GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 200,000 Max Cl/Cd: 77.92 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe402-il-200000-n5.txt Download as CSV file: xf-goe402-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2544 0.09572 0.09250 -0.0239 1.0000 0.0176
-7.500 -0.2536 0.09361 0.09045 -0.0235 1.0000 0.0180
-7.250 -0.2552 0.09171 0.08862 -0.0226 1.0000 0.0184
-7.000 -0.2473 0.08904 0.08600 -0.0245 0.9950 0.0189
-6.750 -0.2219 0.08527 0.08223 -0.0317 0.9813 0.0199
-6.250 -0.1598 0.07788 0.07478 -0.0498 0.9484 0.0206
-6.000 -0.1257 0.07359 0.07043 -0.0582 0.9283 0.0208
-5.750 -0.0902 0.06909 0.06584 -0.0658 0.9061 0.0208
-5.250 -0.0162 0.06011 0.05653 -0.0799 0.8523 0.0209
-5.000 0.0162 0.05651 0.05270 -0.0848 0.8252 0.0211
-4.750 0.0412 0.05300 0.04899 -0.0875 0.8030 0.0211
-4.500 0.0641 0.04953 0.04534 -0.0895 0.7850 0.0210
-4.250 0.0750 0.04563 0.04137 -0.0894 0.7695 0.0200
-4.000 0.0987 0.04246 0.03803 -0.0913 0.7556 0.0191
-3.750 0.1262 0.03933 0.03467 -0.0935 0.7424 0.0186
-3.500 0.1579 0.03607 0.03114 -0.0958 0.7302 0.0197
-3.250 0.1927 0.03274 0.02743 -0.0976 0.7189 0.0208
-2.750 0.2475 0.02652 0.02062 -0.0993 0.6984 0.0219
-2.500 0.2711 0.02593 0.01995 -0.0994 0.6886 0.0242
-2.250 0.2995 0.02399 0.01770 -0.0996 0.6789 0.0267
-2.000 0.3289 0.02165 0.01494 -0.0995 0.6696 0.0278
-1.750 0.3583 0.01992 0.01265 -0.0991 0.6606 0.0317
-1.500 0.3846 0.01849 0.01101 -0.0990 0.6507 0.0332
-1.250 0.4112 0.01757 0.00988 -0.0987 0.6409 0.0351
-1.000 0.4381 0.01687 0.00892 -0.0984 0.6306 0.0387
-0.750 0.4653 0.01601 0.00776 -0.0979 0.6197 0.0396
-0.500 0.4923 0.01536 0.00688 -0.0974 0.6083 0.0405
-0.250 0.5191 0.01519 0.00646 -0.0969 0.5968 0.0426
0.250 0.5720 0.01436 0.00532 -0.0960 0.5744 0.0430
0.500 0.5982 0.01390 0.00478 -0.0956 0.5623 0.0431
0.750 0.6240 0.01346 0.00428 -0.0951 0.5499 0.0437
1.000 0.6495 0.01311 0.00390 -0.0946 0.5371 0.0448
1.250 0.6750 0.01291 0.00366 -0.0941 0.5240 0.0462
1.500 0.7006 0.01281 0.00351 -0.0936 0.5110 0.0480
1.750 0.7262 0.01277 0.00341 -0.0931 0.4971 0.0500
2.000 0.7517 0.01281 0.00337 -0.0927 0.4816 0.0541
2.250 0.7771 0.01283 0.00331 -0.0922 0.4657 0.0573
2.500 0.8024 0.01290 0.00330 -0.0917 0.4486 0.0595
2.750 0.8276 0.01302 0.00332 -0.0911 0.4319 0.0631
3.000 0.8527 0.01313 0.00340 -0.0906 0.4164 0.0765
3.500 0.9080 0.01205 0.00376 -0.0910 0.3896 1.0000
3.750 0.9329 0.01232 0.00393 -0.0905 0.3791 1.0000
4.000 0.9577 0.01259 0.00413 -0.0900 0.3701 1.0000
4.250 0.9829 0.01284 0.00434 -0.0895 0.3629 1.0000
4.500 1.0077 0.01312 0.00460 -0.0890 0.3561 1.0000
4.750 1.0327 0.01340 0.00485 -0.0886 0.3501 1.0000
5.000 1.0576 0.01367 0.00512 -0.0881 0.3440 1.0000
5.500 1.1072 0.01425 0.00575 -0.0872 0.3337 1.0000
5.750 1.1317 0.01455 0.00607 -0.0867 0.3283 1.0000
6.000 1.1559 0.01490 0.00642 -0.0861 0.3243 1.0000
6.250 1.1810 0.01517 0.00681 -0.0857 0.3198 1.0000
6.500 1.2054 0.01547 0.00719 -0.0853 0.3150 1.0000
6.750 1.2293 0.01583 0.00759 -0.0847 0.3107 1.0000
7.000 1.2537 0.01614 0.00801 -0.0842 0.3057 1.0000
7.250 1.2776 0.01646 0.00846 -0.0836 0.2998 1.0000
7.500 1.3005 0.01679 0.00887 -0.0829 0.2909 1.0000
7.750 1.3222 0.01709 0.00924 -0.0821 0.2739 1.0000
8.000 1.3426 0.01747 0.00960 -0.0811 0.2477 1.0000
8.250 1.3612 0.01804 0.01007 -0.0799 0.2083 1.0000
8.500 1.3698 0.01955 0.01113 -0.0776 0.1388 1.0000
8.750 1.3801 0.02098 0.01238 -0.0754 0.1073 1.0000
9.000 1.3827 0.02294 0.01395 -0.0724 0.0457 1.0000
9.250 1.3853 0.02469 0.01558 -0.0692 0.0216 1.0000
9.500 1.3911 0.02597 0.01691 -0.0662 0.0170 1.0000
9.750 1.3955 0.02728 0.01837 -0.0631 0.0143 1.0000
10.000 1.4013 0.02852 0.01980 -0.0605 0.0133 1.0000
10.250 1.4046 0.02998 0.02144 -0.0579 0.0125 1.0000
10.500 1.4059 0.03170 0.02334 -0.0555 0.0118 1.0000
10.750 1.4053 0.03370 0.02555 -0.0535 0.0113 1.0000
11.000 1.4027 0.03608 0.02809 -0.0519 0.0106 1.0000
11.250 1.3968 0.03903 0.03120 -0.0507 0.0101 1.0000
11.500 1.3866 0.04270 0.03504 -0.0501 0.0096 1.0000
11.750 1.3771 0.04658 0.03907 -0.0499 0.0093 1.0000
12.000 1.3743 0.04983 0.04248 -0.0498 0.0090 1.0000
12.250 1.3688 0.05355 0.04634 -0.0500 0.0089 1.0000
12.500 1.3628 0.05744 0.05038 -0.0504 0.0087 1.0000
12.750 1.3568 0.06144 0.05451 -0.0509 0.0085 1.0000
13.000 1.3508 0.06551 0.05871 -0.0515 0.0083 1.0000
13.250 1.3456 0.06955 0.06288 -0.0521 0.0082 1.0000
13.500 1.3412 0.07353 0.06698 -0.0527 0.0080 1.0000
13.750 1.3378 0.07746 0.07103 -0.0533 0.0078 1.0000
14.000 1.3354 0.08129 0.07498 -0.0539 0.0077 1.0000
14.250 1.3336 0.08512 0.07892 -0.0545 0.0075 1.0000
14.500 1.3322 0.08896 0.08287 -0.0553 0.0073 1.0000
14.750 1.3301 0.09302 0.08704 -0.0565 0.0070 1.0000
15.000 1.3284 0.09705 0.09117 -0.0576 0.0068 1.0000
15.250 1.3260 0.10112 0.09529 -0.0587 0.0065 1.0000
15.500 1.3242 0.10509 0.09936 -0.0594 0.0063 1.0000
15.750 1.3209 0.10986 0.10438 -0.0614 0.0062 1.0000
16.000 1.3172 0.11474 0.10946 -0.0633 0.0060 1.0000
16.250 1.3130 0.11974 0.11465 -0.0654 0.0059 1.0000
16.500 1.3075 0.12514 0.12023 -0.0678 0.0059 1.0000
16.750 1.3015 0.13075 0.12604 -0.0705 0.0058 1.0000
17.000 1.2943 0.13677 0.13224 -0.0737 0.0058 1.0000
17.250 1.2864 0.14314 0.13880 -0.0772 0.0057 1.0000
17.500 1.2781 0.14973 0.14557 -0.0811 0.0057 1.0000
17.750 1.2693 0.15661 0.15261 -0.0852 0.0057 1.0000
18.000 1.2598 0.16394 0.16012 -0.0898 0.0057 1.0000
18.250 1.2504 0.17149 0.16782 -0.0946 0.0058 1.0000
18.500 1.2409 0.17937 0.17585 -0.0997 0.0058 1.0000
18.750 1.2311 0.18770 0.18431 -0.1051 0.0058 1.0000
19.000 1.2214 0.19653 0.19326 -0.1108 0.0059 1.0000
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