Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| 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: 28.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe765-il-50000-n5.txt Download as CSV file: xf-goe765-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5745 0.09841 0.09078 -0.0247 1.0000 0.0784
-11.750 -0.6057 0.08743 0.07979 -0.0321 1.0000 0.0782
-11.500 -0.6435 0.07845 0.07075 -0.0376 1.0000 0.0778
-11.250 -0.6772 0.07208 0.06425 -0.0395 1.0000 0.0774
-11.000 -0.7102 0.06700 0.05901 -0.0389 1.0000 0.0774
-10.750 -0.7396 0.06287 0.05468 -0.0363 1.0000 0.0777
-10.500 -0.7644 0.05942 0.05099 -0.0324 1.0000 0.0780
-10.250 -0.7854 0.05598 0.04719 -0.0283 1.0000 0.0786
-10.000 -0.7837 0.05360 0.04472 -0.0260 1.0000 0.0798
-9.750 -0.7776 0.05161 0.04264 -0.0239 1.0000 0.0814
-9.500 -0.7728 0.04960 0.04050 -0.0216 1.0000 0.0834
-9.250 -0.7711 0.04731 0.03795 -0.0188 1.0000 0.0856
-9.000 -0.7705 0.04483 0.03507 -0.0155 1.0000 0.0880
-8.750 -0.7639 0.04269 0.03266 -0.0129 1.0000 0.0902
-8.500 -0.7505 0.04138 0.03137 -0.0111 1.0000 0.0928
-8.250 -0.7412 0.03998 0.02984 -0.0086 1.0000 0.0960
-8.000 -0.7354 0.03850 0.02809 -0.0053 1.0000 0.0993
-7.750 -0.7292 0.03721 0.02665 -0.0022 1.0000 0.1022
-7.500 -0.7234 0.03644 0.02593 0.0010 1.0000 0.1052
-7.250 -0.7189 0.03562 0.02499 0.0045 1.0000 0.1088
-7.000 -0.6933 0.03419 0.02326 0.0042 0.9920 0.1148
-6.750 -0.6548 0.03298 0.02206 0.0014 0.9807 0.1225
-6.500 -0.6142 0.03167 0.02064 -0.0015 0.9706 0.1319
-6.250 -0.5724 0.03053 0.01934 -0.0044 0.9605 0.1437
-6.000 -0.5272 0.02948 0.01823 -0.0080 0.9521 0.1581
-5.750 -0.4815 0.02848 0.01725 -0.0117 0.9431 0.1752
-5.500 -0.4371 0.02755 0.01641 -0.0151 0.9336 0.1951
-5.250 -0.3922 0.02666 0.01560 -0.0185 0.9247 0.2207
-5.000 -0.3556 0.02591 0.01494 -0.0204 0.9129 0.2490
-4.750 -0.3208 0.02518 0.01432 -0.0219 0.9017 0.2839
-4.500 -0.2878 0.02439 0.01374 -0.0231 0.8909 0.3264
-4.250 -0.2636 0.02370 0.01331 -0.0225 0.8778 0.3760
-3.750 -0.1374 0.02286 0.01423 -0.0312 0.8617 0.6971
-3.500 -0.0994 0.02368 0.01491 -0.0309 0.8498 0.7720
-3.250 -0.0679 0.02437 0.01538 -0.0299 0.8379 0.8173
-3.000 -0.0343 0.02505 0.01586 -0.0296 0.8245 0.8517
-2.750 0.0006 0.02560 0.01621 -0.0298 0.8118 0.8803
-2.500 0.0467 0.02597 0.01634 -0.0321 0.8004 0.9038
-2.250 0.0862 0.02622 0.01643 -0.0338 0.7872 0.9251
-2.000 0.1302 0.02628 0.01631 -0.0365 0.7742 0.9435
-1.750 0.1771 0.02608 0.01592 -0.0398 0.7621 0.9598
-1.500 0.2309 0.02567 0.01536 -0.0448 0.7488 0.9798
-1.250 0.2916 0.02487 0.01443 -0.0514 0.7348 1.0000
-1.000 0.3103 0.02482 0.01426 -0.0501 0.7230 1.0000
-0.750 0.3292 0.02477 0.01412 -0.0487 0.7110 1.0000
-0.500 0.3484 0.02479 0.01408 -0.0475 0.6982 1.0000
-0.250 0.3678 0.02477 0.01397 -0.0462 0.6871 1.0000
0.000 0.3872 0.02479 0.01392 -0.0449 0.6751 1.0000
0.250 0.4067 0.02486 0.01394 -0.0436 0.6627 1.0000
0.500 0.4269 0.02484 0.01382 -0.0422 0.6526 1.0000
0.750 0.4471 0.02497 0.01393 -0.0412 0.6399 1.0000
1.000 0.4674 0.02506 0.01398 -0.0400 0.6283 1.0000
1.250 0.4877 0.02509 0.01394 -0.0385 0.6181 1.0000
1.500 0.5075 0.02528 0.01413 -0.0374 0.6055 1.0000
1.750 0.5279 0.02537 0.01416 -0.0360 0.5954 1.0000
2.000 0.5480 0.02552 0.01431 -0.0348 0.5840 1.0000
2.250 0.5678 0.02573 0.01452 -0.0335 0.5724 1.0000
2.500 0.5887 0.02578 0.01450 -0.0321 0.5631 1.0000
2.750 0.6080 0.02611 0.01488 -0.0309 0.5509 1.0000
3.000 0.6284 0.02627 0.01502 -0.0296 0.5410 1.0000
3.250 0.6483 0.02652 0.01526 -0.0283 0.5302 1.0000
3.500 0.6677 0.02683 0.01562 -0.0270 0.5194 1.0000
3.750 0.6885 0.02696 0.01570 -0.0255 0.5102 1.0000
4.000 0.7068 0.02742 0.01623 -0.0243 0.4988 1.0000
4.250 0.7277 0.02755 0.01631 -0.0228 0.4900 1.0000
4.500 0.7456 0.02803 0.01689 -0.0214 0.4787 1.0000
4.750 0.7649 0.02837 0.01725 -0.0200 0.4692 1.0000
5.000 0.7838 0.02870 0.01761 -0.0185 0.4591 1.0000
5.250 0.8013 0.02921 0.01820 -0.0170 0.4490 1.0000
5.500 0.8214 0.02944 0.01841 -0.0155 0.4400 1.0000
5.750 0.8368 0.03011 0.01920 -0.0139 0.4292 1.0000
6.000 0.8582 0.03024 0.01928 -0.0124 0.4210 1.0000
6.250 0.8712 0.03106 0.02026 -0.0106 0.4098 1.0000
6.500 0.8897 0.03142 0.02062 -0.0089 0.4009 1.0000
6.750 0.9042 0.03206 0.02136 -0.0071 0.3906 1.0000
7.000 0.9193 0.03266 0.02203 -0.0052 0.3810 1.0000
7.250 0.9360 0.03310 0.02250 -0.0034 0.3714 1.0000
7.500 0.9468 0.03393 0.02345 -0.0011 0.3612 1.0000
7.750 0.9665 0.03414 0.02364 0.0005 0.3523 1.0000
8.000 0.9721 0.03525 0.02492 0.0032 0.3416 1.0000
8.250 0.9881 0.03566 0.02532 0.0051 0.3325 1.0000
8.500 0.9946 0.03659 0.02638 0.0078 0.3222 1.0000
8.750 1.0034 0.03739 0.02725 0.0104 0.3128 1.0000
9.000 1.0140 0.03797 0.02786 0.0128 0.3031 1.0000
9.250 1.0136 0.03923 0.02923 0.0161 0.2936 1.0000
9.500 1.0297 0.03942 0.02935 0.0182 0.2843 1.0000
9.750 1.0177 0.04123 0.03135 0.0224 0.2753 1.0000
10.000 1.0271 0.04172 0.03182 0.0249 0.2665 1.0000
10.250 1.0087 0.04355 0.03377 0.0298 0.2590 1.0000
10.500 1.0161 0.04405 0.03421 0.0324 0.2506 1.0000
10.750 0.9934 0.04658 0.03688 0.0362 0.2434 1.0000
11.000 1.0029 0.04709 0.03732 0.0383 0.2349 1.0000
11.250 0.9790 0.05044 0.04083 0.0407 0.2277 1.0000
11.500 0.9891 0.05102 0.04134 0.0425 0.2191 1.0000
11.750 0.9638 0.05519 0.04568 0.0437 0.2120 1.0000
12.000 0.9757 0.05569 0.04611 0.0453 0.2037 1.0000
12.250 0.9456 0.06108 0.05169 0.0454 0.1970 1.0000
12.500 0.9621 0.06106 0.05157 0.0470 0.1888 1.0000
12.750 0.9217 0.06851 0.05924 0.0455 0.1829 1.0000
13.000 0.9500 0.06682 0.05741 0.0478 0.1746 1.0000
13.250 0.8881 0.07829 0.06914 0.0439 0.1697 1.0000
13.500 0.9004 0.07884 0.06967 0.0451 0.1626 1.0000
13.750 0.8472 0.09048 0.08142 0.0406 0.1571 1.0000
14.000 0.8063 0.10102 0.09199 0.0365 0.1500 1.0000
14.250 0.8297 0.09946 0.09045 0.0385 0.1451 1.0000
14.500 0.7576 0.11757 0.10853 0.0304 0.1368 1.0000
14.750 0.7976 0.11212 0.10316 0.0343 0.1336 1.0000
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Polar data table (+)
Polar graphs
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