Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=100,000 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: 100,000 Max Cl/Cd: 41.52 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe765-il-100000.txt Download as CSV file: xf-goe765-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4067 0.10733 0.10260 -0.0150 1.0000 0.1743
-10.750 -0.4001 0.10228 0.09758 -0.0155 1.0000 0.1768
-10.500 -0.6483 0.08086 0.07568 -0.0330 1.0000 0.1278
-10.250 -0.5752 0.07949 0.07446 -0.0310 1.0000 0.1309
-10.000 -0.7249 0.06005 0.05446 -0.0302 1.0000 0.0957
-9.750 -0.8165 0.05208 0.04539 -0.0187 1.0000 0.0896
-9.500 -0.7956 0.04956 0.04305 -0.0187 1.0000 0.0914
-9.250 -0.7883 0.04744 0.04085 -0.0165 1.0000 0.0929
-9.000 -0.7869 0.04507 0.03828 -0.0133 1.0000 0.0942
-8.750 -0.7890 0.04265 0.03561 -0.0093 1.0000 0.0952
-8.500 -0.7960 0.04073 0.03346 -0.0043 1.0000 0.0959
-8.250 -0.8085 0.03936 0.03189 0.0018 1.0000 0.0966
-8.000 -0.8189 0.03805 0.03035 0.0076 1.0000 0.0973
-7.750 -0.8259 0.03673 0.02874 0.0129 1.0000 0.0987
-7.500 -0.8296 0.03554 0.02716 0.0177 0.9998 0.1004
-7.250 -0.7904 0.03326 0.02479 0.0145 0.9919 0.1048
-7.000 -0.7497 0.03163 0.02294 0.0115 0.9835 0.1102
-6.750 -0.7113 0.02979 0.02081 0.0091 0.9749 0.1162
-6.500 -0.6658 0.02852 0.01946 0.0053 0.9679 0.1241
-6.250 -0.6234 0.02706 0.01793 0.0022 0.9593 0.1327
-6.000 -0.5763 0.02586 0.01655 -0.0015 0.9526 0.1441
-5.750 -0.5310 0.02480 0.01550 -0.0051 0.9445 0.1575
-5.500 -0.4809 0.02363 0.01438 -0.0095 0.9384 0.1746
-5.250 -0.4403 0.02262 0.01349 -0.0120 0.9287 0.1934
-5.000 -0.3988 0.02166 0.01274 -0.0148 0.9202 0.2168
-4.750 -0.3628 0.02088 0.01206 -0.0163 0.9101 0.2463
-4.500 -0.3351 0.02025 0.01163 -0.0162 0.8984 0.2789
-4.250 -0.3040 0.01941 0.01110 -0.0166 0.8889 0.3238
-4.000 -0.2817 0.01867 0.01073 -0.0154 0.8767 0.3800
-3.750 -0.1628 0.01737 0.01152 -0.0292 0.8750 0.7498
-3.500 -0.1257 0.01876 0.01279 -0.0279 0.8625 0.8186
-3.250 -0.0817 0.02011 0.01395 -0.0280 0.8513 0.8540
-3.000 -0.0347 0.02116 0.01480 -0.0292 0.8397 0.8815
-2.750 0.0234 0.02197 0.01541 -0.0331 0.8272 0.9040
-2.500 0.0709 0.02244 0.01571 -0.0355 0.8151 0.9261
-2.250 0.1296 0.02246 0.01555 -0.0403 0.8032 0.9450
-2.000 0.1855 0.02219 0.01515 -0.0453 0.7891 0.9637
-1.750 0.2379 0.02178 0.01459 -0.0500 0.7762 0.9826
-1.500 0.3007 0.02058 0.01322 -0.0567 0.7635 1.0000
-1.250 0.3183 0.02046 0.01303 -0.0553 0.7499 1.0000
-1.000 0.3365 0.02039 0.01288 -0.0539 0.7372 1.0000
-0.750 0.3544 0.02027 0.01263 -0.0521 0.7263 1.0000
-0.500 0.3734 0.02021 0.01252 -0.0509 0.7132 1.0000
-0.250 0.3925 0.02017 0.01242 -0.0495 0.7008 1.0000
0.000 0.4116 0.02006 0.01218 -0.0478 0.6907 1.0000
0.250 0.4315 0.02007 0.01217 -0.0467 0.6772 1.0000
0.500 0.4514 0.02005 0.01209 -0.0454 0.6654 1.0000
0.750 0.4715 0.01997 0.01191 -0.0439 0.6548 1.0000
1.000 0.4918 0.02003 0.01195 -0.0427 0.6418 1.0000
1.250 0.5124 0.02003 0.01187 -0.0414 0.6312 1.0000
1.500 0.5332 0.02002 0.01180 -0.0401 0.6195 1.0000
1.750 0.5540 0.02012 0.01190 -0.0390 0.6074 1.0000
2.000 0.5754 0.02008 0.01173 -0.0376 0.5981 1.0000
2.250 0.5962 0.02021 0.01188 -0.0365 0.5851 1.0000
2.500 0.6174 0.02032 0.01198 -0.0354 0.5740 1.0000
2.750 0.6391 0.02034 0.01191 -0.0341 0.5640 1.0000
3.000 0.6600 0.02054 0.01215 -0.0330 0.5518 1.0000
3.250 0.6819 0.02061 0.01214 -0.0318 0.5423 1.0000
3.500 0.7031 0.02078 0.01232 -0.0307 0.5307 1.0000
3.750 0.7243 0.02100 0.01254 -0.0296 0.5200 1.0000
4.000 0.7465 0.02106 0.01252 -0.0284 0.5104 1.0000
4.250 0.7670 0.02136 0.01291 -0.0273 0.4987 1.0000
4.500 0.7895 0.02148 0.01293 -0.0262 0.4897 1.0000
4.750 0.8099 0.02176 0.01328 -0.0250 0.4781 1.0000
5.000 0.8310 0.02204 0.01357 -0.0239 0.4679 1.0000
5.250 0.8530 0.02218 0.01365 -0.0227 0.4579 1.0000
5.500 0.8727 0.02257 0.01414 -0.0215 0.4467 1.0000
5.750 0.8956 0.02270 0.01415 -0.0204 0.4375 1.0000
6.000 0.9144 0.02308 0.01466 -0.0190 0.4258 1.0000
6.250 0.9348 0.02342 0.01501 -0.0177 0.4155 1.0000
6.500 0.9565 0.02360 0.01514 -0.0165 0.4053 1.0000
6.750 0.9743 0.02407 0.01573 -0.0150 0.3938 1.0000
7.000 0.9957 0.02432 0.01591 -0.0138 0.3838 1.0000
7.250 1.0143 0.02465 0.01629 -0.0123 0.3722 1.0000
7.500 1.0316 0.02512 0.01684 -0.0107 0.3608 1.0000
7.750 1.0529 0.02536 0.01697 -0.0094 0.3503 1.0000
8.000 1.0688 0.02578 0.01749 -0.0076 0.3384 1.0000
8.250 1.0845 0.02628 0.01808 -0.0057 0.3267 1.0000
8.500 1.1035 0.02659 0.01830 -0.0042 0.3156 1.0000
8.750 1.1186 0.02698 0.01873 -0.0022 0.3035 1.0000
9.000 1.1307 0.02756 0.01943 0.0001 0.2914 1.0000
9.250 1.1450 0.02802 0.01988 0.0022 0.2798 1.0000
9.500 1.1618 0.02836 0.02008 0.0039 0.2681 1.0000
9.750 1.1680 0.02904 0.02093 0.0070 0.2559 1.0000
10.000 1.1757 0.02972 0.02168 0.0099 0.2441 1.0000
10.250 1.1849 0.03034 0.02224 0.0126 0.2329 1.0000
10.500 1.1921 0.03098 0.02282 0.0155 0.2216 1.0000
10.750 1.1913 0.03194 0.02390 0.0194 0.2108 1.0000
11.000 1.1940 0.03281 0.02474 0.0228 0.2009 1.0000
11.250 1.1958 0.03363 0.02548 0.0263 0.1912 1.0000
11.500 1.1861 0.03474 0.02670 0.0312 0.1832 1.0000
11.750 1.1892 0.03558 0.02735 0.0344 0.1746 1.0000
12.000 1.1737 0.03691 0.02888 0.0394 0.1683 1.0000
12.250 1.1787 0.03796 0.02975 0.0418 0.1599 1.0000
12.500 1.1658 0.03967 0.03167 0.0454 0.1539 1.0000
12.750 1.1737 0.04084 0.03263 0.0472 0.1459 1.0000
13.000 1.1608 0.04294 0.03498 0.0500 0.1406 1.0000
13.250 1.1758 0.04402 0.03579 0.0512 0.1330 1.0000
13.500 1.1596 0.04659 0.03866 0.0535 0.1289 1.0000
13.750 1.1582 0.04844 0.04054 0.0549 0.1236 1.0000
14.000 1.1646 0.05026 0.04231 0.0561 0.1183 1.0000
14.250 1.1515 0.05320 0.04548 0.0573 0.1148 1.0000
14.500 1.1597 0.05470 0.04689 0.0583 0.1099 1.0000
14.750 1.1578 0.05730 0.04957 0.0591 0.1061 1.0000
15.000 1.1405 0.06105 0.05357 0.0595 0.1038 1.0000
15.250 1.1290 0.06449 0.05716 0.0596 0.1011 1.0000
15.500 1.1567 0.06486 0.05728 0.0608 0.0961 1.0000
15.750 1.1309 0.06973 0.06244 0.0602 0.0951 1.0000
16.000 1.1021 0.07538 0.06837 0.0589 0.0943 1.0000
16.250 1.0672 0.08240 0.07566 0.0565 0.0938 1.0000
16.500 1.0240 0.09143 0.08495 0.0527 0.0943 1.0000
16.750 0.9562 0.10568 0.09946 0.0455 0.0956 1.0000
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Polar data table (+)
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