GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 500,000 Max Cl/Cd: 79.63 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe280-il-500000-n5.txt Download as CSV file: xf-goe280-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3323 0.10445 0.10229 -0.0212 1.0000 0.0084
-8.500 -0.3270 0.10120 0.09907 -0.0226 1.0000 0.0084
-8.250 -0.3226 0.09804 0.09594 -0.0237 1.0000 0.0084
-8.000 -0.2083 0.07731 0.07535 -0.0355 0.9840 0.0079
-7.750 -0.2015 0.07329 0.07132 -0.0377 0.9778 0.0074
-7.250 -0.2904 0.08417 0.08214 -0.0323 0.9844 0.0075
-7.000 -0.2720 0.07951 0.07747 -0.0385 0.9769 0.0069
-6.750 -0.2531 0.07428 0.07222 -0.0453 0.9677 0.0064
-6.500 -0.2325 0.06880 0.06671 -0.0523 0.9581 0.0061
-6.250 -0.2108 0.06432 0.06217 -0.0578 0.9492 0.0062
-6.000 -0.1885 0.06010 0.05789 -0.0626 0.9396 0.0063
-5.750 -0.1651 0.05597 0.05367 -0.0671 0.9303 0.0065
-5.500 -0.1399 0.05194 0.04954 -0.0711 0.9224 0.0068
-5.250 -0.1121 0.04734 0.04480 -0.0753 0.9142 0.0077
-5.000 -0.0825 0.04214 0.03941 -0.0794 0.9067 0.0080
-4.750 -0.0508 0.03624 0.03322 -0.0829 0.8988 0.0083
-4.500 -0.0216 0.03251 0.02927 -0.0849 0.8907 0.0088
-4.250 0.0062 0.03034 0.02691 -0.0858 0.8819 0.0094
-4.000 0.0360 0.02751 0.02384 -0.0868 0.8719 0.0109
-3.750 0.0697 0.02207 0.01785 -0.0879 0.8624 0.0128
-3.500 0.0969 0.02145 0.01711 -0.0881 0.8495 0.0135
-3.250 0.1255 0.02014 0.01557 -0.0882 0.8339 0.0155
-3.000 0.1575 0.01651 0.01133 -0.0883 0.8171 0.0190
-2.750 0.1840 0.01651 0.01122 -0.0882 0.7935 0.0199
-2.500 0.2109 0.01630 0.01085 -0.0882 0.7696 0.0213
-2.250 0.2392 0.01544 0.00968 -0.0881 0.7464 0.0229
-1.750 0.2958 0.01432 0.00800 -0.0879 0.7028 0.0262
-1.500 0.3240 0.01397 0.00743 -0.0878 0.6813 0.0267
-1.250 0.3522 0.01367 0.00695 -0.0879 0.6601 0.0271
-1.000 0.3803 0.01273 0.00574 -0.0880 0.6316 0.0283
-0.750 0.4077 0.01240 0.00517 -0.0879 0.5891 0.0283
-0.500 0.4350 0.01219 0.00472 -0.0878 0.5516 0.0281
-0.250 0.4628 0.01187 0.00425 -0.0878 0.5286 0.0281
0.000 0.4907 0.01150 0.00376 -0.0879 0.5105 0.0284
0.250 0.5186 0.01118 0.00335 -0.0880 0.4928 0.0292
0.750 0.5745 0.01096 0.00297 -0.0883 0.4563 0.0318
1.000 0.6025 0.01093 0.00287 -0.0884 0.4380 0.0330
1.250 0.6304 0.01092 0.00279 -0.0886 0.4208 0.0339
1.500 0.6584 0.01093 0.00274 -0.0887 0.4052 0.0346
1.750 0.6863 0.01099 0.00273 -0.0888 0.3887 0.0358
2.000 0.7139 0.01107 0.00274 -0.0889 0.3713 0.0370
2.250 0.7416 0.01115 0.00274 -0.0890 0.3532 0.0370
2.500 0.7689 0.01131 0.00278 -0.0891 0.3298 0.0370
2.750 0.7957 0.01154 0.00287 -0.0891 0.3001 0.0370
3.000 0.8223 0.01183 0.00299 -0.0890 0.2692 0.0371
3.250 0.8487 0.01212 0.00313 -0.0890 0.2415 0.0374
3.500 0.8752 0.01241 0.00331 -0.0889 0.2176 0.0380
4.000 0.9266 0.01320 0.00380 -0.0887 0.1561 0.0752
4.500 0.9723 0.01221 0.00441 -0.0875 0.1243 1.0000
4.750 0.9980 0.01261 0.00470 -0.0873 0.1079 1.0000
5.000 1.0217 0.01329 0.00510 -0.0870 0.0652 1.0000
5.250 1.0439 0.01420 0.00579 -0.0863 0.0224 1.0000
5.500 1.0695 0.01454 0.00612 -0.0861 0.0145 1.0000
5.750 1.0951 0.01490 0.00656 -0.0858 0.0124 1.0000
6.000 1.1199 0.01536 0.00713 -0.0854 0.0101 1.0000
6.250 1.1451 0.01573 0.00757 -0.0851 0.0091 1.0000
6.500 1.1696 0.01617 0.00810 -0.0847 0.0082 1.0000
6.750 1.1934 0.01670 0.00871 -0.0841 0.0074 1.0000
7.000 1.2159 0.01738 0.00950 -0.0834 0.0067 1.0000
7.250 1.2394 0.01788 0.01009 -0.0829 0.0060 1.0000
7.500 1.2615 0.01855 0.01084 -0.0821 0.0055 1.0000
7.750 1.2826 0.01931 0.01168 -0.0812 0.0051 1.0000
8.000 1.3021 0.02019 0.01264 -0.0801 0.0048 1.0000
8.250 1.3171 0.02152 0.01408 -0.0783 0.0046 1.0000
8.500 1.3340 0.02252 0.01517 -0.0768 0.0045 1.0000
8.750 1.3505 0.02347 0.01622 -0.0752 0.0042 1.0000
9.000 1.3661 0.02442 0.01729 -0.0736 0.0037 1.0000
9.250 1.3787 0.02553 0.01848 -0.0716 0.0035 1.0000
9.500 1.3881 0.02675 0.01980 -0.0690 0.0034 1.0000
9.750 1.3939 0.02800 0.02114 -0.0660 0.0033 1.0000
10.000 1.3972 0.02937 0.02260 -0.0628 0.0032 1.0000
10.250 1.3993 0.03097 0.02429 -0.0597 0.0031 1.0000
10.500 1.3985 0.03293 0.02635 -0.0568 0.0030 1.0000
10.750 1.3952 0.03532 0.02883 -0.0540 0.0029 1.0000
11.000 1.3963 0.03749 0.03111 -0.0518 0.0029 1.0000
11.250 1.3971 0.03985 0.03356 -0.0498 0.0028 1.0000
11.500 1.3983 0.04233 0.03615 -0.0481 0.0028 1.0000
11.750 1.4001 0.04487 0.03878 -0.0465 0.0027 1.0000
12.000 1.4021 0.04749 0.04154 -0.0451 0.0027 1.0000
12.250 1.4042 0.05019 0.04435 -0.0438 0.0026 1.0000
12.500 1.4059 0.05300 0.04729 -0.0427 0.0026 1.0000
12.750 1.4066 0.05600 0.05042 -0.0418 0.0026 1.0000
13.000 1.4059 0.05923 0.05379 -0.0412 0.0026 1.0000
13.250 1.4031 0.06272 0.05743 -0.0408 0.0026 1.0000
13.500 1.3983 0.06654 0.06142 -0.0409 0.0025 1.0000
13.750 1.3917 0.07070 0.06575 -0.0414 0.0025 1.0000
14.000 1.3837 0.07514 0.07037 -0.0422 0.0024 1.0000
14.250 1.3746 0.07992 0.07532 -0.0435 0.0024 1.0000
14.500 1.3652 0.08498 0.08055 -0.0452 0.0023 1.0000
14.750 1.3553 0.09033 0.08606 -0.0473 0.0023 1.0000
15.000 1.3448 0.09592 0.09180 -0.0497 0.0022 1.0000
15.250 1.3342 0.10175 0.09778 -0.0525 0.0022 1.0000
15.500 1.3227 0.10796 0.10415 -0.0555 0.0022 1.0000
15.750 1.3116 0.11432 0.11065 -0.0588 0.0022 1.0000
16.000 1.2999 0.12096 0.11744 -0.0624 0.0021 1.0000
16.250 1.2883 0.12785 0.12448 -0.0663 0.0021 1.0000
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Polar data table (+)
Polar graphs
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