GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 100,000 Max Cl/Cd: 53.55 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe623-il-100000.txt Download as CSV file: xf-goe623-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2555 0.10284 0.09820 -0.0373 1.0000 0.1237
-9.500 -0.2846 0.10126 0.09674 -0.0401 1.0000 0.1264
-9.250 -0.3173 0.09978 0.09541 -0.0419 1.0000 0.1270
-9.000 -0.2681 0.09354 0.08909 -0.0370 1.0000 0.1304
-8.750 -0.2656 0.09116 0.08676 -0.0352 1.0000 0.1344
-8.500 -0.3510 0.09428 0.08953 -0.0360 1.0000 0.1309
-8.250 -0.3482 0.09174 0.08705 -0.0351 1.0000 0.1345
-8.000 -0.3626 0.08983 0.08526 -0.0345 1.0000 0.1384
-7.750 -0.3964 0.08908 0.08469 -0.0320 1.0000 0.1400
-7.500 -0.4433 0.08820 0.08395 -0.0330 1.0000 0.1414
-7.250 -0.4674 0.08503 0.08081 -0.0336 1.0000 0.1425
-7.000 -0.4508 0.08218 0.07805 -0.0274 1.0000 0.1444
-6.750 -0.4477 0.08047 0.07639 -0.0235 1.0000 0.1478
-6.500 -0.4569 0.07829 0.07425 -0.0226 1.0000 0.1521
-6.250 -0.4828 0.07398 0.06978 -0.0294 1.0000 0.1584
-6.000 -0.4663 0.07134 0.06727 -0.0259 0.9983 0.1612
-5.750 -0.4340 0.06523 0.06085 -0.0374 0.9894 0.1748
-5.500 -0.3997 0.04418 0.03840 -0.0520 0.9838 0.0961
-5.250 -0.3658 0.03892 0.03255 -0.0558 0.9764 0.0937
-5.000 -0.3249 0.03364 0.02641 -0.0599 0.9714 0.0907
-4.750 -0.2882 0.03071 0.02291 -0.0622 0.9634 0.0911
-4.500 -0.2435 0.02881 0.02058 -0.0658 0.9577 0.0953
-4.250 -0.2065 0.02706 0.01836 -0.0675 0.9488 0.0979
-4.000 -0.1609 0.02539 0.01651 -0.0709 0.9433 0.1020
-3.750 -0.1248 0.02463 0.01567 -0.0726 0.9335 0.1098
-3.500 -0.0784 0.02357 0.01459 -0.0760 0.9281 0.1205
-3.250 -0.0437 0.02277 0.01380 -0.0773 0.9182 0.1368
-3.000 0.0021 0.02148 0.01271 -0.0806 0.9130 0.1914
-2.750 0.0356 0.02083 0.01228 -0.0819 0.9032 0.2411
-2.500 0.0775 0.02029 0.01189 -0.0846 0.8970 0.2894
-2.250 0.1071 0.01996 0.01174 -0.0850 0.8865 0.3366
-2.000 0.1454 0.01912 0.01130 -0.0867 0.8805 0.4083
-1.750 0.1659 0.01803 0.01131 -0.0848 0.8698 0.6223
-1.500 0.2619 0.01710 0.01090 -0.0951 0.8698 1.0000
-1.250 0.2958 0.01700 0.01053 -0.0960 0.8619 1.0000
-1.000 0.3191 0.01712 0.01047 -0.0951 0.8502 1.0000
-0.750 0.3419 0.01730 0.01049 -0.0942 0.8391 1.0000
-0.500 0.3732 0.01722 0.01023 -0.0944 0.8318 1.0000
-0.250 0.3933 0.01750 0.01038 -0.0930 0.8199 1.0000
0.000 0.4184 0.01763 0.01038 -0.0923 0.8106 1.0000
0.250 0.4452 0.01765 0.01028 -0.0917 0.8016 1.0000
0.500 0.4675 0.01786 0.01039 -0.0905 0.7906 1.0000
0.750 0.4982 0.01768 0.01007 -0.0902 0.7835 1.0000
1.000 0.5195 0.01792 0.01025 -0.0890 0.7714 1.0000
1.250 0.5438 0.01805 0.01030 -0.0880 0.7612 1.0000
1.500 0.5729 0.01790 0.01004 -0.0875 0.7529 1.0000
1.750 0.5957 0.01807 0.01017 -0.0864 0.7410 1.0000
2.000 0.6212 0.01808 0.01012 -0.0855 0.7303 1.0000
2.250 0.6506 0.01786 0.00979 -0.0849 0.7212 1.0000
2.500 0.6741 0.01799 0.00989 -0.0839 0.7088 1.0000
2.750 0.6991 0.01805 0.00992 -0.0830 0.6973 1.0000
3.000 0.7266 0.01800 0.00980 -0.0823 0.6870 1.0000
3.250 0.7535 0.01800 0.00975 -0.0816 0.6759 1.0000
3.500 0.7780 0.01814 0.00988 -0.0808 0.6635 1.0000
3.750 0.8036 0.01824 0.00995 -0.0800 0.6513 1.0000
4.000 0.8302 0.01831 0.00998 -0.0793 0.6392 1.0000
4.250 0.8577 0.01834 0.00993 -0.0787 0.6269 1.0000
4.500 0.8828 0.01848 0.01006 -0.0779 0.6127 1.0000
4.750 0.9075 0.01864 0.01022 -0.0770 0.5978 1.0000
5.000 0.9323 0.01879 0.01036 -0.0761 0.5820 1.0000
5.250 0.9572 0.01893 0.01045 -0.0751 0.5652 1.0000
5.500 0.9808 0.01909 0.01060 -0.0740 0.5467 1.0000
5.750 1.0029 0.01929 0.01084 -0.0728 0.5261 1.0000
6.000 1.0260 0.01947 0.01098 -0.0716 0.5051 1.0000
6.250 1.0484 0.01971 0.01115 -0.0704 0.4830 1.0000
6.500 1.0695 0.02001 0.01143 -0.0690 0.4590 1.0000
6.750 1.0908 0.02037 0.01171 -0.0677 0.4363 1.0000
7.000 1.1115 0.02084 0.01212 -0.0664 0.4143 1.0000
7.250 1.1335 0.02140 0.01256 -0.0653 0.3959 1.0000
7.500 1.1560 0.02206 0.01314 -0.0645 0.3800 1.0000
7.750 1.1786 0.02281 0.01386 -0.0637 0.3659 1.0000
8.000 1.2012 0.02361 0.01467 -0.0630 0.3535 1.0000
8.250 1.2246 0.02445 0.01553 -0.0624 0.3429 1.0000
8.500 1.2507 0.02530 0.01630 -0.0623 0.3338 1.0000
8.750 1.2718 0.02623 0.01742 -0.0614 0.3252 1.0000
9.000 1.2977 0.02712 0.01825 -0.0613 0.3169 1.0000
9.250 1.3166 0.02792 0.01924 -0.0601 0.3073 1.0000
9.500 1.3360 0.02870 0.02010 -0.0591 0.2971 1.0000
9.750 1.3549 0.02930 0.02067 -0.0579 0.2851 1.0000
10.000 1.3720 0.02980 0.02112 -0.0565 0.2722 1.0000
10.250 1.3818 0.03034 0.02190 -0.0540 0.2605 1.0000
10.500 1.3929 0.03098 0.02268 -0.0518 0.2495 1.0000
10.750 1.4043 0.03157 0.02334 -0.0496 0.2388 1.0000
11.000 1.4135 0.03214 0.02395 -0.0472 0.2278 1.0000
11.250 1.4136 0.03285 0.02493 -0.0435 0.2171 1.0000
11.500 1.4104 0.03364 0.02588 -0.0396 0.2059 1.0000
11.750 1.4036 0.03471 0.02710 -0.0358 0.1926 1.0000
12.000 1.3930 0.03628 0.02884 -0.0324 0.1756 1.0000
12.250 1.3784 0.03868 0.03131 -0.0298 0.1519 1.0000
12.500 1.3618 0.04209 0.03465 -0.0279 0.1194 1.0000
12.750 1.3462 0.04598 0.03834 -0.0265 0.0984 1.0000
13.000 1.3328 0.04995 0.04221 -0.0256 0.0872 1.0000
13.250 1.3191 0.05412 0.04630 -0.0250 0.0808 1.0000
13.500 1.3107 0.05791 0.05016 -0.0245 0.0750 1.0000
13.750 1.3003 0.06192 0.05416 -0.0242 0.0712 1.0000
14.000 1.2953 0.06537 0.05766 -0.0236 0.0677 1.0000
14.250 1.2933 0.06856 0.06093 -0.0231 0.0645 1.0000
14.500 1.2934 0.07136 0.06369 -0.0223 0.0615 1.0000
14.750 1.3004 0.07338 0.06569 -0.0207 0.0584 1.0000
15.000 1.3019 0.07641 0.06891 -0.0203 0.0561 1.0000
15.250 1.3065 0.07901 0.07160 -0.0197 0.0540 1.0000
15.500 1.3199 0.08062 0.07318 -0.0181 0.0519 1.0000
15.750 1.3431 0.08201 0.07455 -0.0155 0.0499 1.0000
16.000 1.3354 0.08626 0.07908 -0.0161 0.0493 1.0000
16.250 1.3259 0.09089 0.08398 -0.0171 0.0488 1.0000
16.500 1.3141 0.09595 0.08931 -0.0185 0.0484 1.0000
16.750 1.3002 0.10152 0.09514 -0.0205 0.0480 1.0000
17.000 1.2842 0.10764 0.10151 -0.0230 0.0478 1.0000
17.250 1.2655 0.11449 0.10862 -0.0264 0.0477 1.0000
17.500 1.2439 0.12222 0.11659 -0.0306 0.0478 1.0000
17.750 1.2198 0.13098 0.12558 -0.0359 0.0483 1.0000
18.000 1.1929 0.14099 0.13580 -0.0423 0.0489 1.0000
18.250 1.1652 0.15199 0.14698 -0.0494 0.0496 1.0000
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