GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 200,000 Max Cl/Cd: 72.93 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe280-il-200000.txt Download as CSV file: xf-goe280-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3327 0.09016 0.08698 -0.0212 1.0000 0.0253
-7.000 -0.3332 0.08774 0.08462 -0.0219 1.0000 0.0258
-6.750 -0.3338 0.08545 0.08238 -0.0226 1.0000 0.0264
-6.500 -0.3324 0.08329 0.08024 -0.0243 1.0000 0.0269
-6.250 -0.3258 0.08112 0.07808 -0.0279 1.0000 0.0274
-6.000 -0.3147 0.07864 0.07555 -0.0314 1.0000 0.0276
-5.750 -0.3026 0.07589 0.07273 -0.0337 1.0000 0.0277
-5.500 -0.2896 0.07302 0.06978 -0.0354 1.0000 0.0278
-5.250 -0.2824 0.06823 0.06499 -0.0361 1.0000 0.0282
-5.000 -0.2698 0.06280 0.05966 -0.0367 0.9973 0.0292
-4.750 -0.2365 0.05841 0.05519 -0.0418 0.9937 0.0305
-4.500 -0.1974 0.05406 0.05071 -0.0480 0.9890 0.0322
-4.250 -0.1510 0.04973 0.04618 -0.0551 0.9851 0.0349
-4.000 -0.0861 0.04800 0.04380 -0.0624 0.9805 0.0376
-3.750 -0.0591 0.04093 0.03680 -0.0668 0.9758 0.0394
-3.500 -0.0216 0.03777 0.03355 -0.0710 0.9720 0.0433
-3.250 0.0374 0.03772 0.03274 -0.0752 0.9686 0.0497
-3.000 0.0656 0.03142 0.02659 -0.0789 0.9624 0.0531
-2.750 0.1138 0.02970 0.02435 -0.0827 0.9586 0.0642
-2.500 0.1547 0.02661 0.02130 -0.0870 0.9561 0.0726
-2.250 0.1919 0.02456 0.01903 -0.0893 0.9485 0.0845
-0.750 0.3924 0.01658 0.00985 -0.0936 0.8866 0.1509
-0.500 0.4237 0.01569 0.00855 -0.0913 0.8714 0.0892
-0.250 0.4511 0.01526 0.00787 -0.0898 0.8541 0.0771
0.000 0.4768 0.01408 0.00668 -0.0887 0.8318 0.0732
0.250 0.5028 0.01343 0.00592 -0.0875 0.8078 0.0708
0.500 0.5286 0.01294 0.00531 -0.0864 0.7811 0.0697
0.750 0.5546 0.01265 0.00489 -0.0855 0.7534 0.0722
1.000 0.5808 0.01247 0.00456 -0.0847 0.7253 0.0738
1.250 0.6073 0.01236 0.00430 -0.0842 0.6976 0.0739
1.500 0.6340 0.01232 0.00412 -0.0837 0.6696 0.0748
1.750 0.6610 0.01233 0.00398 -0.0834 0.6430 0.0768
2.000 0.6882 0.01233 0.00387 -0.0831 0.6182 0.0835
2.250 0.7105 0.01093 0.00400 -0.0823 0.5963 0.7541
2.500 0.7344 0.01066 0.00386 -0.0808 0.5739 1.0000
2.750 0.7609 0.01094 0.00390 -0.0804 0.5529 1.0000
3.000 0.7876 0.01121 0.00402 -0.0802 0.5323 1.0000
3.250 0.8140 0.01150 0.00418 -0.0799 0.5127 1.0000
3.500 0.8404 0.01180 0.00436 -0.0797 0.4937 1.0000
3.750 0.8669 0.01207 0.00455 -0.0795 0.4735 1.0000
4.000 0.8929 0.01237 0.00474 -0.0792 0.4521 1.0000
4.250 0.9188 0.01264 0.00497 -0.0789 0.4272 1.0000
4.500 0.9444 0.01295 0.00518 -0.0786 0.4003 1.0000
4.750 0.9692 0.01332 0.00541 -0.0782 0.3679 1.0000
5.000 0.9926 0.01383 0.00565 -0.0777 0.3200 1.0000
5.250 1.0162 0.01439 0.00601 -0.0772 0.2812 1.0000
5.500 1.0399 0.01495 0.00640 -0.0768 0.2516 1.0000
5.750 1.0634 0.01554 0.00681 -0.0764 0.2222 1.0000
6.000 1.0877 0.01603 0.00722 -0.0761 0.2023 1.0000
6.250 1.1112 0.01659 0.00763 -0.0757 0.1808 1.0000
6.500 1.1349 0.01711 0.00804 -0.0753 0.1592 1.0000
6.750 1.1579 0.01772 0.00848 -0.0748 0.1391 1.0000
7.000 1.1813 0.01825 0.00895 -0.0743 0.1261 1.0000
7.250 1.2050 0.01875 0.00944 -0.0738 0.1159 1.0000
7.500 1.2287 0.01922 0.00998 -0.0733 0.1070 1.0000
7.750 1.2492 0.02007 0.01062 -0.0725 0.0653 1.0000
8.000 1.2666 0.02128 0.01165 -0.0711 0.0426 1.0000
8.250 1.2847 0.02237 0.01265 -0.0698 0.0242 1.0000
8.500 1.3058 0.02307 0.01344 -0.0688 0.0220 1.0000
8.750 1.3258 0.02387 0.01439 -0.0677 0.0214 1.0000
9.000 1.3450 0.02472 0.01541 -0.0664 0.0210 1.0000
9.250 1.3627 0.02568 0.01657 -0.0649 0.0207 1.0000
9.500 1.3775 0.02689 0.01801 -0.0631 0.0199 1.0000
9.750 1.3891 0.02829 0.01964 -0.0610 0.0192 1.0000
10.000 1.3996 0.02958 0.02114 -0.0586 0.0190 1.0000
10.250 1.4065 0.03093 0.02268 -0.0559 0.0190 1.0000
10.500 1.4095 0.03239 0.02434 -0.0526 0.0191 1.0000
10.750 1.4112 0.03405 0.02617 -0.0496 0.0192 1.0000
11.000 1.4117 0.03595 0.02822 -0.0469 0.0194 1.0000
11.250 1.4115 0.03805 0.03048 -0.0446 0.0196 1.0000
11.500 1.4107 0.04039 0.03297 -0.0426 0.0198 1.0000
11.750 1.4096 0.04293 0.03565 -0.0410 0.0201 1.0000
12.000 1.4086 0.04565 0.03852 -0.0396 0.0205 1.0000
12.250 1.4076 0.04853 0.04153 -0.0385 0.0209 1.0000
12.500 1.4070 0.05150 0.04463 -0.0374 0.0213 1.0000
12.750 1.4076 0.05444 0.04765 -0.0362 0.0217 1.0000
13.000 1.4129 0.05693 0.05021 -0.0347 0.0221 1.0000
13.250 1.4197 0.05917 0.05262 -0.0343 0.0227 1.0000
13.500 1.4259 0.06170 0.05539 -0.0335 0.0237 1.0000
13.750 1.4306 0.06465 0.05859 -0.0322 0.0247 1.0000
14.000 1.4298 0.06834 0.06252 -0.0314 0.0253 1.0000
14.250 1.4254 0.07255 0.06698 -0.0311 0.0259 1.0000
14.500 1.4188 0.07716 0.07182 -0.0311 0.0264 1.0000
14.750 1.4105 0.08219 0.07707 -0.0313 0.0272 1.0000
15.000 1.4115 0.08653 0.08158 -0.0304 0.0283 1.0000
15.250 1.3985 0.09157 0.08688 -0.0330 0.0289 1.0000
15.500 1.3780 0.09846 0.09406 -0.0366 0.0293 1.0000
15.750 1.3562 0.10615 0.10202 -0.0409 0.0296 1.0000
16.000 1.3343 0.11436 0.11046 -0.0458 0.0299 1.0000
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Polar data table (+)
Polar graphs
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