GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 50,000 Max Cl/Cd: 36.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe314-il-50000-n5.txt Download as CSV file: xf-goe314-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3220 0.10978 0.10267 -0.0236 1.0000 0.0871
-8.500 -0.3303 0.10917 0.10218 -0.0254 1.0000 0.0880
-8.250 -0.3410 0.10855 0.10171 -0.0270 1.0000 0.0884
-8.000 -0.3131 0.10108 0.09420 -0.0239 1.0000 0.0916
-7.750 -0.3098 0.09839 0.09158 -0.0234 1.0000 0.0940
-7.500 -0.3111 0.09623 0.08952 -0.0231 1.0000 0.0962
-7.250 -0.3140 0.09429 0.08769 -0.0237 1.0000 0.0987
-7.000 -0.3189 0.09308 0.08658 -0.0265 1.0000 0.1008
-6.750 -0.3216 0.09216 0.08570 -0.0306 1.0000 0.1017
-6.500 -0.3143 0.08739 0.08104 -0.0271 1.0000 0.1031
-6.250 -0.3090 0.08420 0.07792 -0.0247 1.0000 0.1058
-6.000 -0.3068 0.08192 0.07571 -0.0242 1.0000 0.1098
-5.750 -0.3064 0.08101 0.07478 -0.0278 1.0000 0.1147
-5.500 -0.3044 0.07810 0.07193 -0.0272 1.0000 0.1165
-5.250 -0.3025 0.07512 0.06906 -0.0239 1.0000 0.1196
-5.000 -0.2992 0.07298 0.06694 -0.0231 1.0000 0.1238
-4.750 -0.2888 0.07208 0.06584 -0.0279 1.0000 0.1302
-4.500 -0.2750 0.06770 0.06160 -0.0268 0.9956 0.1332
-4.250 -0.2312 0.06456 0.05816 -0.0358 0.9838 0.1460
-4.000 -0.2040 0.06038 0.05404 -0.0375 0.9738 0.1524
-3.750 -0.1700 0.05710 0.05065 -0.0422 0.9619 0.1681
-3.500 -0.1364 0.05425 0.04763 -0.0468 0.9491 0.1950
-2.500 0.0483 0.04195 0.03352 -0.0655 0.9019 0.1013
-2.250 0.0826 0.03917 0.03067 -0.0676 0.8889 0.0986
-2.000 0.1199 0.03696 0.02819 -0.0696 0.8755 0.0966
-1.500 0.1974 0.03321 0.02355 -0.0726 0.8476 0.0871
-1.250 0.2322 0.03153 0.02162 -0.0736 0.8321 0.0857
-1.000 0.2659 0.03011 0.01991 -0.0741 0.8154 0.0848
-0.750 0.2984 0.02894 0.01844 -0.0742 0.7975 0.0855
-0.500 0.3304 0.02806 0.01718 -0.0741 0.7788 0.0878
-0.250 0.3612 0.02707 0.01594 -0.0739 0.7598 0.0892
0.000 0.3919 0.02614 0.01480 -0.0737 0.7406 0.0896
0.250 0.4203 0.02538 0.01385 -0.0731 0.7206 0.0906
0.500 0.4501 0.02475 0.01302 -0.0726 0.6999 0.0921
0.750 0.4799 0.02424 0.01232 -0.0722 0.6802 0.0959
1.000 0.5086 0.02390 0.01171 -0.0716 0.6615 0.1014
1.250 0.5362 0.02341 0.01114 -0.0710 0.6438 0.1055
1.500 0.5623 0.02313 0.01071 -0.0701 0.6264 0.1096
1.750 0.5881 0.02296 0.01039 -0.0693 0.6098 0.1163
2.000 0.6136 0.02280 0.01014 -0.0685 0.5940 0.1281
2.250 0.6395 0.02269 0.00997 -0.0678 0.5793 0.1403
2.500 0.6651 0.02259 0.00994 -0.0672 0.5648 0.1672
2.750 0.7054 0.02104 0.00988 -0.0694 0.5493 1.0000
3.000 0.7300 0.02144 0.01001 -0.0685 0.5354 1.0000
3.250 0.7543 0.02185 0.01020 -0.0676 0.5219 1.0000
3.500 0.7786 0.02227 0.01045 -0.0668 0.5089 1.0000
3.750 0.8029 0.02269 0.01072 -0.0659 0.4963 1.0000
4.000 0.8271 0.02312 0.01101 -0.0651 0.4840 1.0000
4.250 0.8499 0.02361 0.01145 -0.0641 0.4711 1.0000
4.500 0.8730 0.02411 0.01191 -0.0633 0.4591 1.0000
4.750 0.8968 0.02460 0.01232 -0.0624 0.4482 1.0000
5.000 0.9200 0.02512 0.01281 -0.0616 0.4372 1.0000
5.250 0.9423 0.02571 0.01345 -0.0606 0.4261 1.0000
5.500 0.9658 0.02626 0.01396 -0.0598 0.4165 1.0000
5.750 0.9881 0.02687 0.01462 -0.0589 0.4063 1.0000
6.000 1.0100 0.02753 0.01534 -0.0580 0.3965 1.0000
6.250 1.0336 0.02811 0.01593 -0.0573 0.3880 1.0000
6.500 1.0541 0.02892 0.01689 -0.0563 0.3787 1.0000
6.750 1.0781 0.02954 0.01750 -0.0556 0.3715 1.0000
7.000 1.0972 0.03047 0.01863 -0.0545 0.3625 1.0000
7.250 1.1209 0.03106 0.01924 -0.0538 0.3555 1.0000
7.500 1.1381 0.03202 0.02042 -0.0525 0.3460 1.0000
7.750 1.1606 0.03256 0.02096 -0.0516 0.3385 1.0000
8.000 1.1768 0.03353 0.02217 -0.0502 0.3294 1.0000
8.250 1.1981 0.03412 0.02283 -0.0492 0.3222 1.0000
8.500 1.2134 0.03520 0.02417 -0.0478 0.3143 1.0000
8.750 1.2360 0.03572 0.02472 -0.0469 0.3082 1.0000
9.000 1.2474 0.03701 0.02632 -0.0452 0.3002 1.0000
9.250 1.2682 0.03738 0.02676 -0.0441 0.2931 1.0000
9.500 1.2774 0.03872 0.02842 -0.0421 0.2852 1.0000
9.750 1.2955 0.03941 0.02924 -0.0409 0.2791 1.0000
10.000 1.3064 0.04076 0.03086 -0.0392 0.2734 1.0000
10.250 1.3167 0.04204 0.03240 -0.0374 0.2673 1.0000
10.500 1.3320 0.04268 0.03321 -0.0358 0.2607 1.0000
10.750 1.3324 0.04429 0.03512 -0.0333 0.2530 1.0000
11.000 1.3419 0.04497 0.03594 -0.0311 0.2452 1.0000
11.250 1.3355 0.04667 0.03788 -0.0280 0.2374 1.0000
11.500 1.3345 0.04795 0.03929 -0.0254 0.2291 1.0000
11.750 1.3278 0.04995 0.04148 -0.0232 0.2212 1.0000
12.000 1.3189 0.05246 0.04418 -0.0216 0.2137 1.0000
12.250 1.3133 0.05469 0.04654 -0.0204 0.2047 1.0000
12.500 1.2916 0.05947 0.05153 -0.0205 0.1978 1.0000
12.750 1.2837 0.06248 0.05461 -0.0205 0.1869 1.0000
13.000 1.2549 0.06953 0.06189 -0.0227 0.1809 1.0000
13.250 1.2410 0.07433 0.06676 -0.0241 0.1702 1.0000
13.500 1.2287 0.07904 0.07151 -0.0257 0.1579 1.0000
13.750 1.1940 0.08875 0.08138 -0.0299 0.1522 1.0000
14.000 1.1794 0.09453 0.08720 -0.0321 0.1409 1.0000
14.250 1.1677 0.09989 0.09255 -0.0343 0.1293 1.0000
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Polar data table (+)
Polar graphs
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