GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 100,000 Max Cl/Cd: 56.41 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe376-il-100000.txt Download as CSV file: xf-goe376-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3108 0.09694 0.09214 -0.0219 1.0000 0.0447
-7.500 -0.3123 0.09508 0.09036 -0.0218 1.0000 0.0456
-7.250 -0.3156 0.09379 0.08917 -0.0226 1.0000 0.0467
-7.000 -0.3149 0.09350 0.08895 -0.0279 1.0000 0.0475
-6.750 -0.3078 0.09260 0.08806 -0.0331 1.0000 0.0479
-6.500 -0.3078 0.08660 0.08218 -0.0284 1.0000 0.0487
-6.250 -0.3055 0.08282 0.07847 -0.0247 1.0000 0.0499
-6.000 -0.3030 0.08016 0.07587 -0.0234 1.0000 0.0513
-5.750 -0.3007 0.07780 0.07355 -0.0229 1.0000 0.0529
-5.500 -0.2979 0.07558 0.07137 -0.0229 1.0000 0.0546
-5.250 -0.2931 0.07344 0.06924 -0.0236 1.0000 0.0568
-5.000 -0.2687 0.07342 0.06902 -0.0317 1.0000 0.0600
-4.750 -0.2632 0.06996 0.06556 -0.0318 1.0000 0.0608
-4.500 -0.2690 0.06618 0.06194 -0.0274 1.0000 0.0622
-4.250 -0.2665 0.06377 0.05956 -0.0256 1.0000 0.0646
-4.000 -0.2569 0.06160 0.05736 -0.0258 1.0000 0.0684
-3.750 -0.2058 0.05890 0.05429 -0.0360 0.9958 0.0748
-3.500 -0.1808 0.05428 0.04977 -0.0381 0.9889 0.0788
-3.250 -0.1228 0.05132 0.04639 -0.0475 0.9807 0.0893
-2.750 -0.0511 0.04437 0.03931 -0.0554 0.9640 0.1094
-2.500 -0.0064 0.04142 0.03617 -0.0606 0.9567 0.1238
-2.250 0.0380 0.03951 0.03388 -0.0652 0.9466 0.1472
-2.000 0.0702 0.03646 0.03086 -0.0676 0.9371 0.1655
-1.750 0.1121 0.03398 0.02828 -0.0716 0.9302 0.2087
-1.250 0.2038 0.01097 0.00599 -0.0761 0.8877 0.3941
-1.000 0.2312 0.00913 0.00417 -0.0758 0.8760 0.4497
-0.750 0.2704 0.00772 0.00259 -0.0778 0.8653 0.4744
-0.500 0.3288 0.00687 0.00117 -0.0837 0.8562 0.4115
-0.250 0.3964 0.00742 0.00018 -0.0874 0.8441 0.1732
0.000 0.4269 0.02204 0.01406 -0.0886 0.8598 0.1438
0.250 0.4664 0.02110 0.01267 -0.0888 0.8458 0.1175
0.500 0.5015 0.01981 0.01131 -0.0891 0.8303 0.1090
0.750 0.5358 0.01919 0.01042 -0.0888 0.8132 0.1017
1.000 0.5667 0.01825 0.00943 -0.0882 0.7943 0.0990
1.250 0.5942 0.01769 0.00879 -0.0872 0.7724 0.0998
1.500 0.6231 0.01722 0.00820 -0.0863 0.7525 0.1021
1.750 0.6497 0.01686 0.00776 -0.0853 0.7313 0.1026
2.000 0.6769 0.01660 0.00737 -0.0845 0.7110 0.1045
2.250 0.7044 0.01649 0.00712 -0.0837 0.6920 0.1090
2.500 0.7300 0.01652 0.00702 -0.0828 0.6721 0.1167
2.750 0.7560 0.01643 0.00702 -0.0820 0.6530 0.1594
3.000 0.8076 0.01509 0.00692 -0.0868 0.6323 1.0000
3.250 0.8319 0.01536 0.00700 -0.0856 0.6146 1.0000
3.500 0.8554 0.01564 0.00715 -0.0845 0.5963 1.0000
3.750 0.8791 0.01592 0.00731 -0.0834 0.5784 1.0000
4.000 0.9029 0.01622 0.00748 -0.0823 0.5609 1.0000
4.250 0.9268 0.01653 0.00768 -0.0812 0.5433 1.0000
4.500 0.9502 0.01687 0.00791 -0.0801 0.5254 1.0000
4.750 0.9727 0.01725 0.00823 -0.0789 0.5062 1.0000
5.000 0.9956 0.01765 0.00855 -0.0778 0.4874 1.0000
5.250 1.0188 0.01810 0.00892 -0.0767 0.4691 1.0000
5.500 1.0416 0.01862 0.00935 -0.0756 0.4511 1.0000
5.750 1.0636 0.01915 0.00988 -0.0745 0.4326 1.0000
6.000 1.0860 0.01973 0.01045 -0.0734 0.4154 1.0000
6.250 1.1084 0.02033 0.01107 -0.0723 0.3991 1.0000
6.500 1.1306 0.02092 0.01168 -0.0713 0.3835 1.0000
6.750 1.1526 0.02152 0.01230 -0.0702 0.3688 1.0000
7.000 1.1747 0.02215 0.01298 -0.0692 0.3551 1.0000
7.250 1.1961 0.02269 0.01360 -0.0680 0.3411 1.0000
7.500 1.2154 0.02300 0.01394 -0.0664 0.3245 1.0000
7.750 1.2345 0.02334 0.01432 -0.0649 0.3088 1.0000
8.000 1.2540 0.02381 0.01486 -0.0635 0.2949 1.0000
8.250 1.2713 0.02413 0.01522 -0.0617 0.2787 1.0000
8.500 1.2881 0.02453 0.01569 -0.0599 0.2631 1.0000
8.750 1.3052 0.02504 0.01633 -0.0583 0.2492 1.0000
9.000 1.3200 0.02549 0.01687 -0.0563 0.2336 1.0000
9.250 1.3321 0.02591 0.01741 -0.0539 0.2151 1.0000
9.500 1.3413 0.02633 0.01797 -0.0512 0.1896 1.0000
9.750 1.3502 0.02704 0.01879 -0.0485 0.1491 1.0000
10.000 1.3459 0.02925 0.02048 -0.0445 0.0818 1.0000
10.250 1.3392 0.03155 0.02253 -0.0402 0.0635 1.0000
10.500 1.3340 0.03364 0.02462 -0.0362 0.0575 1.0000
10.750 1.3306 0.03567 0.02679 -0.0329 0.0535 1.0000
11.000 1.3231 0.03813 0.02933 -0.0299 0.0503 1.0000
11.250 1.3146 0.04086 0.03212 -0.0274 0.0485 1.0000
11.500 1.3136 0.04321 0.03468 -0.0257 0.0459 1.0000
11.750 1.3114 0.04581 0.03742 -0.0243 0.0443 1.0000
12.000 1.3095 0.04855 0.04028 -0.0231 0.0429 1.0000
12.250 1.3091 0.05130 0.04312 -0.0221 0.0418 1.0000
12.500 1.3112 0.05397 0.04587 -0.0209 0.0406 1.0000
12.750 1.3191 0.05639 0.04831 -0.0194 0.0396 1.0000
13.000 1.3404 0.05894 0.05087 -0.0172 0.0385 1.0000
13.250 1.3488 0.06191 0.05407 -0.0161 0.0382 1.0000
13.500 1.3486 0.06536 0.05779 -0.0155 0.0379 1.0000
13.750 1.3433 0.06917 0.06188 -0.0153 0.0376 1.0000
14.000 1.3366 0.07332 0.06630 -0.0155 0.0374 1.0000
14.250 1.3253 0.07792 0.07116 -0.0163 0.0372 1.0000
14.500 1.3115 0.08301 0.07651 -0.0177 0.0371 1.0000
14.750 1.2959 0.08857 0.08231 -0.0197 0.0371 1.0000
15.000 1.2792 0.09459 0.08856 -0.0222 0.0372 1.0000
15.250 1.2607 0.10122 0.09541 -0.0254 0.0374 1.0000
15.500 1.2418 0.10828 0.10266 -0.0292 0.0377 1.0000
15.750 1.2225 0.11590 0.11045 -0.0334 0.0380 1.0000
16.000 1.2020 0.12415 0.11887 -0.0384 0.0382 1.0000
16.250 1.1840 0.13243 0.12731 -0.0435 0.0387 1.0000
16.500 1.0657 0.17400 0.16907 -0.0726 0.0464 1.0000
16.750 1.0610 0.18149 0.17652 -0.0760 0.0475 1.0000
17.000 1.0619 0.18702 0.18204 -0.0781 0.0484 1.0000
17.250 1.0357 0.20756 0.20240 -0.0897 0.0632 1.0000
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Polar data table (+)
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