GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 123 AIRFOIL (goe123-il) Reynolds number: 100,000 Max Cl/Cd: 66.69 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe123-il-100000-n5.txt Download as CSV file: xf-goe123-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 123 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3027 0.10501 0.10028 -0.0282 1.0000 0.0344
-7.750 -0.3167 0.10501 0.10041 -0.0258 1.0000 0.0345
-7.500 -0.3270 0.10473 0.10021 -0.0249 1.0000 0.0347
-7.250 -0.3194 0.10334 0.09884 -0.0302 0.9966 0.0349
-7.000 -0.3035 0.09765 0.09317 -0.0324 0.9927 0.0353
-6.750 -0.2923 0.09227 0.08780 -0.0305 0.9901 0.0363
-6.500 -0.2723 0.08820 0.08370 -0.0339 0.9860 0.0376
-6.250 -0.2512 0.08456 0.08004 -0.0383 0.9800 0.0392
-6.000 -0.2259 0.08088 0.07633 -0.0442 0.9747 0.0415
-5.750 -0.1669 0.07869 0.07389 -0.0637 0.9671 0.0457
-5.500 -0.1501 0.07378 0.06900 -0.0654 0.9615 0.0463
-5.250 -0.1352 0.06937 0.06462 -0.0650 0.9582 0.0477
-5.000 -0.1103 0.06598 0.06118 -0.0684 0.9535 0.0501
-4.500 -0.0277 0.05914 0.05402 -0.0847 0.9442 0.0583
-4.250 -0.0104 0.05599 0.05086 -0.0851 0.9377 0.0601
-4.000 0.0231 0.05294 0.04771 -0.0894 0.9337 0.0637
-3.750 0.0833 0.05195 0.04620 -0.0992 0.9273 0.0696
-3.500 0.0972 0.04721 0.04163 -0.0991 0.9221 0.0718
-3.250 0.1299 0.04447 0.03879 -0.1020 0.9182 0.0762
-3.000 0.1788 0.04424 0.03803 -0.1071 0.9101 0.0831
-2.750 0.2079 0.04025 0.03402 -0.1095 0.9058 0.0842
-2.500 0.2324 0.03768 0.03143 -0.1104 0.8993 0.0859
-2.250 0.2616 0.03568 0.02932 -0.1118 0.8934 0.0894
-2.000 0.3016 0.03408 0.02741 -0.1147 0.8895 0.0993
-1.500 0.3725 0.02850 0.02105 -0.1172 0.8771 0.0560
-1.250 0.4040 0.02684 0.01920 -0.1182 0.8719 0.0544
-1.000 0.4330 0.02542 0.01756 -0.1185 0.8644 0.0532
-0.750 0.4667 0.02388 0.01575 -0.1193 0.8596 0.0522
-0.500 0.4943 0.02281 0.01444 -0.1190 0.8503 0.0536
-0.250 0.5259 0.02160 0.01293 -0.1190 0.8426 0.0553
0.000 0.5538 0.02055 0.01167 -0.1185 0.8318 0.0551
0.250 0.5812 0.01962 0.01056 -0.1179 0.8211 0.0549
0.500 0.6105 0.01872 0.00949 -0.1176 0.8129 0.0551
0.750 0.6367 0.01810 0.00877 -0.1169 0.8023 0.0555
1.000 0.6635 0.01754 0.00814 -0.1163 0.7924 0.0563
1.250 0.6909 0.01698 0.00753 -0.1157 0.7836 0.0574
1.500 0.7163 0.01663 0.00721 -0.1149 0.7718 0.0596
1.750 0.7426 0.01640 0.00697 -0.1142 0.7601 0.0648
2.000 0.7694 0.01618 0.00673 -0.1137 0.7483 0.0727
2.250 0.7964 0.01597 0.00648 -0.1131 0.7358 0.0826
2.500 0.8234 0.01580 0.00642 -0.1125 0.7221 0.1129
2.750 0.8499 0.01567 0.00632 -0.1120 0.7071 0.1725
3.000 0.8720 0.01427 0.00632 -0.1106 0.6909 1.0000
3.250 0.8977 0.01438 0.00633 -0.1099 0.6725 1.0000
3.500 0.9232 0.01449 0.00634 -0.1091 0.6520 1.0000
3.750 0.9485 0.01463 0.00635 -0.1082 0.6285 1.0000
4.000 0.9734 0.01480 0.00641 -0.1073 0.6027 1.0000
4.250 0.9980 0.01504 0.00652 -0.1065 0.5759 1.0000
4.500 1.0224 0.01533 0.00669 -0.1056 0.5500 1.0000
5.000 1.0701 0.01609 0.00724 -0.1039 0.5005 1.0000
5.250 1.0934 0.01654 0.00759 -0.1030 0.4754 1.0000
5.500 1.1163 0.01701 0.00798 -0.1021 0.4509 1.0000
5.750 1.1391 0.01750 0.00842 -0.1012 0.4275 1.0000
6.000 1.1615 0.01801 0.00891 -0.1003 0.4060 1.0000
6.250 1.1840 0.01854 0.00941 -0.0994 0.3876 1.0000
6.500 1.2065 0.01907 0.00996 -0.0986 0.3702 1.0000
6.750 1.2283 0.01964 0.01054 -0.0977 0.3514 1.0000
7.000 1.2493 0.02024 0.01118 -0.0966 0.3317 1.0000
7.250 1.2695 0.02090 0.01181 -0.0955 0.3120 1.0000
7.500 1.2893 0.02153 0.01249 -0.0944 0.2886 1.0000
7.750 1.3074 0.02225 0.01319 -0.0930 0.2600 1.0000
8.000 1.3248 0.02304 0.01397 -0.0916 0.2268 1.0000
8.250 1.3394 0.02407 0.01484 -0.0900 0.1826 1.0000
8.500 1.3490 0.02568 0.01605 -0.0878 0.1149 1.0000
8.750 1.3540 0.02784 0.01780 -0.0851 0.0723 1.0000
9.000 1.3626 0.02959 0.01945 -0.0827 0.0489 1.0000
9.250 1.3703 0.03125 0.02112 -0.0802 0.0412 1.0000
9.500 1.3734 0.03303 0.02295 -0.0772 0.0374 1.0000
9.750 1.3770 0.03475 0.02488 -0.0743 0.0346 1.0000
10.000 1.3801 0.03654 0.02686 -0.0716 0.0319 1.0000
10.250 1.3807 0.03859 0.02905 -0.0691 0.0298 1.0000
10.500 1.3784 0.04096 0.03157 -0.0665 0.0285 1.0000
10.750 1.3734 0.04371 0.03443 -0.0640 0.0275 1.0000
11.000 1.3742 0.04610 0.03697 -0.0619 0.0267 1.0000
11.250 1.3774 0.04837 0.03943 -0.0602 0.0256 1.0000
11.500 1.3804 0.05074 0.04199 -0.0586 0.0243 1.0000
11.750 1.3828 0.05324 0.04465 -0.0572 0.0230 1.0000
12.000 1.3848 0.05587 0.04743 -0.0559 0.0220 1.0000
12.250 1.3872 0.05861 0.05034 -0.0545 0.0213 1.0000
12.500 1.3893 0.06147 0.05334 -0.0533 0.0207 1.0000
12.750 1.3910 0.06450 0.05652 -0.0522 0.0201 1.0000
13.000 1.3924 0.06777 0.05993 -0.0511 0.0197 1.0000
13.250 1.3928 0.07157 0.06389 -0.0499 0.0191 1.0000
13.500 1.3873 0.07557 0.06813 -0.0495 0.0188 1.0000
13.750 1.3788 0.07979 0.07264 -0.0497 0.0185 1.0000
14.000 1.3686 0.08441 0.07755 -0.0503 0.0183 1.0000
14.250 1.3569 0.08946 0.08287 -0.0515 0.0180 1.0000
14.500 1.3438 0.09494 0.08862 -0.0532 0.0178 1.0000
14.750 1.3297 0.10093 0.09485 -0.0556 0.0177 1.0000
15.000 1.3150 0.10743 0.10160 -0.0586 0.0176 1.0000
15.250 1.2995 0.11448 0.10888 -0.0624 0.0175 1.0000
15.500 1.2835 0.12205 0.11666 -0.0667 0.0176 1.0000
15.750 1.2670 0.13024 0.12506 -0.0717 0.0177 1.0000
16.000 1.2504 0.13903 0.13403 -0.0774 0.0178 1.0000
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Polar data table (+)
Polar graphs
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