GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 500,000 Max Cl/Cd: 77 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe766-il-500000-n5.txt Download as CSV file: xf-goe766-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0920 0.08106 0.07757 -0.0262 1.0000 0.0218
-16.750 -1.1339 0.06954 0.06581 -0.0338 1.0000 0.0217
-16.500 -1.1571 0.06171 0.05780 -0.0392 1.0000 0.0219
-16.250 -1.1722 0.05563 0.05155 -0.0432 1.0000 0.0220
-16.000 -1.1851 0.05040 0.04617 -0.0463 1.0000 0.0221
-15.750 -1.1917 0.04645 0.04207 -0.0482 1.0000 0.0223
-15.500 -1.1968 0.04302 0.03850 -0.0495 1.0000 0.0226
-15.250 -1.2000 0.04010 0.03543 -0.0501 1.0000 0.0228
-15.000 -1.2015 0.03759 0.03278 -0.0500 1.0000 0.0231
-14.750 -1.2016 0.03542 0.03047 -0.0495 1.0000 0.0233
-14.500 -1.1992 0.03365 0.02855 -0.0485 1.0000 0.0236
-14.250 -1.1957 0.03208 0.02682 -0.0471 1.0000 0.0238
-14.000 -1.1923 0.03066 0.02533 -0.0454 1.0000 0.0241
-13.750 -1.1867 0.02949 0.02411 -0.0435 1.0000 0.0244
-13.500 -1.1790 0.02853 0.02309 -0.0415 1.0000 0.0247
-13.250 -1.1702 0.02770 0.02220 -0.0393 1.0000 0.0250
-13.000 -1.1611 0.02692 0.02136 -0.0369 1.0000 0.0253
-12.750 -1.1517 0.02618 0.02055 -0.0344 1.0000 0.0256
-12.500 -1.1412 0.02545 0.01974 -0.0319 1.0000 0.0260
-12.250 -1.1276 0.02471 0.01891 -0.0299 1.0000 0.0264
-12.000 -1.1126 0.02400 0.01811 -0.0281 1.0000 0.0268
-11.750 -1.0965 0.02334 0.01735 -0.0264 1.0000 0.0273
-11.500 -1.0797 0.02269 0.01659 -0.0247 1.0000 0.0276
-11.250 -1.0632 0.02196 0.01578 -0.0230 1.0000 0.0280
-11.000 -1.0470 0.02121 0.01501 -0.0212 1.0000 0.0284
-10.750 -1.0288 0.02064 0.01441 -0.0197 1.0000 0.0288
-10.500 -1.0098 0.02014 0.01387 -0.0182 1.0000 0.0293
-10.250 -0.9906 0.01962 0.01331 -0.0167 1.0000 0.0298
-10.000 -0.9713 0.01909 0.01274 -0.0152 1.0000 0.0302
-9.750 -0.9519 0.01856 0.01216 -0.0137 1.0000 0.0307
-9.500 -0.9319 0.01809 0.01163 -0.0122 1.0000 0.0312
-9.250 -0.9117 0.01764 0.01112 -0.0108 1.0000 0.0317
-9.000 -0.8913 0.01720 0.01061 -0.0093 1.0000 0.0321
-8.750 -0.8720 0.01664 0.01003 -0.0077 1.0000 0.0326
-8.500 -0.8528 0.01612 0.00949 -0.0061 1.0000 0.0331
-8.250 -0.8327 0.01568 0.00905 -0.0045 1.0000 0.0336
-8.000 -0.8123 0.01529 0.00864 -0.0030 1.0000 0.0341
-7.750 -0.7918 0.01493 0.00826 -0.0015 1.0000 0.0348
-7.500 -0.7713 0.01459 0.00790 0.0000 1.0000 0.0355
-7.250 -0.7410 0.01420 0.00749 -0.0006 0.9975 0.0363
-7.000 -0.7083 0.01381 0.00706 -0.0016 0.9924 0.0370
-6.750 -0.6773 0.01338 0.00662 -0.0022 0.9865 0.0377
-6.500 -0.6460 0.01295 0.00620 -0.0029 0.9800 0.0388
-6.250 -0.6130 0.01259 0.00585 -0.0040 0.9722 0.0398
-6.000 -0.5786 0.01226 0.00551 -0.0053 0.9628 0.0411
-5.750 -0.5422 0.01195 0.00518 -0.0069 0.9519 0.0426
-5.500 -0.5032 0.01159 0.00481 -0.0092 0.9359 0.0443
-5.250 -0.4636 0.01125 0.00445 -0.0115 0.9109 0.0464
-5.000 -0.4316 0.01104 0.00415 -0.0121 0.8753 0.0485
-4.750 -0.4056 0.01094 0.00389 -0.0113 0.8264 0.0505
-4.500 -0.3836 0.01090 0.00363 -0.0098 0.7569 0.0534
-4.250 -0.3617 0.01094 0.00342 -0.0083 0.6935 0.0566
-4.000 -0.3389 0.01094 0.00323 -0.0070 0.6399 0.0611
-3.750 -0.3149 0.01089 0.00305 -0.0061 0.5989 0.0669
-3.500 -0.2904 0.01079 0.00287 -0.0052 0.5681 0.0764
-3.250 -0.2657 0.01065 0.00272 -0.0045 0.5432 0.0924
-3.000 -0.2407 0.01051 0.00260 -0.0038 0.5229 0.1137
-2.750 -0.2150 0.01040 0.00250 -0.0032 0.5063 0.1310
-2.500 -0.1890 0.01031 0.00240 -0.0026 0.4920 0.1454
-2.250 -0.1630 0.01023 0.00230 -0.0021 0.4781 0.1585
-2.000 -0.1371 0.01014 0.00220 -0.0015 0.4649 0.1730
-1.750 -0.1112 0.01001 0.00211 -0.0009 0.4531 0.1942
-1.500 -0.0863 0.00978 0.00202 -0.0003 0.4433 0.2355
-1.250 -0.0628 0.00943 0.00192 0.0006 0.4337 0.3133
-1.000 -0.0394 0.00907 0.00185 0.0015 0.4253 0.4000
-0.750 -0.0165 0.00874 0.00178 0.0026 0.4163 0.4771
-0.500 0.0054 0.00841 0.00176 0.0039 0.4079 0.5709
-0.250 0.0292 0.00825 0.00176 0.0050 0.3980 0.6286
0.000 0.0545 0.00818 0.00177 0.0058 0.3892 0.6636
0.250 0.0801 0.00814 0.00177 0.0065 0.3801 0.6910
0.500 0.1055 0.00808 0.00179 0.0073 0.3718 0.7212
0.750 0.1301 0.00801 0.00183 0.0084 0.3625 0.7619
1.000 0.1553 0.00795 0.00188 0.0093 0.3537 0.7989
1.250 0.1817 0.00798 0.00193 0.0099 0.3440 0.8234
1.500 0.2090 0.00799 0.00199 0.0103 0.3336 0.8472
1.750 0.2370 0.00805 0.00206 0.0106 0.3229 0.8715
2.000 0.2672 0.00814 0.00215 0.0104 0.3120 0.8935
2.250 0.3016 0.00825 0.00226 0.0093 0.3023 0.9137
2.500 0.3381 0.00841 0.00238 0.0077 0.2927 0.9297
2.750 0.3741 0.00857 0.00251 0.0062 0.2830 0.9429
3.000 0.4111 0.00874 0.00264 0.0044 0.2747 0.9500
3.250 0.4432 0.00890 0.00276 0.0037 0.2667 0.9581
3.500 0.4791 0.00909 0.00290 0.0021 0.2577 0.9626
3.750 0.5101 0.00926 0.00302 0.0016 0.2497 0.9686
4.000 0.5422 0.00943 0.00316 0.0008 0.2437 0.9724
4.250 0.5759 0.00958 0.00329 -0.0004 0.2364 0.9755
4.500 0.6074 0.00978 0.00343 -0.0011 0.2276 0.9795
4.750 0.6383 0.00993 0.00357 -0.0017 0.2203 0.9834
5.000 0.6720 0.01012 0.00372 -0.0029 0.2136 0.9858
5.250 0.7052 0.01026 0.00387 -0.0040 0.2078 0.9887
5.500 0.7369 0.01044 0.00403 -0.0048 0.2008 0.9917
5.750 0.7691 0.01062 0.00420 -0.0058 0.1937 0.9943
6.000 0.8021 0.01081 0.00436 -0.0069 0.1848 0.9966
6.250 0.8351 0.01100 0.00454 -0.0080 0.1750 0.9988
6.500 0.8640 0.01124 0.00473 -0.0084 0.1639 1.0000
6.750 0.8855 0.01150 0.00494 -0.0072 0.1516 1.0000
7.000 0.9064 0.01183 0.00520 -0.0059 0.1369 1.0000
7.250 0.9269 0.01220 0.00550 -0.0046 0.1232 1.0000
7.500 0.9473 0.01258 0.00583 -0.0032 0.1117 1.0000
7.750 0.9676 0.01297 0.00618 -0.0019 0.1024 1.0000
8.000 0.9881 0.01336 0.00654 -0.0006 0.0939 1.0000
8.250 1.0087 0.01373 0.00690 0.0007 0.0871 1.0000
8.500 1.0286 0.01416 0.00730 0.0021 0.0806 1.0000
8.750 1.0491 0.01454 0.00768 0.0034 0.0752 1.0000
9.000 1.0687 0.01499 0.00812 0.0048 0.0703 1.0000
9.250 1.0891 0.01537 0.00852 0.0060 0.0669 1.0000
9.500 1.1087 0.01581 0.00897 0.0074 0.0637 1.0000
9.750 1.1277 0.01629 0.00946 0.0088 0.0609 1.0000
10.000 1.1476 0.01669 0.00990 0.0101 0.0590 1.0000
10.250 1.1666 0.01714 0.01039 0.0115 0.0570 1.0000
10.500 1.1847 0.01765 0.01092 0.0130 0.0550 1.0000
10.750 1.2012 0.01825 0.01153 0.0147 0.0530 1.0000
11.000 1.2193 0.01870 0.01205 0.0161 0.0519 1.0000
11.250 1.2365 0.01920 0.01260 0.0177 0.0505 1.0000
11.500 1.2525 0.01975 0.01320 0.0194 0.0493 1.0000
11.750 1.2671 0.02036 0.01385 0.0212 0.0482 1.0000
12.000 1.2798 0.02104 0.01457 0.0232 0.0471 1.0000
12.250 1.2883 0.02183 0.01540 0.0258 0.0459 1.0000
12.500 1.2969 0.02246 0.01610 0.0285 0.0453 1.0000
12.750 1.3057 0.02316 0.01687 0.0309 0.0445 1.0000
13.000 1.3134 0.02399 0.01778 0.0332 0.0438 1.0000
13.250 1.3206 0.02495 0.01882 0.0351 0.0430 1.0000
13.500 1.3267 0.02609 0.02003 0.0368 0.0422 1.0000
13.750 1.3314 0.02748 0.02148 0.0380 0.0415 1.0000
14.000 1.3338 0.02924 0.02332 0.0389 0.0407 1.0000
14.250 1.3335 0.03154 0.02570 0.0390 0.0401 1.0000
14.500 1.3337 0.03414 0.02839 0.0385 0.0395 1.0000
14.750 1.3364 0.03673 0.03110 0.0376 0.0389 1.0000
15.000 1.3369 0.03974 0.03423 0.0364 0.0383 1.0000
15.250 1.3357 0.04307 0.03767 0.0350 0.0377 1.0000
15.500 1.3310 0.04686 0.04156 0.0334 0.0373 1.0000
15.750 1.3249 0.05084 0.04565 0.0316 0.0367 1.0000
16.000 1.3164 0.05510 0.05000 0.0299 0.0363 1.0000
16.250 1.3061 0.05960 0.05460 0.0280 0.0359 1.0000
16.500 1.2944 0.06426 0.05934 0.0261 0.0354 1.0000
16.750 1.2820 0.06903 0.06421 0.0241 0.0353 1.0000
17.000 1.2692 0.07398 0.06923 0.0220 0.0349 1.0000
17.250 1.2562 0.07916 0.07447 0.0197 0.0344 1.0000
17.500 1.2471 0.08380 0.07920 0.0177 0.0341 1.0000
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