Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 (goe765-il) Xfoil prediction polar at RE=500,000 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: 500,000 Max Cl/Cd: 80.41 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe765-il-500000.txt Download as CSV file: xf-goe765-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9929 0.08411 0.08074 -0.0332 1.0000 0.0256
-17.000 -1.0325 0.07299 0.06936 -0.0410 1.0000 0.0256
-16.750 -1.0570 0.06527 0.06144 -0.0462 1.0000 0.0256
-16.500 -1.0756 0.05922 0.05520 -0.0497 1.0000 0.0257
-16.250 -1.0869 0.05480 0.05064 -0.0518 1.0000 0.0260
-16.000 -1.0960 0.05111 0.04682 -0.0529 1.0000 0.0262
-15.750 -1.1067 0.04754 0.04308 -0.0532 1.0000 0.0264
-15.500 -1.1144 0.04462 0.04001 -0.0529 1.0000 0.0267
-15.250 -1.1210 0.04200 0.03723 -0.0519 1.0000 0.0269
-15.000 -1.1257 0.03974 0.03480 -0.0504 1.0000 0.0272
-14.750 -1.1286 0.03777 0.03266 -0.0486 1.0000 0.0274
-14.500 -1.1295 0.03599 0.03073 -0.0465 1.0000 0.0276
-14.250 -1.1303 0.03414 0.02871 -0.0442 1.0000 0.0280
-14.000 -1.1259 0.03243 0.02695 -0.0422 1.0000 0.0283
-13.750 -1.1186 0.03121 0.02569 -0.0402 1.0000 0.0287
-13.500 -1.1105 0.03012 0.02455 -0.0381 1.0000 0.0290
-13.250 -1.1015 0.02915 0.02352 -0.0360 1.0000 0.0295
-13.000 -1.0918 0.02832 0.02263 -0.0338 1.0000 0.0300
-12.750 -1.0817 0.02746 0.02167 -0.0315 1.0000 0.0306
-12.500 -1.0708 0.02657 0.02067 -0.0292 1.0000 0.0311
-12.250 -1.0592 0.02581 0.01978 -0.0269 1.0000 0.0316
-12.000 -1.0467 0.02485 0.01871 -0.0248 1.0000 0.0321
-11.750 -1.0332 0.02366 0.01750 -0.0229 1.0000 0.0327
-11.500 -1.0186 0.02296 0.01680 -0.0209 1.0000 0.0333
-11.250 -1.0032 0.02229 0.01610 -0.0190 1.0000 0.0339
-11.000 -0.9873 0.02171 0.01548 -0.0171 1.0000 0.0347
-10.750 -0.9709 0.02114 0.01484 -0.0152 1.0000 0.0356
-10.500 -0.9536 0.02064 0.01425 -0.0134 1.0000 0.0363
-10.250 -0.9376 0.01972 0.01332 -0.0115 1.0000 0.0373
-10.000 -0.9208 0.01913 0.01275 -0.0097 1.0000 0.0381
-9.750 -0.9033 0.01865 0.01227 -0.0079 1.0000 0.0391
-9.250 -0.8253 0.01715 0.01064 -0.0134 0.9464 0.0424
-9.000 -0.7924 0.01657 0.01001 -0.0147 0.9203 0.0442
-8.750 -0.7711 0.01627 0.00962 -0.0133 0.8979 0.0460
-8.500 -0.7512 0.01602 0.00923 -0.0116 0.8805 0.0474
-8.250 -0.7346 0.01544 0.00863 -0.0095 0.8659 0.0494
-8.000 -0.7150 0.01516 0.00829 -0.0078 0.8534 0.0513
-7.750 -0.6940 0.01492 0.00796 -0.0063 0.8415 0.0535
-7.500 -0.6750 0.01447 0.00749 -0.0045 0.8305 0.0561
-7.250 -0.6538 0.01423 0.00719 -0.0031 0.8206 0.0589
-7.000 -0.6318 0.01395 0.00686 -0.0018 0.8103 0.0619
-6.750 -0.6110 0.01360 0.00650 -0.0003 0.8012 0.0655
-6.500 -0.5878 0.01338 0.00623 0.0007 0.7914 0.0691
-6.250 -0.5663 0.01303 0.00587 0.0021 0.7829 0.0738
-6.000 -0.5423 0.01283 0.00564 0.0030 0.7735 0.0786
-5.500 -0.4966 0.01225 0.00506 0.0052 0.7561 0.0915
-5.250 -0.4734 0.01202 0.00482 0.0063 0.7476 0.0993
-5.000 -0.4500 0.01174 0.00458 0.0073 0.7386 0.1088
-4.750 -0.4267 0.01151 0.00435 0.0083 0.7301 0.1197
-4.500 -0.4029 0.01128 0.00415 0.0092 0.7217 0.1324
-4.250 -0.3793 0.01105 0.00396 0.0102 0.7131 0.1475
-4.000 -0.3558 0.01082 0.00378 0.0112 0.7051 0.1659
-3.750 -0.3322 0.01058 0.00361 0.0121 0.6966 0.1872
-3.500 -0.3088 0.01038 0.00346 0.0131 0.6889 0.2115
-3.250 -0.2855 0.01013 0.00332 0.0141 0.6805 0.2395
-3.000 -0.2628 0.00991 0.00318 0.0153 0.6728 0.2714
-2.750 -0.2401 0.00964 0.00306 0.0164 0.6643 0.3078
-2.500 -0.2187 0.00937 0.00291 0.0178 0.6561 0.3512
-2.250 -0.2004 0.00895 0.00276 0.0197 0.6481 0.4175
-2.000 -0.1919 0.00827 0.00257 0.0237 0.6401 0.5398
-1.750 -0.1929 0.00747 0.00243 0.0300 0.6331 0.7026
-1.500 -0.1558 0.00717 0.00261 0.0287 0.6239 0.8248
-1.250 -0.1091 0.00735 0.00280 0.0252 0.6149 0.8634
-1.000 -0.0716 0.00754 0.00297 0.0236 0.6051 0.8809
-0.750 -0.0491 0.00774 0.00309 0.0252 0.5969 0.8952
-0.500 0.0003 0.00809 0.00340 0.0212 0.5859 0.9007
-0.250 0.0174 0.00827 0.00352 0.0239 0.5775 0.9115
0.000 0.0653 0.00865 0.00383 0.0201 0.5663 0.9137
0.250 0.1118 0.00909 0.00420 0.0167 0.5554 0.9161
0.750 0.1820 0.00977 0.00476 0.0146 0.5341 0.9282
1.000 0.2285 0.01013 0.00504 0.0111 0.5224 0.9300
1.250 0.2714 0.01043 0.00525 0.0082 0.5101 0.9324
1.500 0.3105 0.01065 0.00544 0.0061 0.4985 0.9360
1.750 0.3330 0.01084 0.00557 0.0074 0.4882 0.9431
2.000 0.3777 0.01104 0.00570 0.0041 0.4754 0.9447
2.250 0.4192 0.01119 0.00581 0.0014 0.4631 0.9470
2.500 0.4539 0.01131 0.00588 0.0000 0.4521 0.9498
2.750 0.4805 0.01142 0.00593 0.0002 0.4409 0.9534
3.000 0.5021 0.01151 0.00600 0.0015 0.4311 0.9575
3.250 0.5363 0.01156 0.00599 0.0000 0.4202 0.9586
3.500 0.5701 0.01159 0.00599 -0.0013 0.4093 0.9599
3.750 0.6020 0.01165 0.00602 -0.0022 0.3990 0.9615
4.000 0.6323 0.01174 0.00607 -0.0029 0.3890 0.9636
4.250 0.6604 0.01184 0.00615 -0.0030 0.3797 0.9664
4.500 0.6796 0.01205 0.00633 -0.0014 0.3709 0.9705
4.750 0.7135 0.01205 0.00632 -0.0028 0.3609 0.9715
5.000 0.7463 0.01214 0.00636 -0.0040 0.3511 0.9728
5.250 0.7784 0.01218 0.00641 -0.0051 0.3416 0.9743
5.500 0.8079 0.01230 0.00650 -0.0057 0.3322 0.9762
5.750 0.8362 0.01242 0.00661 -0.0060 0.3220 0.9785
6.000 0.8599 0.01264 0.00683 -0.0053 0.3135 0.9818
6.250 0.8898 0.01274 0.00690 -0.0060 0.3030 0.9834
6.500 0.9217 0.01278 0.00695 -0.0071 0.2928 0.9845
6.750 0.9520 0.01292 0.00705 -0.0080 0.2821 0.9860
7.000 0.9821 0.01306 0.00717 -0.0088 0.2709 0.9878
7.250 1.0114 0.01321 0.00733 -0.0094 0.2600 0.9899
7.500 1.0381 0.01345 0.00754 -0.0095 0.2490 0.9920
7.750 1.0650 0.01371 0.00776 -0.0098 0.2367 0.9938
8.000 1.0953 0.01386 0.00791 -0.0107 0.2243 0.9952
8.250 1.1253 0.01408 0.00811 -0.0117 0.2117 0.9969
8.500 1.1547 0.01436 0.00836 -0.0126 0.1987 0.9988
8.750 1.1817 0.01471 0.00865 -0.0130 0.1852 1.0000
9.000 1.1987 0.01514 0.00904 -0.0114 0.1739 1.0000
9.250 1.2152 0.01557 0.00944 -0.0098 0.1622 1.0000
9.500 1.2309 0.01602 0.00987 -0.0080 0.1507 1.0000
9.750 1.2453 0.01652 0.01035 -0.0061 0.1399 1.0000
10.000 1.2579 0.01708 0.01087 -0.0039 0.1296 1.0000
10.250 1.2682 0.01770 0.01145 -0.0013 0.1196 1.0000
10.500 1.2778 0.01828 0.01201 0.0013 0.1107 1.0000
10.750 1.2848 0.01889 0.01262 0.0044 0.1029 1.0000
11.000 1.2868 0.01960 0.01331 0.0082 0.0959 1.0000
11.250 1.2830 0.02017 0.01390 0.0132 0.0906 1.0000
11.500 1.2697 0.02089 0.01464 0.0194 0.0870 1.0000
11.750 1.2634 0.02173 0.01551 0.0239 0.0829 1.0000
12.000 1.2579 0.02278 0.01659 0.0278 0.0789 1.0000
12.250 1.2533 0.02400 0.01783 0.0312 0.0749 1.0000
12.500 1.2519 0.02521 0.01907 0.0340 0.0711 1.0000
12.750 1.2466 0.02680 0.02067 0.0367 0.0676 1.0000
13.000 1.2471 0.02818 0.02211 0.0389 0.0645 1.0000
13.250 1.2454 0.02983 0.02378 0.0408 0.0617 1.0000
13.500 1.2389 0.03197 0.02594 0.0427 0.0591 1.0000
13.750 1.2411 0.03356 0.02761 0.0440 0.0565 1.0000
14.000 1.2384 0.03565 0.02974 0.0453 0.0544 1.0000
14.250 1.2312 0.03826 0.03237 0.0464 0.0524 1.0000
14.500 1.2304 0.04040 0.03459 0.0472 0.0505 1.0000
14.750 1.2285 0.04274 0.03699 0.0478 0.0485 1.0000
15.000 1.2225 0.04559 0.03989 0.0482 0.0471 1.0000
15.250 1.2124 0.04901 0.04335 0.0483 0.0457 1.0000
15.500 1.2113 0.05161 0.04604 0.0484 0.0444 1.0000
15.750 1.2086 0.05448 0.04899 0.0483 0.0430 1.0000
16.000 1.2032 0.05773 0.05231 0.0480 0.0418 1.0000
16.250 1.1944 0.06150 0.05611 0.0474 0.0406 1.0000
16.500 1.1843 0.06547 0.06013 0.0467 0.0399 1.0000
16.750 1.1817 0.06865 0.06341 0.0461 0.0388 1.0000
17.000 1.1779 0.07204 0.06688 0.0454 0.0378 1.0000
17.250 1.1728 0.07566 0.07057 0.0445 0.0368 1.0000
17.500 1.1657 0.07958 0.07453 0.0435 0.0360 1.0000
17.750 1.1571 0.08372 0.07871 0.0424 0.0352 1.0000
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Polar data table (+)
Polar graphs
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