.1336
-8.750 -0.3987 0.11160 0.10470 -0.0162 1.0000 0.1355
-8.500 -0.3756 0.10484 0.09792 -0.0142 1.0000 0.1408
-8.250 -0.3722 0.10218 0.09532 -0.0148 1.0000 0.1469
-8.000 -0.3854 0.10164 0.09494 -0.0175 1.0000 0.1503
-7.750 -0.3698 0.09652 0.08985 -0.0162 1.0000 0.1555
-7.500 -0.3685 0.09407 0.08749 -0.0165 1.0000 0.1629
-7.250 -0.3821 0.09387 0.08740 -0.0231 1.0000 0.1665
-7.000 -0.3627 0.08826 0.08184 -0.0179 1.0000 0.1779
-6.500 -0.3608 0.08333 0.07708 -0.0216 1.0000 0.1962
-6.250 -0.3507 0.07939 0.07321 -0.0190 1.0000 0.2058
-6.000 -0.3486 0.07663 0.07054 -0.0200 1.0000 0.2166
-5.750 -0.3462 0.07409 0.06808 -0.0207 1.0000 0.2303
-5.500 -0.3421 0.07133 0.06542 -0.0197 1.0000 0.2460
-5.250 -0.3379 0.06856 0.06276 -0.0173 1.0000 0.2639
-5.000 -0.3365 0.06628 0.06059 -0.0150 1.0000 0.2855
-4.750 0.0413 0.04221 0.03550 -0.0231 1.0000 1.0000
-4.500 0.0525 0.04041 0.03377 -0.0239 1.0000 1.0000
-4.250 0.0636 0.03866 0.03211 -0.0247 1.0000 1.0000
-4.000 0.0744 0.03701 0.03056 -0.0254 1.0000 1.0000
-3.750 0.0848 0.03543 0.02908 -0.0260 1.0000 1.0000
-3.500 0.0611 0.03602 0.02987 -0.0187 1.0000 0.9846
-3.250 0.0083 0.03774 0.03191 -0.0057 1.0000 0.9471
-3.000 -0.0417 0.03894 0.03345 0.0052 1.0000 0.9147
-2.750 -0.0959 0.04029 0.03511 0.0161 1.0000 0.8961
-2.500 -0.1520 0.04157 0.03662 0.0266 1.0000 0.8811
-2.250 -0.2202 0.04288 0.03817 0.0386 1.0000 0.8633
-2.000 -0.3843 0.04575 0.04142 0.0576 0.9950 0.7651
-1.750 -0.3474 0.04264 0.03824 0.0455 0.9785 0.7493
-1.500 -0.0603 0.03631 0.02874 -0.0437 0.9587 0.3206
-1.250 0.0025 0.03551 0.02695 -0.0498 0.9461 0.2414
-1.000 0.0508 0.03455 0.02545 -0.0532 0.9339 0.2086
-0.750 0.0966 0.03370 0.02417 -0.0562 0.9225 0.1931
-0.500 0.1481 0.03293 0.02295 -0.0599 0.9116 0.1792
-0.250 0.1855 0.03227 0.02205 -0.0615 0.8991 0.1709
0.000 0.2232 0.03203 0.02148 -0.0629 0.8868 0.1655
0.250 0.2668 0.03144 0.02075 -0.0653 0.8753 0.1643
0.500 0.3268 0.03057 0.01977 -0.0701 0.8649 0.1701
0.750 0.3631 0.03027 0.01943 -0.0713 0.8515 0.1743
1.000 0.3999 0.03005 0.01915 -0.0723 0.8375 0.1802
1.250 0.4370 0.02969 0.01882 -0.0733 0.8231 0.1939
1.500 0.4745 0.02910 0.01850 -0.0743 0.8081 0.2379
1.750 0.5348 0.02708 0.01789 -0.0779 0.7928 1.0000
2.000 0.5656 0.02742 0.01786 -0.0773 0.7769 1.0000
2.250 0.5941 0.02781 0.01806 -0.0765 0.7610 1.0000
2.500 0.6212 0.02822 0.01834 -0.0756 0.7448 1.0000
2.750 0.6472 0.02866 0.01868 -0.0744 0.7286 1.0000
3.000 0.6725 0.02911 0.01908 -0.0732 0.7122 1.0000
3.250 0.6975 0.02956 0.01947 -0.0718 0.6955 1.0000
3.500 0.7226 0.02995 0.01983 -0.0703 0.6786 1.0000
3.750 0.7475 0.03034 0.02019 -0.0688 0.6618 1.0000
4.000 0.7728 0.03067 0.02052 -0.0672 0.6451 1.0000
4.250 0.7916 0.03149 0.02136 -0.0656 0.6261 1.0000
4.500 0.8123 0.03223 0.02214 -0.0640 0.6082 1.0000
4.750 0.8344 0.03290 0.02284 -0.0626 0.5913 1.0000
5.000 0.8567 0.03361 0.02360 -0.0612 0.5753 1.0000
5.250 0.8783 0.03446 0.02450 -0.0599 0.5602 1.0000
5.500 0.8992 0.03552 0.02563 -0.0587 0.5466 1.0000
5.750 0.9243 0.03621 0.02637 -0.0576 0.5348 1.0000
6.000 0.9452 0.03733 0.02761 -0.0566 0.5226 1.0000
6.250 0.9555 0.03961 0.03005 -0.0556 0.5098 1.0000
6.500 0.9684 0.04162 0.03219 -0.0546 0.4983 1.0000
6.750 0.9921 0.04208 0.03275 -0.0531 0.4856 1.0000
7.000 1.0188 0.04184 0.03262 -0.0513 0.4708 1.0000
7.250 1.0435 0.04159 0.03247 -0.0494 0.4548 1.0000
7.500 1.0677 0.04119 0.03217 -0.0473 0.4379 1.0000
7.750 1.0928 0.04078 0.03192 -0.0455 0.4220 1.0000
8.000 1.1268 0.03862 0.02978 -0.0432 0.4013 1.0000
8.250 1.1536 0.03660 0.02779 -0.0405 0.3755 1.0000
8.500 1.1770 0.03468 0.02587 -0.0376 0.3460 1.0000
8.750 1.1929 0.03368 0.02488 -0.0344 0.3121 1.0000
9.000 1.1954 0.03375 0.02471 -0.0301 0.2616 1.0000
9.250 1.1882 0.03569 0.02628 -0.0257 0.2082 1.0000
9.500 1.1882 0.03780 0.02807 -0.0225 0.1767 1.0000
9.750 1.1934 0.03983 0.03000 -0.0201 0.1576 1.0000
10.000 1.2040 0.04181 0.03191 -0.0182 0.1448 1.0000
10.250 1.2233 0.04379 0.03373 -0.0170 0.1351 1.0000
10.500 1.2382 0.04629 0.03654 -0.0156 0.1278 1.0000
10.750 1.2591 0.04864 0.03881 -0.0149 0.1208 1.0000
11.000 1.2688 0.05164 0.04218 -0.0134 0.1165 1.0000
11.250 1.2822 0.05484 0.04562 -0.0124 0.1135 1.0000
11.500 1.3065 0.05840 0.04916 -0.0124 0.1098 1.0000
11.750 1.2963 0.06203 0.05323 -0.0100 0.1089 1.0000
12.000 1.2796 0.06579 0.05733 -0.0078 0.1084 1.0000
12.250 1.2606 0.07009 0.06192 -0.0066 0.1083 1.0000
12.500 1.2378 0.07503 0.06712 -0.0065 0.1084 1.0000
12.750 1.2131 0.08078 0.07309 -0.0077 0.1089 1.0000
13.000 1.1877 0.08734 0.07981 -0.0099 0.1095 1.0000
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Polar data table (+)
Polar graphs
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