Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Reynolds number: 50,000 Max Cl/Cd: 15.13 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe765-il-50000.txt Download as CSV file: xf-goe765-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Gottingen 765 airfoil (recovered). Thick: .144 L
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3308 0.11932 0.11259 -0.0029 1.0000 0.3160
-10.750 -0.3176 0.11501 0.10829 -0.0032 1.0000 0.3240
-10.500 -0.3367 0.11367 0.10700 -0.0035 1.0000 0.3362
-10.250 -0.3055 0.10842 0.10173 -0.0036 1.0000 0.3466
-10.000 -0.3153 0.10563 0.09900 -0.0038 1.0000 0.3582
-9.750 -0.3190 0.10320 0.09660 -0.0035 1.0000 0.3735
-9.500 -0.2920 0.09834 0.09173 -0.0039 1.0000 0.3833
-9.250 -0.5456 0.07908 0.07212 -0.0240 1.0000 0.2051
-9.000 -0.6062 0.07167 0.06467 -0.0238 1.0000 0.1880
-8.750 -0.6778 0.06528 0.05789 -0.0191 1.0000 0.1743
-8.500 -0.6839 0.06156 0.05405 -0.0166 1.0000 0.1737
-8.250 -0.6924 0.05817 0.05051 -0.0134 1.0000 0.1732
-8.000 -0.7020 0.05524 0.04742 -0.0093 1.0000 0.1728
-7.750 -0.7155 0.05284 0.04484 -0.0042 1.0000 0.1727
-7.500 -0.7306 0.05084 0.04263 0.0014 1.0000 0.1730
-7.250 -0.7456 0.04899 0.04049 0.0073 1.0000 0.1737
-7.000 -0.7575 0.04718 0.03831 0.0128 1.0000 0.1748
-6.750 -0.7506 0.04516 0.03640 0.0154 1.0000 0.1783
-6.500 -0.7479 0.04355 0.03467 0.0188 1.0000 0.1815
-6.250 -0.7466 0.04193 0.03281 0.0225 1.0000 0.1853
-6.000 -0.7459 0.04028 0.03075 0.0265 1.0000 0.1896
-5.750 -0.7394 0.03858 0.02881 0.0295 1.0000 0.1945
-5.500 -0.7277 0.03736 0.02757 0.0316 1.0000 0.2014
-5.250 -0.7200 0.03611 0.02587 0.0347 1.0000 0.2088
-5.000 -0.7042 0.03488 0.02475 0.0361 1.0000 0.2179
-4.750 -0.6915 0.03379 0.02337 0.0383 1.0000 0.2284
-4.500 -0.6756 0.03285 0.02243 0.0398 1.0000 0.2409
-4.250 -0.6588 0.03190 0.02149 0.0411 1.0000 0.2552
-4.000 -0.6412 0.03102 0.02061 0.0423 1.0000 0.2728
-3.750 -0.5981 0.03013 0.01980 0.0387 0.9928 0.3056
-3.500 -0.5340 0.02907 0.01907 0.0315 0.9822 0.3658
-3.250 -0.1700 0.03271 0.02501 -0.0147 0.9882 0.9653
-3.000 -0.0314 0.03204 0.02373 -0.0368 0.9803 1.0000
-2.750 0.0255 0.03163 0.02303 -0.0445 0.9636 1.0000
-2.500 0.0827 0.03128 0.02246 -0.0517 0.9476 1.0000
-2.250 0.1407 0.03093 0.02191 -0.0587 0.9324 1.0000
-2.000 0.2007 0.03053 0.02134 -0.0657 0.9177 1.0000
-1.750 0.2495 0.03028 0.02096 -0.0704 0.9021 1.0000
-1.500 0.2897 0.03019 0.02076 -0.0734 0.8861 1.0000
-1.250 0.3242 0.03022 0.02070 -0.0751 0.8699 1.0000
-1.000 0.3540 0.03033 0.02073 -0.0757 0.8542 1.0000
-0.750 0.3780 0.03057 0.02090 -0.0753 0.8383 1.0000
-0.500 0.3951 0.03102 0.02130 -0.0738 0.8217 1.0000
-0.250 0.4104 0.03156 0.02180 -0.0721 0.8056 1.0000
0.000 0.4258 0.03211 0.02231 -0.0703 0.7898 1.0000
0.250 0.4416 0.03268 0.02283 -0.0686 0.7749 1.0000
0.500 0.4605 0.03308 0.02319 -0.0669 0.7613 1.0000
0.750 0.4788 0.03347 0.02354 -0.0651 0.7478 1.0000
1.000 0.4899 0.03434 0.02441 -0.0630 0.7325 1.0000
1.250 0.5031 0.03512 0.02519 -0.0610 0.7187 1.0000
1.500 0.5240 0.03536 0.02538 -0.0592 0.7071 1.0000
1.750 0.5367 0.03619 0.02622 -0.0572 0.6934 1.0000
2.000 0.5459 0.03733 0.02737 -0.0551 0.6796 1.0000
2.250 0.5640 0.03781 0.02784 -0.0532 0.6683 1.0000
2.500 0.5787 0.03855 0.02858 -0.0513 0.6562 1.0000
2.750 0.5841 0.04002 0.03008 -0.0490 0.6428 1.0000
3.000 0.6073 0.04013 0.03019 -0.0472 0.6331 1.0000
3.250 0.6132 0.04159 0.03168 -0.0449 0.6204 1.0000
3.500 0.6142 0.04342 0.03354 -0.0424 0.6080 1.0000
3.750 0.6462 0.04288 0.03299 -0.0409 0.5994 1.0000
4.000 0.6329 0.04582 0.03597 -0.0379 0.5860 1.0000
4.250 0.6408 0.04717 0.03735 -0.0355 0.5755 1.0000
4.500 0.6564 0.04791 0.03812 -0.0335 0.5652 1.0000
4.750 0.6327 0.05149 0.04170 -0.0297 0.5536 1.0000
5.000 0.6858 0.04958 0.03984 -0.0292 0.5452 1.0000
5.250 0.6221 0.05588 0.04609 -0.0238 0.5335 1.0000
5.500 0.6530 0.05584 0.04610 -0.0225 0.5242 1.0000
5.750 0.5895 0.06105 0.05119 -0.0162 0.5158 1.0000
6.000 0.6164 0.06164 0.05185 -0.0151 0.5062 1.0000
6.250 0.5687 0.06603 0.05613 -0.0103 0.4991 1.0000
6.500 0.5981 0.06650 0.05668 -0.0093 0.4888 1.0000
6.750 0.5590 0.07088 0.06098 -0.0060 0.4826 1.0000
7.000 0.5947 0.07109 0.06127 -0.0050 0.4720 1.0000
7.250 0.5547 0.07580 0.06591 -0.0025 0.4665 1.0000
7.500 0.5930 0.07585 0.06605 -0.0014 0.4548 1.0000
7.750 0.5558 0.08083 0.07097 0.0002 0.4512 1.0000
8.000 0.5498 0.08378 0.07392 0.0014 0.4441 1.0000
8.250 0.5615 0.08584 0.07602 0.0025 0.4353 1.0000
8.500 0.5435 0.08993 0.08010 0.0031 0.4326 1.0000
8.750 0.5337 0.09369 0.08387 0.0034 0.4306 1.0000
9.000 0.5262 0.09784 0.08805 0.0033 0.4331 1.0000
9.250 0.5289 0.10194 0.09219 0.0029 0.4364 1.0000
9.500 0.5478 0.10358 0.09389 0.0042 0.4200 1.0000
9.750 0.4751 0.11329 0.10356 -0.0006 0.4943 1.0000
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Polar data table (+)
Polar graphs
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