GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 50,000 Max Cl/Cd: 38.01 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe100-il-50000-n5.txt Download as CSV file: xf-goe100-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3893 0.10338 0.09693 -0.0214 1.0000 0.0796
-7.500 -0.3956 0.10180 0.09549 -0.0238 1.0000 0.0811
-7.250 -0.3969 0.09971 0.09348 -0.0274 1.0000 0.0817
-7.000 -0.3948 0.09717 0.09100 -0.0305 1.0000 0.0819
-6.750 -0.3879 0.09215 0.08607 -0.0278 1.0000 0.0829
-6.500 -0.3821 0.08837 0.08234 -0.0266 1.0000 0.0841
-6.250 -0.3770 0.08508 0.07909 -0.0267 1.0000 0.0852
-6.000 -0.3714 0.08186 0.07591 -0.0275 1.0000 0.0858
-5.750 -0.3588 0.07660 0.07055 -0.0304 1.0000 0.0521
-5.500 -0.3431 0.07179 0.06562 -0.0353 1.0000 0.0423
-5.250 -0.3364 0.06835 0.06221 -0.0342 1.0000 0.0408
-5.000 -0.3253 0.06471 0.05852 -0.0348 1.0000 0.0394
-4.750 -0.3107 0.06089 0.05462 -0.0362 1.0000 0.0384
-4.500 -0.2935 0.05704 0.05062 -0.0377 1.0000 0.0383
-4.250 -0.2738 0.05318 0.04657 -0.0392 1.0000 0.0388
-4.000 -0.2518 0.04926 0.04241 -0.0408 1.0000 0.0394
-3.750 -0.2280 0.04532 0.03812 -0.0421 1.0000 0.0397
-3.500 -0.2023 0.04138 0.03380 -0.0433 1.0000 0.0397
-3.250 -0.1745 0.03751 0.02942 -0.0444 1.0000 0.0399
-3.000 -0.1450 0.03388 0.02518 -0.0452 1.0000 0.0407
-2.750 -0.1151 0.03082 0.02146 -0.0457 1.0000 0.0441
-2.500 -0.0885 0.02903 0.01933 -0.0458 1.0000 0.0508
-2.250 -0.0568 0.02653 0.01610 -0.0459 1.0000 0.0563
-2.000 -0.0298 0.02525 0.01463 -0.0459 1.0000 0.0729
-1.750 -0.0023 0.02433 0.01353 -0.0456 1.0000 0.1016
-1.500 0.0240 0.02392 0.01289 -0.0454 1.0000 0.1327
-1.250 0.0512 0.02338 0.01200 -0.0451 1.0000 0.1525
-1.000 0.0773 0.02286 0.01136 -0.0448 1.0000 0.1715
-0.750 0.1033 0.02239 0.01080 -0.0447 1.0000 0.1979
-0.500 0.1293 0.02193 0.01048 -0.0449 1.0000 0.2462
0.000 0.1910 0.01979 0.01001 -0.0467 0.9895 1.0000
0.250 0.2361 0.02014 0.00992 -0.0505 0.9786 1.0000
0.500 0.2801 0.02036 0.00982 -0.0540 0.9640 1.0000
0.750 0.3241 0.02050 0.00974 -0.0573 0.9480 1.0000
1.000 0.3682 0.02057 0.00965 -0.0605 0.9320 1.0000
1.250 0.4118 0.02056 0.00953 -0.0634 0.9163 1.0000
1.500 0.4564 0.02046 0.00937 -0.0664 0.9004 1.0000
1.750 0.4930 0.02033 0.00925 -0.0675 0.8806 1.0000
2.000 0.5316 0.02009 0.00902 -0.0688 0.8603 1.0000
2.250 0.5639 0.01989 0.00885 -0.0688 0.8357 1.0000
2.500 0.5948 0.01967 0.00871 -0.0684 0.8079 1.0000
2.750 0.6243 0.01947 0.00856 -0.0677 0.7759 1.0000
3.000 0.6512 0.01934 0.00848 -0.0666 0.7363 1.0000
3.250 0.6801 0.01920 0.00837 -0.0657 0.6891 1.0000
3.500 0.7098 0.01916 0.00818 -0.0647 0.6311 1.0000
3.750 0.7365 0.01942 0.00816 -0.0635 0.5691 1.0000
4.000 0.7595 0.01998 0.00845 -0.0620 0.5144 1.0000
4.250 0.7815 0.02068 0.00901 -0.0606 0.4664 1.0000
4.500 0.8033 0.02141 0.00964 -0.0595 0.4265 1.0000
4.750 0.8242 0.02219 0.01028 -0.0582 0.3880 1.0000
5.000 0.8413 0.02304 0.01084 -0.0566 0.3348 1.0000
5.250 0.8596 0.02388 0.01144 -0.0552 0.2886 1.0000
5.500 0.8794 0.02467 0.01214 -0.0542 0.2469 1.0000
5.750 0.9014 0.02537 0.01289 -0.0533 0.2205 1.0000
6.000 0.9223 0.02617 0.01360 -0.0524 0.1838 1.0000
6.250 0.9446 0.02692 0.01436 -0.0515 0.1531 1.0000
6.500 0.9636 0.02836 0.01526 -0.0506 0.0467 1.0000
6.750 0.9821 0.03039 0.01712 -0.0494 0.0306 1.0000
7.000 1.0021 0.03197 0.01908 -0.0482 0.0277 1.0000
7.250 1.0205 0.03366 0.02108 -0.0468 0.0265 1.0000
7.500 1.0370 0.03538 0.02310 -0.0452 0.0258 1.0000
7.750 1.0516 0.03711 0.02516 -0.0435 0.0253 1.0000
8.000 1.0633 0.03899 0.02734 -0.0415 0.0245 1.0000
8.250 1.0722 0.04099 0.02964 -0.0394 0.0237 1.0000
8.500 1.0784 0.04311 0.03202 -0.0370 0.0229 1.0000
8.750 1.0827 0.04530 0.03445 -0.0346 0.0223 1.0000
9.000 1.0848 0.04748 0.03684 -0.0319 0.0220 1.0000
9.250 1.0870 0.04971 0.03927 -0.0294 0.0220 1.0000
9.500 1.0903 0.05203 0.04181 -0.0272 0.0220 1.0000
9.750 1.0947 0.05447 0.04446 -0.0252 0.0221 1.0000
10.000 1.1002 0.05702 0.04725 -0.0234 0.0222 1.0000
10.250 1.1058 0.05974 0.05022 -0.0218 0.0223 1.0000
10.500 1.1102 0.06270 0.05360 -0.0204 0.0225 1.0000
10.750 1.1120 0.06595 0.05715 -0.0193 0.0227 1.0000
11.000 1.1105 0.06954 0.06102 -0.0186 0.0229 1.0000
11.250 1.1059 0.07352 0.06528 -0.0184 0.0231 1.0000
11.500 1.0985 0.07791 0.06994 -0.0189 0.0233 1.0000
11.750 1.0889 0.08280 0.07508 -0.0202 0.0235 1.0000
12.000 1.0776 0.08822 0.08072 -0.0224 0.0237 1.0000
12.250 1.0651 0.09421 0.08693 -0.0254 0.0238 1.0000
12.500 1.0522 0.10072 0.09363 -0.0291 0.0239 1.0000
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Polar data table (+)
Polar graphs
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