GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 200,000 Max Cl/Cd: 72.3 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe276-il-200000.txt Download as CSV file: xf-goe276-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 276 (DAIMLER VII) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3959 0.11056 0.10692 -0.0179 1.0000 0.0285
-8.750 -0.3971 0.10861 0.10502 -0.0209 1.0000 0.0287
-8.500 -0.3990 0.10643 0.10291 -0.0230 1.0000 0.0288
-8.250 -0.3971 0.10367 0.10019 -0.0261 1.0000 0.0289
-8.000 -0.3940 0.09815 0.09472 -0.0249 1.0000 0.0293
-7.750 -0.3866 0.09386 0.09044 -0.0215 1.0000 0.0298
-7.500 -0.3813 0.09063 0.08723 -0.0210 1.0000 0.0303
-7.250 -0.3767 0.08762 0.08425 -0.0214 1.0000 0.0308
-7.000 -0.3717 0.08461 0.08129 -0.0225 1.0000 0.0314
-6.750 -0.3661 0.08157 0.07826 -0.0239 1.0000 0.0322
-6.500 -0.3596 0.07848 0.07520 -0.0256 1.0000 0.0330
-6.250 -0.3523 0.07537 0.07211 -0.0275 1.0000 0.0340
-6.000 -0.3436 0.07228 0.06903 -0.0298 1.0000 0.0353
-5.750 -0.3158 0.06941 0.06598 -0.0390 1.0000 0.0374
-5.500 -0.2957 0.06667 0.06302 -0.0428 1.0000 0.0377
-5.250 -0.2966 0.06073 0.05721 -0.0414 1.0000 0.0386
-5.000 -0.2905 0.05790 0.05442 -0.0399 1.0000 0.0393
-4.750 -0.2792 0.05525 0.05176 -0.0396 1.0000 0.0404
-4.500 -0.2627 0.05247 0.04892 -0.0405 1.0000 0.0420
-4.250 -0.2305 0.04890 0.04518 -0.0446 0.9986 0.0450
-4.000 -0.1711 0.04359 0.03929 -0.0539 0.9955 0.0503
-3.750 -0.1407 0.04020 0.03597 -0.0570 0.9925 0.0526
-3.500 -0.1008 0.03727 0.03285 -0.0612 0.9887 0.0572
-3.250 -0.0504 0.03379 0.02882 -0.0666 0.9856 0.0642
-3.000 -0.0137 0.03123 0.02627 -0.0701 0.9814 0.0694
-2.750 0.0298 0.02873 0.02340 -0.0738 0.9766 0.0794
-2.500 0.0733 0.02710 0.02139 -0.0773 0.9733 0.0922
-2.250 0.1112 0.02541 0.01950 -0.0800 0.9687 0.1062
-2.000 0.1477 0.02317 0.01726 -0.0828 0.9635 0.1225
-1.750 0.1881 0.02146 0.01556 -0.0864 0.9599 0.1539
-1.500 0.2257 0.02095 0.01486 -0.0886 0.9535 0.1942
-1.250 0.2655 0.01868 0.01268 -0.0917 0.9486 0.2259
-1.000 0.3226 0.01702 0.00991 -0.0923 0.9449 0.0927
-0.750 0.3588 0.01574 0.00856 -0.0932 0.9353 0.0829
-0.500 0.3979 0.01499 0.00762 -0.0944 0.9252 0.0747
-0.250 0.4350 0.01386 0.00645 -0.0955 0.9117 0.0714
0.000 0.4682 0.01311 0.00566 -0.0958 0.8937 0.0698
0.250 0.4983 0.01257 0.00509 -0.0955 0.8735 0.0696
0.500 0.5251 0.01220 0.00469 -0.0947 0.8493 0.0706
0.750 0.5513 0.01192 0.00438 -0.0938 0.8210 0.0735
1.000 0.5770 0.01172 0.00409 -0.0927 0.7831 0.0770
1.250 0.6019 0.01154 0.00370 -0.0915 0.7200 0.0806
1.500 0.6250 0.01176 0.00343 -0.0899 0.6365 0.0869
1.750 0.6494 0.01200 0.00338 -0.0889 0.5821 0.1165
2.000 0.6680 0.01040 0.00341 -0.0869 0.5510 1.0000
2.250 0.6942 0.01077 0.00351 -0.0865 0.5265 1.0000
2.500 0.7205 0.01113 0.00366 -0.0861 0.5077 1.0000
2.750 0.7469 0.01148 0.00384 -0.0858 0.4916 1.0000
3.000 0.7735 0.01182 0.00406 -0.0856 0.4770 1.0000
3.250 0.8002 0.01214 0.00429 -0.0854 0.4639 1.0000
3.500 0.8269 0.01247 0.00455 -0.0852 0.4515 1.0000
3.750 0.8534 0.01281 0.00481 -0.0850 0.4389 1.0000
4.000 0.8799 0.01316 0.00512 -0.0847 0.4273 1.0000
4.250 0.9064 0.01351 0.00541 -0.0845 0.4163 1.0000
4.500 0.9330 0.01378 0.00572 -0.0843 0.4050 1.0000
4.750 0.9594 0.01409 0.00606 -0.0841 0.3940 1.0000
5.000 0.9857 0.01441 0.00637 -0.0838 0.3833 1.0000
5.250 1.0117 0.01470 0.00667 -0.0835 0.3719 1.0000
5.500 1.0378 0.01493 0.00699 -0.0832 0.3597 1.0000
5.750 1.0636 0.01518 0.00732 -0.0828 0.3472 1.0000
6.000 1.0890 0.01540 0.00759 -0.0824 0.3329 1.0000
6.250 1.1140 0.01558 0.00780 -0.0819 0.3159 1.0000
6.500 1.1384 0.01580 0.00802 -0.0813 0.2961 1.0000
6.750 1.1626 0.01608 0.00833 -0.0808 0.2737 1.0000
7.000 1.1862 0.01650 0.00872 -0.0801 0.2533 1.0000
7.250 1.2092 0.01697 0.00916 -0.0795 0.2292 1.0000
7.500 1.2322 0.01748 0.00964 -0.0788 0.2039 1.0000
7.750 1.2548 0.01805 0.01019 -0.0781 0.1748 1.0000
8.000 1.2737 0.01913 0.01096 -0.0770 0.1225 1.0000
8.250 1.2831 0.02160 0.01277 -0.0746 0.0441 1.0000
8.750 1.3159 0.02429 0.01571 -0.0709 0.0333 1.0000
9.000 1.3310 0.02557 0.01713 -0.0691 0.0309 1.0000
9.250 1.3413 0.02722 0.01889 -0.0666 0.0287 1.0000
9.500 1.3487 0.02907 0.02084 -0.0637 0.0272 1.0000
9.750 1.3597 0.03054 0.02244 -0.0613 0.0264 1.0000
10.000 1.3687 0.03218 0.02420 -0.0587 0.0256 1.0000
10.250 1.3770 0.03392 0.02606 -0.0560 0.0250 1.0000
10.500 1.3843 0.03574 0.02800 -0.0531 0.0245 1.0000
10.750 1.3926 0.03771 0.03009 -0.0506 0.0241 1.0000
11.000 1.4014 0.03983 0.03237 -0.0482 0.0237 1.0000
11.250 1.4086 0.04196 0.03465 -0.0459 0.0231 1.0000
11.500 1.4140 0.04418 0.03699 -0.0437 0.0224 1.0000
11.750 1.4203 0.04693 0.03985 -0.0418 0.0217 1.0000
12.000 1.4250 0.05029 0.04341 -0.0399 0.0213 1.0000
12.250 1.4251 0.05346 0.04683 -0.0377 0.0213 1.0000
12.500 1.4215 0.05665 0.05027 -0.0356 0.0213 1.0000
12.750 1.4148 0.05997 0.05384 -0.0337 0.0214 1.0000
13.000 1.4053 0.06352 0.05766 -0.0323 0.0215 1.0000
13.250 1.3929 0.06744 0.06185 -0.0315 0.0216 1.0000
13.500 1.3774 0.07199 0.06669 -0.0316 0.0219 1.0000
13.750 1.3592 0.07738 0.07238 -0.0326 0.0222 1.0000
14.000 1.3375 0.08380 0.07910 -0.0349 0.0226 1.0000
14.250 1.3110 0.09154 0.08715 -0.0391 0.0229 1.0000
14.500 1.2847 0.10011 0.09599 -0.0443 0.0232 1.0000
14.750 1.2588 0.10929 0.10540 -0.0503 0.0235 1.0000
15.000 1.2325 0.11929 0.11561 -0.0570 0.0239 1.0000
15.250 1.2051 0.13030 0.12680 -0.0646 0.0242 1.0000
15.500 1.1755 0.14296 0.13962 -0.0733 0.0247 1.0000
15.750 1.1402 0.15908 0.15585 -0.0841 0.0255 1.0000
16.000 1.1130 0.17411 0.17087 -0.0929 0.0268 1.0000
16.250 1.1124 0.17909 0.17586 -0.0946 0.0278 1.0000
16.500 0.8194 0.17353 0.17043 -0.0699 0.0351 1.0000
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