GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 100,000 Max Cl/Cd: 39.11 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe769-il-100000.txt Download as CSV file: xf-goe769-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1977 0.09965 0.09508 -0.0234 1.0000 0.1123
-8.000 -0.2249 0.09944 0.09504 -0.0271 1.0000 0.1148
-7.750 -0.2634 0.09998 0.09587 -0.0272 1.0000 0.1152
-7.500 -0.2576 0.09691 0.09294 -0.0235 0.9984 0.1159
-7.250 -0.2068 0.09163 0.08766 -0.0236 0.9914 0.1191
-7.000 -0.1725 0.08727 0.08330 -0.0314 0.9708 0.1245
-6.750 -0.1577 0.08178 0.07776 -0.0498 0.9404 0.1296
-6.500 -0.1161 0.07763 0.07361 -0.0489 0.9262 0.1321
-6.250 -0.0849 0.07396 0.06987 -0.0535 0.9041 0.1371
-6.000 -0.0859 0.06992 0.06559 -0.0676 0.8757 0.1444
-5.750 -0.0622 0.06687 0.06255 -0.0644 0.8569 0.1463
-5.500 -0.0443 0.06461 0.06023 -0.0631 0.8375 0.1496
-5.250 -0.0448 0.06202 0.05729 -0.0720 0.8183 0.1607
-5.000 -0.0278 0.05909 0.05445 -0.0686 0.8010 0.1627
-4.750 -0.0115 0.05727 0.05262 -0.0661 0.7843 0.1668
-4.500 -0.0016 0.05470 0.04978 -0.0702 0.7696 0.1796
-4.250 0.0156 0.05260 0.04767 -0.0676 0.7556 0.1831
-4.000 0.0301 0.05064 0.04546 -0.0701 0.7401 0.1982
-3.750 0.0471 0.04840 0.04326 -0.0680 0.7257 0.2016
-3.500 0.0745 0.03623 0.02949 -0.0762 0.7188 0.1166
-3.250 0.0968 0.03397 0.02695 -0.0754 0.7053 0.1130
-3.000 0.1199 0.03181 0.02436 -0.0746 0.6937 0.1125
-2.750 0.1429 0.02991 0.02210 -0.0737 0.6792 0.1123
-2.500 0.1675 0.02825 0.02002 -0.0727 0.6668 0.1126
-2.250 0.1932 0.02693 0.01818 -0.0716 0.6544 0.1146
-2.000 0.2174 0.02593 0.01716 -0.0708 0.6404 0.1191
-1.750 0.2437 0.02518 0.01615 -0.0698 0.6286 0.1248
-1.500 0.2696 0.02421 0.01492 -0.0688 0.6150 0.1306
-1.250 0.2952 0.02370 0.01436 -0.0679 0.6021 0.1399
-1.000 0.3219 0.02296 0.01347 -0.0670 0.5913 0.1507
-0.750 0.3473 0.02243 0.01293 -0.0662 0.5782 0.1643
-0.500 0.3741 0.02196 0.01235 -0.0653 0.5682 0.1809
-0.250 0.3995 0.02158 0.01203 -0.0645 0.5559 0.1991
0.000 0.4255 0.02124 0.01172 -0.0637 0.5456 0.2193
0.250 0.4513 0.02088 0.01143 -0.0628 0.5348 0.2424
0.500 0.4767 0.02061 0.01126 -0.0619 0.5242 0.2723
0.750 0.5031 0.02009 0.01093 -0.0611 0.5144 0.3242
1.000 0.5666 0.01809 0.01061 -0.0667 0.4999 1.0000
1.250 0.5925 0.01830 0.01047 -0.0657 0.4911 1.0000
1.500 0.6160 0.01859 0.01062 -0.0646 0.4797 1.0000
1.750 0.6413 0.01886 0.01065 -0.0637 0.4705 1.0000
2.000 0.6654 0.01915 0.01079 -0.0627 0.4598 1.0000
2.250 0.6901 0.01950 0.01097 -0.0618 0.4503 1.0000
2.500 0.7146 0.01980 0.01112 -0.0609 0.4401 1.0000
2.750 0.7388 0.02022 0.01140 -0.0600 0.4304 1.0000
3.000 0.7637 0.02055 0.01157 -0.0591 0.4208 1.0000
3.250 0.7876 0.02104 0.01198 -0.0582 0.4115 1.0000
3.500 0.8124 0.02141 0.01221 -0.0574 0.4023 1.0000
3.750 0.8362 0.02194 0.01265 -0.0565 0.3935 1.0000
4.000 0.8603 0.02236 0.01299 -0.0557 0.3847 1.0000
4.250 0.8852 0.02292 0.01340 -0.0550 0.3771 1.0000
4.500 0.9074 0.02346 0.01398 -0.0540 0.3685 1.0000
4.750 0.9350 0.02391 0.01415 -0.0536 0.3621 1.0000
5.000 0.9545 0.02463 0.01503 -0.0524 0.3538 1.0000
5.250 0.9795 0.02509 0.01538 -0.0517 0.3473 1.0000
5.500 1.0037 0.02579 0.01598 -0.0510 0.3413 1.0000
5.750 1.0237 0.02652 0.01683 -0.0499 0.3341 1.0000
6.000 1.0495 0.02698 0.01715 -0.0494 0.3286 1.0000
6.250 1.0717 0.02782 0.01798 -0.0486 0.3231 1.0000
6.500 1.0906 0.02869 0.01897 -0.0474 0.3169 1.0000
6.750 1.1151 0.02923 0.01942 -0.0468 0.3119 1.0000
7.000 1.1401 0.03000 0.02009 -0.0463 0.3073 1.0000
7.250 1.1544 0.03114 0.02146 -0.0448 0.3016 1.0000
7.500 1.1755 0.03190 0.02224 -0.0439 0.2968 1.0000
7.750 1.2025 0.03246 0.02265 -0.0436 0.2929 1.0000
8.000 1.2176 0.03380 0.02414 -0.0423 0.2886 1.0000
8.250 1.2302 0.03511 0.02564 -0.0407 0.2837 1.0000
8.500 1.2506 0.03590 0.02643 -0.0398 0.2795 1.0000
8.750 1.2784 0.03646 0.02686 -0.0397 0.2761 1.0000
9.000 1.2877 0.03824 0.02883 -0.0379 0.2725 1.0000
9.250 1.2888 0.04030 0.03117 -0.0355 0.2685 1.0000
9.500 1.3015 0.04161 0.03256 -0.0341 0.2647 1.0000
9.750 1.3260 0.04220 0.03309 -0.0337 0.2614 1.0000
10.000 1.3566 0.04297 0.03370 -0.0340 0.2584 1.0000
10.250 1.3261 0.04675 0.03797 -0.0294 0.2555 1.0000
10.500 1.2706 0.05186 0.04346 -0.0237 0.2532 1.0000
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Polar data table (+)
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