GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 200,000 Max Cl/Cd: 71.32 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe100-il-200000.txt Download as CSV file: xf-goe100-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 100 (SOPWITH) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3995 0.08759 0.08439 -0.0210 1.0000 0.0340
-7.000 -0.3976 0.08471 0.08155 -0.0217 1.0000 0.0348
-6.750 -0.3957 0.08181 0.07870 -0.0225 1.0000 0.0358
-6.500 -0.3937 0.07892 0.07584 -0.0233 1.0000 0.0368
-6.250 -0.3915 0.07606 0.07300 -0.0241 1.0000 0.0380
-6.000 -0.3884 0.07319 0.07014 -0.0250 1.0000 0.0394
-5.750 -0.3773 0.07044 0.06733 -0.0286 1.0000 0.0416
-5.500 -0.3605 0.06781 0.06455 -0.0321 1.0000 0.0425
-5.250 -0.3478 0.06466 0.06129 -0.0329 1.0000 0.0426
-5.000 -0.3405 0.05891 0.05548 -0.0339 1.0000 0.0432
-4.750 -0.3357 0.05487 0.05143 -0.0327 1.0000 0.0442
-4.500 -0.3251 0.05205 0.04860 -0.0319 1.0000 0.0452
-4.250 -0.3105 0.04925 0.04574 -0.0318 1.0000 0.0467
-4.000 -0.2919 0.04624 0.04261 -0.0323 1.0000 0.0487
-3.750 -0.2691 0.04287 0.03905 -0.0334 1.0000 0.0515
-3.500 -0.2232 0.03972 0.03518 -0.0368 0.9983 0.0561
-3.250 -0.1874 0.03057 0.02569 -0.0407 0.9966 0.0451
-3.000 -0.1441 0.02529 0.01976 -0.0435 0.9948 0.0379
-2.750 -0.1013 0.02014 0.01354 -0.0453 0.9945 0.0338
-2.500 -0.0630 0.01829 0.01129 -0.0469 0.9921 0.0357
-2.250 -0.0244 0.01722 0.00989 -0.0487 0.9889 0.0412
-2.000 0.0151 0.01605 0.00862 -0.0510 0.9861 0.0535
-1.750 0.0604 0.01493 0.00744 -0.0545 0.9831 0.0840
-1.500 0.1030 0.01453 0.00710 -0.0577 0.9745 0.1055
-1.250 0.1508 0.01402 0.00656 -0.0617 0.9687 0.1196
-1.000 0.1874 0.01359 0.00617 -0.0634 0.9612 0.1376
-0.750 0.2330 0.01288 0.00574 -0.0671 0.9569 0.2065
-0.500 0.2692 0.01224 0.00540 -0.0689 0.9482 0.2818
-0.250 0.3174 0.01015 0.00514 -0.0722 0.9450 1.0000
0.000 0.3566 0.00990 0.00474 -0.0741 0.9351 1.0000
0.250 0.3952 0.00965 0.00438 -0.0758 0.9259 1.0000
0.500 0.4324 0.00939 0.00402 -0.0772 0.9161 1.0000
0.750 0.4630 0.00923 0.00380 -0.0773 0.9031 1.0000
1.000 0.4924 0.00910 0.00359 -0.0770 0.8883 1.0000
1.250 0.5184 0.00903 0.00348 -0.0761 0.8704 1.0000
1.500 0.5448 0.00897 0.00336 -0.0752 0.8506 1.0000
1.750 0.5703 0.00894 0.00326 -0.0741 0.8273 1.0000
2.000 0.5955 0.00893 0.00318 -0.0730 0.7997 1.0000
2.250 0.6203 0.00895 0.00310 -0.0719 0.7639 1.0000
2.500 0.6444 0.00905 0.00305 -0.0706 0.7118 1.0000
2.750 0.6668 0.00935 0.00300 -0.0689 0.6352 1.0000
3.000 0.6871 0.00992 0.00311 -0.0672 0.5549 1.0000
3.250 0.7071 0.01060 0.00336 -0.0656 0.4795 1.0000
3.500 0.7266 0.01136 0.00363 -0.0642 0.3955 1.0000
3.750 0.7478 0.01202 0.00390 -0.0631 0.3329 1.0000
4.000 0.7708 0.01253 0.00423 -0.0624 0.2928 1.0000
4.250 0.7949 0.01295 0.00453 -0.0619 0.2631 1.0000
4.500 0.8189 0.01338 0.00482 -0.0613 0.2325 1.0000
4.750 0.8417 0.01398 0.00509 -0.0607 0.1833 1.0000
5.000 0.8655 0.01449 0.00540 -0.0601 0.1509 1.0000
5.250 0.8898 0.01496 0.00583 -0.0595 0.1276 1.0000
5.500 0.9086 0.01627 0.00660 -0.0583 0.0377 1.0000
5.750 0.9308 0.01714 0.00749 -0.0572 0.0259 1.0000
6.000 0.9546 0.01778 0.00830 -0.0563 0.0241 1.0000
6.250 0.9782 0.01846 0.00917 -0.0554 0.0234 1.0000
6.500 1.0015 0.01920 0.01011 -0.0544 0.0233 1.0000
6.750 1.0242 0.01999 0.01114 -0.0533 0.0235 1.0000
7.000 1.0461 0.02083 0.01216 -0.0520 0.0241 1.0000
7.250 1.0665 0.02178 0.01329 -0.0506 0.0251 1.0000
7.500 1.0844 0.02301 0.01464 -0.0487 0.0255 1.0000
7.750 1.1000 0.02455 0.01624 -0.0468 0.0245 1.0000
8.000 1.1184 0.02605 0.01783 -0.0449 0.0255 1.0000
8.250 1.1389 0.02794 0.01979 -0.0432 0.0278 1.0000
8.500 1.1642 0.03000 0.02181 -0.0423 0.0302 1.0000
8.750 1.1922 0.03102 0.02329 -0.0407 0.0357 1.0000
9.000 1.2222 0.03387 0.02623 -0.0402 0.0401 1.0000
9.250 1.2440 0.03603 0.02903 -0.0377 0.0456 1.0000
9.500 1.2604 0.04044 0.03382 -0.0360 0.0482 1.0000
9.750 1.2781 0.04487 0.03849 -0.0346 0.0499 1.0000
10.000 1.2888 0.04695 0.04098 -0.0318 0.0506 1.0000
10.250 1.2919 0.05002 0.04453 -0.0285 0.0516 1.0000
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Polar data table (+)
Polar graphs
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