GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.36 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe361-il-1000000.txt Download as CSV file: xf-goe361-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2860 0.09340 0.09188 -0.0226 1.0000 0.0127
-7.750 -0.2890 0.09130 0.08981 -0.0223 1.0000 0.0128
-7.500 -0.2887 0.08889 0.08744 -0.0228 0.9993 0.0129
-7.250 -0.2642 0.08419 0.08273 -0.0304 0.9949 0.0129
-7.000 -0.2408 0.07969 0.07822 -0.0373 0.9893 0.0129
-6.750 -0.2238 0.07550 0.07403 -0.0397 0.9851 0.0133
-6.500 -0.2021 0.07252 0.07104 -0.0437 0.9772 0.0136
-6.250 -0.1734 0.06899 0.06750 -0.0500 0.9704 0.0145
-5.250 -0.0122 0.04793 0.04606 -0.0907 0.9077 0.0171
-5.000 0.0090 0.04609 0.04412 -0.0922 0.8863 0.0176
-4.750 0.0322 0.04372 0.04163 -0.0944 0.8661 0.0183
-4.500 0.0672 0.04029 0.03801 -0.0993 0.8446 0.0207
-4.250 0.0972 0.03684 0.03433 -0.1023 0.8188 0.0209
-4.000 0.1252 0.03337 0.03060 -0.1044 0.7879 0.0210
-3.750 0.1497 0.02773 0.02463 -0.1073 0.7580 0.0216
-3.500 0.1725 0.02649 0.02319 -0.1075 0.7264 0.0220
-3.250 0.1971 0.02518 0.02170 -0.1078 0.7031 0.0226
-3.000 0.2235 0.02359 0.01992 -0.1083 0.6839 0.0234
-2.750 0.2546 0.02224 0.01831 -0.1082 0.6686 0.0266
-2.500 0.2832 0.02032 0.01609 -0.1084 0.6548 0.0269
-2.250 0.3104 0.01860 0.01408 -0.1085 0.6418 0.0269
-2.000 0.3359 0.01474 0.00980 -0.1090 0.6304 0.0281
-1.750 0.3621 0.01400 0.00896 -0.1089 0.6175 0.0287
-1.500 0.3886 0.01340 0.00823 -0.1087 0.6046 0.0295
-1.250 0.4154 0.01283 0.00752 -0.1085 0.5918 0.0309
-1.000 0.4426 0.01240 0.00693 -0.1082 0.5786 0.0331
-0.750 0.4702 0.01290 0.00731 -0.1077 0.5641 0.0347
-0.500 0.4962 0.01082 0.00496 -0.1076 0.5501 0.0377
-0.250 0.5227 0.01054 0.00459 -0.1073 0.5330 0.0398
0.000 0.5494 0.01036 0.00428 -0.1069 0.5146 0.0423
0.250 0.5757 0.00998 0.00376 -0.1067 0.4956 0.0487
0.500 0.6022 0.00983 0.00354 -0.1063 0.4771 0.0519
0.750 0.6288 0.00970 0.00332 -0.1059 0.4603 0.0545
1.000 0.6557 0.00888 0.00229 -0.1050 0.4461 0.0324
1.250 0.6822 0.00872 0.00205 -0.1046 0.4321 0.0319
1.500 0.7087 0.00863 0.00190 -0.1042 0.4191 0.0323
1.750 0.7353 0.00860 0.00181 -0.1039 0.4068 0.0333
2.000 0.7619 0.00862 0.00177 -0.1036 0.3948 0.0339
2.250 0.7884 0.00866 0.00176 -0.1032 0.3825 0.0344
2.500 0.8150 0.00871 0.00177 -0.1029 0.3702 0.0347
2.750 0.8416 0.00875 0.00177 -0.1026 0.3577 0.0356
3.000 0.8681 0.00884 0.00179 -0.1023 0.3449 0.0374
3.250 0.8944 0.00895 0.00185 -0.1019 0.3316 0.0394
3.500 0.9207 0.00907 0.00194 -0.1016 0.3182 0.0541
3.750 0.9511 0.00771 0.00235 -0.1029 0.3050 1.0000
4.000 0.9770 0.00792 0.00248 -0.1025 0.2923 1.0000
4.250 1.0026 0.00817 0.00262 -0.1021 0.2757 1.0000
4.500 1.0283 0.00839 0.00278 -0.1017 0.2647 1.0000
4.750 1.0541 0.00859 0.00295 -0.1013 0.2559 1.0000
5.000 1.0798 0.00880 0.00311 -0.1009 0.2455 1.0000
5.250 1.1054 0.00903 0.00329 -0.1005 0.2363 1.0000
5.500 1.1307 0.00927 0.00348 -0.1001 0.2262 1.0000
5.750 1.1560 0.00952 0.00368 -0.0997 0.2134 1.0000
6.000 1.1803 0.00986 0.00393 -0.0991 0.1908 1.0000
6.250 1.1875 0.01228 0.00541 -0.0962 0.0292 1.0000
6.500 1.2107 0.01277 0.00590 -0.0954 0.0213 1.0000
6.750 1.2345 0.01316 0.00634 -0.0947 0.0187 1.0000
7.000 1.2582 0.01355 0.00676 -0.0940 0.0170 1.0000
7.250 1.2809 0.01405 0.00729 -0.0932 0.0153 1.0000
7.500 1.3017 0.01477 0.00811 -0.0920 0.0139 1.0000
7.750 1.3245 0.01520 0.00857 -0.0912 0.0133 1.0000
8.000 1.3466 0.01569 0.00912 -0.0903 0.0125 1.0000
8.250 1.3686 0.01616 0.00962 -0.0895 0.0117 1.0000
8.500 1.3892 0.01675 0.01025 -0.0884 0.0109 1.0000
8.750 1.4032 0.01796 0.01158 -0.0864 0.0101 1.0000
9.000 1.4186 0.01893 0.01264 -0.0845 0.0098 1.0000
9.250 1.4374 0.01954 0.01332 -0.0832 0.0094 1.0000
9.500 1.4534 0.02034 0.01419 -0.0815 0.0091 1.0000
9.750 1.4672 0.02122 0.01515 -0.0795 0.0088 1.0000
10.000 1.4809 0.02205 0.01604 -0.0775 0.0085 1.0000
10.250 1.4907 0.02294 0.01700 -0.0749 0.0082 1.0000
10.500 1.4984 0.02378 0.01790 -0.0720 0.0079 1.0000
10.750 1.5076 0.02456 0.01872 -0.0694 0.0076 1.0000
11.000 1.5104 0.02575 0.01998 -0.0663 0.0073 1.0000
11.250 1.5039 0.02768 0.02201 -0.0625 0.0071 1.0000
11.500 1.4863 0.03082 0.02529 -0.0585 0.0069 1.0000
11.750 1.4852 0.03297 0.02754 -0.0564 0.0068 1.0000
12.000 1.4897 0.03472 0.02938 -0.0551 0.0067 1.0000
12.250 1.4938 0.03663 0.03139 -0.0540 0.0066 1.0000
12.500 1.4936 0.03914 0.03400 -0.0529 0.0065 1.0000
12.750 1.4947 0.04165 0.03661 -0.0522 0.0064 1.0000
13.000 1.4943 0.04445 0.03953 -0.0517 0.0063 1.0000
13.250 1.4934 0.04743 0.04262 -0.0512 0.0062 1.0000
13.500 1.4924 0.05051 0.04581 -0.0510 0.0061 1.0000
13.750 1.4906 0.05378 0.04919 -0.0509 0.0060 1.0000
14.000 1.4885 0.05716 0.05269 -0.0509 0.0059 1.0000
14.250 1.4868 0.06058 0.05621 -0.0514 0.0058 1.0000
14.500 1.4834 0.06433 0.06008 -0.0517 0.0057 1.0000
14.750 1.4799 0.06821 0.06408 -0.0525 0.0056 1.0000
15.000 1.4750 0.07242 0.06843 -0.0533 0.0055 1.0000
15.250 1.4696 0.07686 0.07300 -0.0544 0.0055 1.0000
15.500 1.4664 0.08108 0.07730 -0.0562 0.0054 1.0000
15.750 1.4591 0.08609 0.08244 -0.0579 0.0053 1.0000
16.000 1.4515 0.09131 0.08780 -0.0599 0.0053 1.0000
16.250 1.4467 0.09622 0.09281 -0.0624 0.0052 1.0000
16.500 1.4385 0.10186 0.09857 -0.0649 0.0051 1.0000
16.750 1.4285 0.10796 0.10481 -0.0677 0.0051 1.0000
17.000 1.4203 0.11383 0.11080 -0.0707 0.0051 1.0000
17.250 1.4106 0.12017 0.11727 -0.0740 0.0050 1.0000
17.500 1.3996 0.12694 0.12417 -0.0777 0.0050 1.0000
17.750 1.3881 0.13393 0.13130 -0.0817 0.0050 1.0000
18.000 1.3778 0.14083 0.13832 -0.0858 0.0049 1.0000
18.250 1.3659 0.14829 0.14590 -0.0903 0.0049 1.0000
18.500 1.3550 0.15567 0.15341 -0.0950 0.0049 1.0000
18.750 1.3373 0.16509 0.16300 -0.1009 0.0049 1.0000
19.000 1.3129 0.17684 0.17495 -0.1085 0.0050 1.0000
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Polar data table (+)
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