GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 767 AIRFOIL (goe767-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.48 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe767-il-1000000-n5.txt Download as CSV file: xf-goe767-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 767 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.2276 0.08666 0.08342 -0.0149 1.0000 0.0216
-17.750 -1.3012 0.07092 0.06744 -0.0246 1.0000 0.0215
-17.500 -1.3632 0.05657 0.05281 -0.0344 1.0000 0.0213
-17.250 -1.3905 0.04793 0.04398 -0.0410 1.0000 0.0214
-17.000 -1.4061 0.04199 0.03788 -0.0452 1.0000 0.0215
-16.750 -1.4146 0.03781 0.03356 -0.0475 1.0000 0.0216
-16.500 -1.4185 0.03474 0.03038 -0.0485 1.0000 0.0217
-16.250 -1.4203 0.03232 0.02786 -0.0485 1.0000 0.0218
-16.000 -1.4195 0.03045 0.02590 -0.0477 1.0000 0.0219
-15.750 -1.4164 0.02896 0.02433 -0.0463 1.0000 0.0220
-15.500 -1.4123 0.02770 0.02299 -0.0445 1.0000 0.0221
-15.250 -1.4059 0.02668 0.02191 -0.0424 1.0000 0.0223
-15.000 -1.3994 0.02576 0.02092 -0.0400 1.0000 0.0225
-14.750 -1.3927 0.02493 0.02001 -0.0372 1.0000 0.0226
-14.500 -1.3815 0.02422 0.01924 -0.0350 1.0000 0.0229
-14.250 -1.3670 0.02350 0.01846 -0.0333 1.0000 0.0231
-14.000 -1.3517 0.02278 0.01768 -0.0316 1.0000 0.0232
-13.750 -1.3351 0.02211 0.01695 -0.0301 1.0000 0.0234
-13.500 -1.3170 0.02150 0.01627 -0.0287 1.0000 0.0235
-13.250 -1.2984 0.02089 0.01560 -0.0273 1.0000 0.0237
-13.000 -1.2784 0.02037 0.01503 -0.0261 1.0000 0.0238
-12.750 -1.2604 0.01965 0.01426 -0.0247 1.0000 0.0241
-12.500 -1.2414 0.01896 0.01353 -0.0233 1.0000 0.0244
-12.250 -1.2212 0.01837 0.01290 -0.0221 1.0000 0.0247
-12.000 -1.2001 0.01783 0.01233 -0.0210 1.0000 0.0249
-11.750 -1.1784 0.01733 0.01179 -0.0199 1.0000 0.0251
-11.500 -1.1563 0.01686 0.01128 -0.0188 1.0000 0.0254
-11.250 -1.1337 0.01641 0.01080 -0.0178 1.0000 0.0256
-11.000 -1.1109 0.01598 0.01034 -0.0168 1.0000 0.0259
-10.750 -1.0878 0.01557 0.00990 -0.0158 1.0000 0.0262
-10.500 -1.0645 0.01518 0.00947 -0.0148 1.0000 0.0265
-10.250 -1.0409 0.01481 0.00908 -0.0139 1.0000 0.0268
-10.000 -1.0173 0.01445 0.00868 -0.0129 1.0000 0.0271
-9.750 -0.9934 0.01411 0.00831 -0.0120 1.0000 0.0273
-9.500 -0.9697 0.01376 0.00794 -0.0110 1.0000 0.0275
-9.250 -0.9465 0.01334 0.00750 -0.0099 1.0000 0.0279
-9.000 -0.9229 0.01297 0.00711 -0.0089 1.0000 0.0283
-8.750 -0.8991 0.01262 0.00676 -0.0079 1.0000 0.0288
-8.500 -0.8751 0.01231 0.00644 -0.0069 1.0000 0.0292
-8.250 -0.8510 0.01201 0.00613 -0.0059 1.0000 0.0296
-8.000 -0.8268 0.01173 0.00584 -0.0049 1.0000 0.0301
-7.750 -0.8007 0.01146 0.00556 -0.0043 0.9994 0.0306
-7.500 -0.7680 0.01118 0.00528 -0.0050 0.9912 0.0312
-7.250 -0.7305 0.01085 0.00495 -0.0069 0.9781 0.0322
-7.000 -0.6727 0.01049 0.00455 -0.0130 0.9210 0.0337
-6.750 -0.6485 0.01054 0.00429 -0.0117 0.8190 0.0347
-6.500 -0.6294 0.01087 0.00406 -0.0096 0.6420 0.0358
-6.250 -0.6042 0.01078 0.00382 -0.0088 0.5920 0.0380
-6.000 -0.5784 0.01064 0.00359 -0.0082 0.5561 0.0412
-5.750 -0.5526 0.01045 0.00335 -0.0075 0.5276 0.0479
-5.500 -0.5266 0.01024 0.00313 -0.0069 0.5034 0.0590
-5.250 -0.4999 0.01009 0.00298 -0.0064 0.4845 0.0675
-5.000 -0.4729 0.00999 0.00284 -0.0059 0.4686 0.0732
-4.750 -0.4456 0.00989 0.00272 -0.0055 0.4544 0.0783
-4.500 -0.4182 0.00980 0.00261 -0.0051 0.4416 0.0820
-4.250 -0.3908 0.00972 0.00250 -0.0046 0.4283 0.0855
-4.000 -0.3631 0.00966 0.00240 -0.0042 0.4149 0.0883
-3.750 -0.3356 0.00959 0.00230 -0.0038 0.4030 0.0913
-3.500 -0.3081 0.00952 0.00221 -0.0034 0.3915 0.0949
-3.250 -0.2803 0.00946 0.00212 -0.0030 0.3818 0.0976
-3.000 -0.2525 0.00943 0.00204 -0.0027 0.3720 0.0998
-2.750 -0.2247 0.00935 0.00196 -0.0023 0.3627 0.1031
-2.500 -0.1971 0.00929 0.00189 -0.0019 0.3534 0.1070
-2.250 -0.1692 0.00925 0.00182 -0.0015 0.3445 0.1103
-2.000 -0.1413 0.00922 0.00176 -0.0012 0.3354 0.1128
-1.750 -0.1136 0.00916 0.00170 -0.0008 0.3269 0.1180
-1.500 -0.0858 0.00913 0.00165 -0.0004 0.3178 0.1236
-1.250 -0.0580 0.00907 0.00161 -0.0001 0.3090 0.1307
-1.000 -0.0303 0.00905 0.00158 0.0003 0.2992 0.1385
-0.750 -0.0026 0.00900 0.00155 0.0006 0.2898 0.1497
-0.500 0.0251 0.00897 0.00152 0.0010 0.2811 0.1620
-0.250 0.0529 0.00893 0.00151 0.0013 0.2727 0.1749
0.000 0.0806 0.00893 0.00150 0.0017 0.2633 0.1881
0.250 0.1082 0.00890 0.00149 0.0021 0.2540 0.2039
0.500 0.1355 0.00884 0.00148 0.0024 0.2462 0.2290
0.750 0.1621 0.00869 0.00149 0.0029 0.2384 0.2847
1.000 0.1892 0.00862 0.00150 0.0033 0.2316 0.3253
1.250 0.2164 0.00853 0.00153 0.0037 0.2271 0.3632
1.500 0.2434 0.00844 0.00156 0.0041 0.2224 0.4089
1.750 0.2695 0.00829 0.00159 0.0047 0.2168 0.4792
2.000 0.2959 0.00812 0.00164 0.0052 0.2137 0.5450
2.250 0.3223 0.00801 0.00169 0.0058 0.2104 0.6020
2.500 0.3489 0.00794 0.00175 0.0063 0.2074 0.6513
2.750 0.3746 0.00785 0.00183 0.0071 0.2041 0.7104
3.000 0.3992 0.00773 0.00192 0.0081 0.2005 0.7755
3.250 0.4241 0.00761 0.00200 0.0092 0.1984 0.8327
3.500 0.4493 0.00754 0.00211 0.0102 0.1953 0.8902
3.750 0.4789 0.00757 0.00222 0.0103 0.1915 0.9281
4.000 0.5138 0.00769 0.00234 0.0092 0.1871 0.9529
4.250 0.5517 0.00782 0.00246 0.0073 0.1833 0.9671
4.500 0.5925 0.00795 0.00258 0.0049 0.1783 0.9781
4.750 0.6314 0.00813 0.00270 0.0028 0.1704 0.9861
5.000 0.6666 0.00827 0.00282 0.0015 0.1639 0.9909
5.250 0.6992 0.00846 0.00294 0.0006 0.1549 0.9939
5.500 0.7323 0.00867 0.00309 -0.0003 0.1438 0.9961
5.750 0.7648 0.00891 0.00326 -0.0012 0.1335 0.9981
6.000 0.7969 0.00916 0.00345 -0.0020 0.1246 0.9997
6.250 0.8228 0.00940 0.00365 -0.0015 0.1182 1.0000
6.500 0.8467 0.00960 0.00384 -0.0006 0.1140 1.0000
6.750 0.8704 0.00985 0.00405 0.0004 0.1094 1.0000
7.000 0.8946 0.01005 0.00425 0.0013 0.1062 1.0000
7.250 0.9188 0.01027 0.00446 0.0022 0.1031 1.0000
7.500 0.9428 0.01052 0.00469 0.0031 0.0997 1.0000
7.750 0.9670 0.01075 0.00492 0.0039 0.0969 1.0000
8.000 0.9916 0.01095 0.00513 0.0047 0.0952 1.0000
8.250 1.0161 0.01117 0.00535 0.0055 0.0928 1.0000
8.500 1.0403 0.01143 0.00560 0.0063 0.0902 1.0000
8.750 1.0643 0.01171 0.00587 0.0071 0.0876 1.0000
9.000 1.0889 0.01193 0.00611 0.0079 0.0861 1.0000
9.250 1.1133 0.01217 0.00636 0.0086 0.0840 1.0000
9.500 1.1373 0.01244 0.00664 0.0094 0.0816 1.0000
9.750 1.1610 0.01276 0.00695 0.0102 0.0790 1.0000
10.000 1.1851 0.01303 0.00723 0.0109 0.0770 1.0000
10.250 1.2091 0.01331 0.00754 0.0116 0.0744 1.0000
10.500 1.2323 0.01368 0.00789 0.0124 0.0710 1.0000
10.750 1.2557 0.01401 0.00822 0.0132 0.0681 1.0000
11.000 1.2786 0.01439 0.00860 0.0140 0.0644 1.0000
11.250 1.3011 0.01479 0.00901 0.0148 0.0611 1.0000
11.500 1.3232 0.01524 0.00944 0.0156 0.0571 1.0000
11.750 1.3448 0.01570 0.00991 0.0165 0.0536 1.0000
12.000 1.3653 0.01625 0.01045 0.0175 0.0497 1.0000
12.250 1.3860 0.01675 0.01096 0.0185 0.0468 1.0000
12.500 1.4055 0.01735 0.01156 0.0196 0.0440 1.0000
12.750 1.4252 0.01788 0.01212 0.0206 0.0420 1.0000
13.000 1.4435 0.01850 0.01276 0.0218 0.0400 1.0000
13.250 1.4613 0.01912 0.01341 0.0230 0.0385 1.0000
13.500 1.4787 0.01972 0.01405 0.0243 0.0374 1.0000
13.750 1.4948 0.02037 0.01474 0.0257 0.0364 1.0000
14.000 1.5088 0.02110 0.01551 0.0273 0.0355 1.0000
14.250 1.5199 0.02191 0.01635 0.0292 0.0347 1.0000
14.500 1.5278 0.02263 0.01714 0.0317 0.0342 1.0000
14.750 1.5342 0.02346 0.01804 0.0341 0.0338 1.0000
15.000 1.5391 0.02449 0.01913 0.0363 0.0333 1.0000
15.250 1.5420 0.02581 0.02053 0.0379 0.0328 1.0000
15.500 1.5428 0.02756 0.02236 0.0388 0.0324 1.0000
15.750 1.5415 0.02997 0.02487 0.0386 0.0320 1.0000
16.000 1.5371 0.03354 0.02856 0.0367 0.0317 1.0000
16.250 1.5286 0.03836 0.03352 0.0333 0.0314 1.0000
16.500 1.5140 0.04401 0.03931 0.0298 0.0312 1.0000
16.750 1.4915 0.05048 0.04593 0.0262 0.0311 1.0000
17.000 1.4616 0.05773 0.05332 0.0225 0.0309 1.0000
17.250 1.4302 0.06510 0.06083 0.0190 0.0310 1.0000
17.500 1.3956 0.07296 0.06883 0.0152 0.0309 1.0000
17.750 1.3647 0.08050 0.07649 0.0116 0.0308 1.0000
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