Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=200,000 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: 200,000 Max Cl/Cd: 58.57 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe765-il-200000-n5.txt Download as CSV file: xf-goe765-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9189 0.07214 0.06730 -0.0397 1.0000 0.0291
-15.250 -0.9517 0.06336 0.05825 -0.0456 1.0000 0.0291
-15.000 -0.9716 0.05771 0.05240 -0.0484 1.0000 0.0292
-14.750 -0.9865 0.05338 0.04788 -0.0496 1.0000 0.0294
-14.500 -0.9988 0.04976 0.04407 -0.0498 1.0000 0.0296
-14.250 -1.0073 0.04685 0.04099 -0.0492 1.0000 0.0299
-14.000 -1.0141 0.04426 0.03822 -0.0479 1.0000 0.0303
-13.750 -1.0193 0.04193 0.03568 -0.0463 1.0000 0.0307
-13.500 -1.0228 0.03977 0.03332 -0.0442 1.0000 0.0311
-13.250 -1.0248 0.03782 0.03111 -0.0419 1.0000 0.0317
-13.000 -1.0213 0.03628 0.02945 -0.0397 1.0000 0.0321
-12.750 -1.0142 0.03509 0.02823 -0.0378 1.0000 0.0326
-12.500 -1.0066 0.03395 0.02703 -0.0357 1.0000 0.0331
-12.250 -0.9983 0.03282 0.02582 -0.0335 1.0000 0.0336
-12.000 -0.9892 0.03168 0.02457 -0.0313 1.0000 0.0342
-11.750 -0.9791 0.03057 0.02333 -0.0291 1.0000 0.0349
-11.500 -0.9678 0.02948 0.02209 -0.0270 1.0000 0.0358
-11.250 -0.9551 0.02845 0.02088 -0.0250 1.0000 0.0366
-11.000 -0.9421 0.02761 0.02005 -0.0230 1.0000 0.0374
-10.750 -0.9282 0.02686 0.01928 -0.0210 1.0000 0.0383
-10.500 -0.9133 0.02608 0.01845 -0.0191 1.0000 0.0392
-10.250 -0.8975 0.02529 0.01757 -0.0173 1.0000 0.0403
-10.000 -0.8807 0.02450 0.01665 -0.0156 1.0000 0.0414
-9.750 -0.8650 0.02375 0.01590 -0.0138 1.0000 0.0424
-9.500 -0.8489 0.02315 0.01531 -0.0120 1.0000 0.0436
-9.250 -0.8217 0.02244 0.01454 -0.0124 0.9650 0.0454
-9.000 -0.7843 0.02161 0.01357 -0.0148 0.9389 0.0477
-8.750 -0.7538 0.02091 0.01285 -0.0157 0.9168 0.0497
-8.500 -0.7283 0.02036 0.01221 -0.0155 0.8976 0.0518
-8.250 -0.7056 0.01987 0.01159 -0.0145 0.8810 0.0542
-8.000 -0.6853 0.01941 0.01110 -0.0131 0.8664 0.0564
-7.750 -0.6642 0.01901 0.01062 -0.0118 0.8534 0.0593
-7.500 -0.6435 0.01859 0.01012 -0.0104 0.8411 0.0621
-7.250 -0.6226 0.01819 0.00970 -0.0091 0.8298 0.0653
-7.000 -0.6009 0.01787 0.00926 -0.0078 0.8195 0.0691
-6.750 -0.5800 0.01745 0.00885 -0.0064 0.8087 0.0729
-6.500 -0.5581 0.01713 0.00845 -0.0052 0.7993 0.0776
-6.250 -0.5364 0.01676 0.00808 -0.0040 0.7893 0.0824
-6.000 -0.5140 0.01647 0.00772 -0.0028 0.7805 0.0883
-5.750 -0.4919 0.01612 0.00739 -0.0016 0.7708 0.0947
-5.500 -0.4691 0.01585 0.00706 -0.0005 0.7623 0.1019
-5.250 -0.4464 0.01554 0.00676 0.0006 0.7528 0.1106
-5.000 -0.4238 0.01525 0.00646 0.0017 0.7446 0.1201
-4.750 -0.4007 0.01498 0.00620 0.0027 0.7351 0.1316
-4.500 -0.3778 0.01472 0.00593 0.0038 0.7271 0.1446
-4.250 -0.3545 0.01445 0.00571 0.0048 0.7176 0.1599
-4.000 -0.3319 0.01420 0.00547 0.0059 0.7094 0.1774
-3.750 -0.3090 0.01392 0.00527 0.0069 0.6998 0.1977
-3.500 -0.2864 0.01368 0.00506 0.0081 0.6914 0.2211
-3.250 -0.2638 0.01341 0.00489 0.0092 0.6822 0.2475
-3.000 -0.2419 0.01316 0.00470 0.0104 0.6738 0.2777
-2.750 -0.2204 0.01287 0.00453 0.0117 0.6651 0.3119
-2.500 -0.2002 0.01255 0.00435 0.0133 0.6565 0.3534
-2.250 -0.1829 0.01213 0.00417 0.0155 0.6485 0.4132
-2.000 -0.1720 0.01149 0.00398 0.0190 0.6401 0.5159
-1.750 -0.1439 0.01066 0.00406 0.0195 0.6321 0.7157
-1.500 -0.0409 0.01123 0.00483 0.0053 0.6199 0.8196
-1.250 -0.0097 0.01149 0.00503 0.0052 0.6104 0.8423
-1.000 0.0198 0.01173 0.00519 0.0054 0.6010 0.8586
-0.750 0.0512 0.01201 0.00540 0.0052 0.5911 0.8701
-0.500 0.0791 0.01230 0.00559 0.0058 0.5817 0.8826
-0.250 0.1056 0.01258 0.00583 0.0066 0.5716 0.8958
0.000 0.1492 0.01301 0.00615 0.0040 0.5611 0.9021
0.250 0.1753 0.01322 0.00630 0.0047 0.5508 0.9123
0.500 0.2181 0.01352 0.00651 0.0020 0.5396 0.9170
0.750 0.2464 0.01372 0.00665 0.0022 0.5290 0.9254
1.000 0.2850 0.01392 0.00679 0.0003 0.5175 0.9303
1.250 0.3223 0.01409 0.00688 -0.0015 0.5067 0.9350
1.500 0.3470 0.01419 0.00692 -0.0008 0.4958 0.9406
1.750 0.3749 0.01423 0.00692 -0.0009 0.4856 0.9436
2.000 0.4071 0.01428 0.00689 -0.0018 0.4745 0.9454
2.250 0.4379 0.01433 0.00690 -0.0025 0.4635 0.9477
2.500 0.4665 0.01440 0.00692 -0.0027 0.4532 0.9506
2.750 0.4916 0.01449 0.00698 -0.0023 0.4428 0.9541
3.000 0.5162 0.01459 0.00704 -0.0017 0.4331 0.9574
3.250 0.5479 0.01466 0.00706 -0.0026 0.4225 0.9590
3.500 0.5782 0.01473 0.00712 -0.0033 0.4122 0.9609
3.750 0.6069 0.01484 0.00718 -0.0036 0.4025 0.9632
4.000 0.6344 0.01495 0.00729 -0.0037 0.3925 0.9660
4.250 0.6579 0.01512 0.00742 -0.0030 0.3836 0.9692
4.500 0.6859 0.01523 0.00753 -0.0033 0.3738 0.9712
4.750 0.7166 0.01534 0.00763 -0.0041 0.3643 0.9729
5.000 0.7458 0.01548 0.00775 -0.0046 0.3547 0.9749
5.250 0.7734 0.01563 0.00791 -0.0048 0.3455 0.9770
5.500 0.7993 0.01582 0.00808 -0.0047 0.3362 0.9794
5.750 0.8242 0.01603 0.00832 -0.0044 0.3269 0.9821
6.000 0.8529 0.01621 0.00848 -0.0049 0.3173 0.9838
6.250 0.8817 0.01636 0.00867 -0.0054 0.3071 0.9853
6.500 0.9092 0.01657 0.00888 -0.0057 0.2970 0.9872
6.750 0.9365 0.01681 0.00912 -0.0061 0.2864 0.9893
7.000 0.9632 0.01705 0.00939 -0.0063 0.2754 0.9915
7.250 0.9881 0.01735 0.00969 -0.0061 0.2651 0.9934
7.500 1.0151 0.01763 0.00996 -0.0065 0.2531 0.9950
7.750 1.0420 0.01791 0.01027 -0.0069 0.2408 0.9968
8.000 1.0689 0.01825 0.01062 -0.0073 0.2286 0.9988
8.250 1.0920 0.01866 0.01103 -0.0071 0.2171 1.0000
8.500 1.1073 0.01912 0.01147 -0.0053 0.2062 1.0000
8.750 1.1223 0.01957 0.01194 -0.0034 0.1953 1.0000
9.000 1.1356 0.02009 0.01246 -0.0013 0.1849 1.0000
9.250 1.1466 0.02068 0.01303 0.0011 0.1744 1.0000
9.500 1.1571 0.02124 0.01361 0.0036 0.1638 1.0000
9.750 1.1656 0.02185 0.01423 0.0064 0.1547 1.0000
10.000 1.1701 0.02256 0.01492 0.0097 0.1460 1.0000
10.250 1.1740 0.02321 0.01560 0.0131 0.1377 1.0000
10.500 1.1685 0.02391 0.01630 0.0181 0.1318 1.0000
10.750 1.1624 0.02464 0.01707 0.0229 0.1257 1.0000
11.250 1.1533 0.02664 0.01911 0.0305 0.1142 1.0000
11.500 1.1490 0.02792 0.02039 0.0337 0.1085 1.0000
11.750 1.1484 0.02915 0.02167 0.0363 0.1031 1.0000
12.000 1.1453 0.03067 0.02320 0.0387 0.0978 1.0000
12.250 1.1445 0.03219 0.02476 0.0408 0.0930 1.0000
12.500 1.1426 0.03389 0.02649 0.0426 0.0883 1.0000
12.750 1.1403 0.03576 0.02839 0.0442 0.0843 1.0000
13.000 1.1393 0.03763 0.03033 0.0455 0.0802 1.0000
13.250 1.1354 0.03987 0.03259 0.0466 0.0768 1.0000
13.500 1.1337 0.04202 0.03480 0.0475 0.0733 1.0000
13.750 1.1312 0.04434 0.03718 0.0483 0.0701 1.0000
14.000 1.1256 0.04708 0.03994 0.0487 0.0675 1.0000
14.250 1.1235 0.04955 0.04250 0.0491 0.0647 1.0000
14.500 1.1200 0.05227 0.04529 0.0493 0.0623 1.0000
14.750 1.1144 0.05539 0.04846 0.0492 0.0602 1.0000
15.000 1.1094 0.05853 0.05166 0.0490 0.0582 1.0000
15.250 1.1064 0.06153 0.05475 0.0487 0.0561 1.0000
15.500 1.1014 0.06489 0.05818 0.0482 0.0542 1.0000
15.750 1.0947 0.06853 0.06187 0.0474 0.0526 1.0000
16.000 1.0897 0.07204 0.06545 0.0467 0.0511 1.0000
16.250 1.0858 0.07550 0.06901 0.0459 0.0493 1.0000
16.500 1.0808 0.07915 0.07274 0.0450 0.0480 1.0000
16.750 1.0741 0.08313 0.07677 0.0439 0.0466 1.0000
17.000 1.0671 0.08719 0.08085 0.0426 0.0455 1.0000
17.250 1.0637 0.09081 0.08459 0.0416 0.0442 1.0000
17.500 1.0589 0.09469 0.08856 0.0404 0.0428 1.0000
17.750 1.0536 0.09870 0.09264 0.0390 0.0417 1.0000
18.000 1.0487 0.10269 0.09668 0.0376 0.0408 1.0000
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Polar data table (+)
Polar graphs
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