Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=200,000 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: 200,000 Max Cl/Cd: 59.45 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe765-il-200000.txt Download as CSV file: xf-goe765-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5602 0.13104 0.12724 -0.0109 1.0000 0.0789
-13.250 -0.6784 0.08740 0.08349 -0.0314 1.0000 0.0537
-13.000 -0.7076 0.07763 0.07367 -0.0378 1.0000 0.0530
-12.750 -0.7524 0.06801 0.06390 -0.0440 1.0000 0.0522
-12.500 -0.7974 0.06097 0.05664 -0.0458 1.0000 0.0515
-12.250 -0.8376 0.05562 0.05103 -0.0442 1.0000 0.0510
-12.000 -0.8724 0.05132 0.04645 -0.0406 1.0000 0.0507
-11.750 -0.8971 0.04804 0.04290 -0.0361 1.0000 0.0508
-11.500 -0.9153 0.04541 0.04002 -0.0311 1.0000 0.0512
-11.250 -0.9294 0.04290 0.03725 -0.0261 1.0000 0.0514
-11.000 -0.9374 0.04039 0.03440 -0.0216 1.0000 0.0521
-10.750 -0.9409 0.03796 0.03162 -0.0176 1.0000 0.0527
-10.500 -0.9395 0.03581 0.02910 -0.0139 1.0000 0.0533
-10.250 -0.9356 0.03392 0.02683 -0.0103 1.0000 0.0540
-10.000 -0.9158 0.03197 0.02490 -0.0097 1.0000 0.0552
-9.750 -0.8982 0.03096 0.02388 -0.0083 1.0000 0.0566
-9.500 -0.8823 0.02991 0.02275 -0.0065 1.0000 0.0582
-9.250 -0.8697 0.02874 0.02139 -0.0041 1.0000 0.0596
-9.000 -0.8680 0.02797 0.02042 0.0002 1.0000 0.0607
-8.750 -0.8470 0.02644 0.01880 0.0006 0.9946 0.0623
-8.500 -0.8062 0.02525 0.01763 -0.0025 0.9853 0.0649
-8.250 -0.7657 0.02420 0.01639 -0.0053 0.9765 0.0685
-8.000 -0.7223 0.02272 0.01490 -0.0088 0.9693 0.0719
-7.750 -0.6819 0.02180 0.01394 -0.0115 0.9585 0.0761
-7.500 -0.6423 0.02069 0.01275 -0.0140 0.9478 0.0808
-7.250 -0.6066 0.01998 0.01206 -0.0157 0.9353 0.0858
-7.000 -0.5752 0.01919 0.01119 -0.0164 0.9221 0.0912
-6.750 -0.5511 0.01871 0.01072 -0.0155 0.9079 0.0966
-6.500 -0.5285 0.01820 0.01014 -0.0143 0.8939 0.1026
-6.250 -0.5075 0.01778 0.00975 -0.0129 0.8810 0.1092
-6.000 -0.4859 0.01729 0.00922 -0.0114 0.8695 0.1169
-5.750 -0.4653 0.01697 0.00888 -0.0098 0.8579 0.1257
-5.500 -0.4443 0.01650 0.00846 -0.0084 0.8466 0.1355
-5.250 -0.4236 0.01611 0.00806 -0.0068 0.8370 0.1475
-5.000 -0.4025 0.01574 0.00773 -0.0053 0.8257 0.1618
-4.750 -0.3821 0.01537 0.00741 -0.0037 0.8162 0.1790
-4.500 -0.3617 0.01499 0.00712 -0.0021 0.8059 0.1996
-4.250 -0.3412 0.01466 0.00685 -0.0005 0.7964 0.2253
-4.000 -0.3219 0.01426 0.00659 0.0013 0.7867 0.2554
-3.750 -0.3027 0.01389 0.00637 0.0031 0.7771 0.2920
-3.500 -0.2846 0.01347 0.00611 0.0052 0.7680 0.3369
-3.250 -0.2702 0.01294 0.00588 0.0079 0.7588 0.3968
-3.000 -0.2634 0.01216 0.00562 0.0122 0.7499 0.5046
-2.750 -0.1677 0.01180 0.00654 0.0004 0.7414 0.8114
-2.500 -0.1316 0.01243 0.00708 0.0002 0.7318 0.8469
-2.250 -0.0942 0.01319 0.00772 -0.0003 0.7228 0.8663
-2.000 -0.0560 0.01385 0.00826 -0.0010 0.7130 0.8816
-1.750 -0.0199 0.01442 0.00872 -0.0017 0.7033 0.8957
-1.500 0.0359 0.01502 0.00917 -0.0061 0.6930 0.9032
-1.250 0.0744 0.01539 0.00945 -0.0075 0.6822 0.9142
-1.000 0.1198 0.01569 0.00959 -0.0103 0.6725 0.9227
-0.750 0.1626 0.01586 0.00971 -0.0128 0.6604 0.9312
-0.500 0.2003 0.01603 0.00976 -0.0144 0.6504 0.9405
-0.250 0.2497 0.01601 0.00965 -0.0183 0.6383 0.9479
0.000 0.2946 0.01605 0.00962 -0.0214 0.6260 0.9590
0.250 0.3391 0.01607 0.00951 -0.0245 0.6147 0.9703
0.500 0.3916 0.01566 0.00904 -0.0294 0.6013 0.9796
0.750 0.4401 0.01521 0.00853 -0.0336 0.5878 0.9889
1.000 0.4841 0.01475 0.00799 -0.0370 0.5750 0.9965
1.250 0.5179 0.01444 0.00758 -0.0384 0.5633 1.0000
1.500 0.5394 0.01439 0.00752 -0.0375 0.5513 1.0000
1.750 0.5609 0.01438 0.00744 -0.0365 0.5404 1.0000
2.000 0.5826 0.01437 0.00737 -0.0356 0.5293 1.0000
2.250 0.6043 0.01438 0.00736 -0.0346 0.5178 1.0000
2.500 0.6262 0.01442 0.00730 -0.0337 0.5078 1.0000
2.750 0.6480 0.01444 0.00733 -0.0327 0.4962 1.0000
3.000 0.6699 0.01450 0.00735 -0.0318 0.4856 1.0000
3.250 0.6918 0.01457 0.00736 -0.0308 0.4752 1.0000
3.500 0.7138 0.01465 0.00745 -0.0299 0.4643 1.0000
3.750 0.7358 0.01477 0.00748 -0.0290 0.4550 1.0000
4.000 0.7577 0.01485 0.00761 -0.0280 0.4442 1.0000
4.250 0.7796 0.01500 0.00770 -0.0271 0.4345 1.0000
4.500 0.8014 0.01512 0.00781 -0.0261 0.4244 1.0000
4.750 0.8232 0.01528 0.00798 -0.0252 0.4144 1.0000
5.000 0.8449 0.01545 0.00809 -0.0242 0.4050 1.0000
5.250 0.8664 0.01561 0.00829 -0.0232 0.3947 1.0000
5.500 0.8879 0.01583 0.00844 -0.0222 0.3856 1.0000
5.750 0.9092 0.01598 0.00867 -0.0212 0.3752 1.0000
6.000 0.9303 0.01622 0.00887 -0.0201 0.3659 1.0000
6.250 0.9511 0.01641 0.00909 -0.0190 0.3556 1.0000
6.500 0.9718 0.01666 0.00936 -0.0179 0.3457 1.0000
6.750 0.9921 0.01691 0.00957 -0.0167 0.3361 1.0000
7.000 1.0121 0.01714 0.00988 -0.0155 0.3254 1.0000
7.250 1.0317 0.01745 0.01014 -0.0142 0.3157 1.0000
7.500 1.0508 0.01769 0.01044 -0.0129 0.3049 1.0000
7.750 1.0695 0.01799 0.01078 -0.0115 0.2942 1.0000
8.000 1.0874 0.01835 0.01107 -0.0100 0.2841 1.0000
8.250 1.1050 0.01863 0.01146 -0.0084 0.2729 1.0000
8.500 1.1216 0.01900 0.01186 -0.0067 0.2620 1.0000
8.750 1.1368 0.01944 0.01224 -0.0049 0.2515 1.0000
9.000 1.1517 0.01982 0.01271 -0.0029 0.2397 1.0000
9.250 1.1651 0.02028 0.01321 -0.0008 0.2282 1.0000
9.500 1.1763 0.02083 0.01373 0.0016 0.2172 1.0000
9.750 1.1857 0.02141 0.01430 0.0043 0.2062 1.0000
10.000 1.1942 0.02198 0.01493 0.0071 0.1949 1.0000
10.250 1.1992 0.02266 0.01561 0.0104 0.1848 1.0000
10.500 1.1993 0.02343 0.01633 0.0144 0.1756 1.0000
10.750 1.1966 0.02407 0.01703 0.0189 0.1666 1.0000
11.000 1.1846 0.02493 0.01782 0.0246 0.1606 1.0000
11.250 1.1801 0.02579 0.01877 0.0287 0.1523 1.0000
11.500 1.1720 0.02702 0.01994 0.0327 0.1457 1.0000
11.750 1.1692 0.02820 0.02119 0.0358 0.1378 1.0000
12.000 1.1637 0.02970 0.02265 0.0388 0.1312 1.0000
12.250 1.1611 0.03119 0.02419 0.0412 0.1241 1.0000
12.500 1.1566 0.03295 0.02591 0.0434 0.1182 1.0000
12.750 1.1545 0.03468 0.02769 0.0453 0.1119 1.0000
13.000 1.1499 0.03670 0.02967 0.0470 0.1067 1.0000
13.250 1.1491 0.03857 0.03163 0.0484 0.1015 1.0000
13.500 1.1446 0.04079 0.03377 0.0497 0.0969 1.0000
13.750 1.1436 0.04287 0.03595 0.0506 0.0924 1.0000
14.000 1.1414 0.04511 0.03822 0.0514 0.0885 1.0000
14.250 1.1393 0.04735 0.04041 0.0524 0.0848 1.0000
14.500 1.1379 0.04971 0.04289 0.0528 0.0813 1.0000
14.750 1.1363 0.05212 0.04532 0.0532 0.0782 1.0000
15.000 1.1365 0.05433 0.04750 0.0539 0.0751 1.0000
15.250 1.1348 0.05698 0.05027 0.0539 0.0723 1.0000
15.500 1.1339 0.05957 0.05290 0.0539 0.0697 1.0000
15.750 1.1387 0.06130 0.05450 0.0547 0.0670 1.0000
16.000 1.1346 0.06450 0.05790 0.0542 0.0650 1.0000
16.250 1.1327 0.06743 0.06091 0.0538 0.0627 1.0000
16.500 1.1350 0.06978 0.06328 0.0537 0.0610 1.0000
16.750 1.1418 0.07140 0.06481 0.0544 0.0588 1.0000
17.000 1.1359 0.07507 0.06868 0.0535 0.0574 1.0000
17.250 1.1324 0.07845 0.07219 0.0527 0.0558 1.0000
17.500 1.1327 0.08126 0.07504 0.0522 0.0543 1.0000
17.750 1.1399 0.08297 0.07668 0.0523 0.0526 1.0000
18.000 1.1403 0.08577 0.07955 0.0521 0.0515 1.0000
18.250 1.1289 0.09059 0.08459 0.0502 0.0504 1.0000
18.500 1.1210 0.09493 0.08909 0.0486 0.0496 1.0000
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Polar data table (+)
Polar graphs
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