GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 692 AIRFOIL (goe692-il) Reynolds number: 500,000 Max Cl/Cd: 108.95 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe692-il-500000.txt Download as CSV file: xf-goe692-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 692 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7615 0.04335 0.03976 -0.1199 0.9913 0.0363
-13.500 -0.7632 0.03774 0.03384 -0.1279 0.9845 0.0365
-13.250 -0.7571 0.03448 0.03033 -0.1311 0.9783 0.0368
-13.000 -0.7450 0.03203 0.02765 -0.1327 0.9722 0.0372
-12.750 -0.7284 0.03010 0.02550 -0.1338 0.9671 0.0376
-12.500 -0.7124 0.02867 0.02385 -0.1338 0.9595 0.0379
-12.250 -0.6959 0.02673 0.02172 -0.1340 0.9541 0.0384
-12.000 -0.6800 0.02534 0.02025 -0.1332 0.9459 0.0388
-11.750 -0.6576 0.02429 0.01913 -0.1333 0.9409 0.0393
-11.500 -0.6390 0.02347 0.01824 -0.1324 0.9327 0.0397
-11.250 -0.6172 0.02262 0.01730 -0.1320 0.9267 0.0403
-11.000 -0.5966 0.02185 0.01642 -0.1313 0.9198 0.0408
-10.750 -0.5751 0.02107 0.01552 -0.1306 0.9131 0.0414
-10.500 -0.5523 0.02033 0.01463 -0.1302 0.9078 0.0420
-10.250 -0.5302 0.01969 0.01386 -0.1295 0.9011 0.0426
-10.000 -0.5064 0.01913 0.01316 -0.1290 0.8955 0.0431
-9.750 -0.4846 0.01816 0.01215 -0.1285 0.8902 0.0441
-9.500 -0.4611 0.01765 0.01161 -0.1280 0.8840 0.0449
-9.250 -0.4363 0.01717 0.01107 -0.1276 0.8785 0.0457
-9.000 -0.4109 0.01672 0.01053 -0.1273 0.8736 0.0467
-8.750 -0.3861 0.01628 0.01001 -0.1269 0.8681 0.0477
-8.500 -0.3603 0.01590 0.00951 -0.1266 0.8628 0.0486
-8.250 -0.3357 0.01526 0.00885 -0.1262 0.8580 0.0500
-8.000 -0.3101 0.01492 0.00849 -0.1259 0.8527 0.0514
-7.750 -0.2838 0.01461 0.00814 -0.1257 0.8471 0.0531
-7.500 -0.2567 0.01434 0.00775 -0.1255 0.8420 0.0549
-7.250 -0.2309 0.01392 0.00735 -0.1252 0.8371 0.0572
-7.000 -0.2042 0.01368 0.00709 -0.1250 0.8316 0.0597
-6.750 -0.1775 0.01336 0.00670 -0.1248 0.8263 0.0625
-6.500 -0.1500 0.01313 0.00644 -0.1248 0.8213 0.0657
-6.250 -0.1227 0.01297 0.00623 -0.1246 0.8155 0.0691
-6.000 -0.0965 0.01260 0.00589 -0.1244 0.8097 0.0731
-5.750 -0.0681 0.01249 0.00568 -0.1244 0.8047 0.0771
-5.500 -0.0418 0.01216 0.00539 -0.1242 0.7988 0.0814
-5.250 -0.0143 0.01200 0.00520 -0.1241 0.7927 0.0854
-5.000 0.0133 0.01177 0.00491 -0.1240 0.7872 0.0895
-4.750 0.0404 0.01158 0.00474 -0.1239 0.7811 0.0937
-4.500 0.0682 0.01145 0.00456 -0.1238 0.7746 0.0975
-4.250 0.0958 0.01123 0.00433 -0.1238 0.7688 0.1028
-4.000 0.1232 0.01110 0.00420 -0.1236 0.7621 0.1078
-3.750 0.1506 0.01091 0.00402 -0.1235 0.7553 0.1137
-3.500 0.1788 0.01082 0.00389 -0.1235 0.7492 0.1206
-3.250 0.2060 0.01066 0.00379 -0.1234 0.7419 0.1295
-3.000 0.2339 0.01056 0.00367 -0.1233 0.7355 0.1401
-2.750 0.2619 0.01050 0.00360 -0.1233 0.7291 0.1509
-2.500 0.2894 0.01036 0.00352 -0.1232 0.7223 0.1631
-2.250 0.3175 0.01030 0.00342 -0.1233 0.7164 0.1738
-2.000 0.3453 0.01025 0.00338 -0.1232 0.7098 0.1836
-1.750 0.3729 0.01015 0.00331 -0.1232 0.7035 0.1941
-1.500 0.4012 0.01015 0.00324 -0.1232 0.6979 0.2032
-1.250 0.4286 0.01005 0.00321 -0.1231 0.6916 0.2146
-1.000 0.4563 0.01000 0.00316 -0.1231 0.6857 0.2265
-0.750 0.4844 0.00998 0.00312 -0.1232 0.6803 0.2402
-0.250 0.5391 0.00980 0.00310 -0.1231 0.6688 0.2852
0.000 0.5666 0.00970 0.00310 -0.1231 0.6637 0.3329
0.250 0.5923 0.00939 0.00315 -0.1229 0.6581 0.4343
0.500 0.6160 0.00892 0.00322 -0.1223 0.6526 0.6086
0.750 0.6371 0.00852 0.00335 -0.1207 0.6477 0.7890
1.000 0.6581 0.00839 0.00353 -0.1185 0.6427 0.9045
1.250 0.6925 0.00846 0.00363 -0.1196 0.6370 0.9570
1.500 0.7316 0.00861 0.00369 -0.1219 0.6316 0.9793
1.750 0.7767 0.00873 0.00378 -0.1256 0.6258 0.9907
2.000 0.8236 0.00883 0.00383 -0.1298 0.6182 0.9981
2.250 0.8529 0.00896 0.00386 -0.1303 0.6106 1.0000
2.500 0.8738 0.00900 0.00390 -0.1289 0.6030 1.0000
2.750 0.8958 0.00911 0.00393 -0.1277 0.5962 1.0000
3.000 0.9178 0.00919 0.00400 -0.1266 0.5895 1.0000
3.250 0.9398 0.00928 0.00406 -0.1254 0.5825 1.0000
3.500 0.9624 0.00942 0.00413 -0.1243 0.5762 1.0000
3.750 0.9847 0.00949 0.00422 -0.1232 0.5688 1.0000
4.000 1.0070 0.00962 0.00429 -0.1221 0.5612 1.0000
4.250 1.0298 0.00972 0.00439 -0.1212 0.5532 1.0000
4.500 1.0523 0.00986 0.00448 -0.1201 0.5449 1.0000
4.750 1.0753 0.00999 0.00460 -0.1192 0.5367 1.0000
5.000 1.0974 0.01015 0.00472 -0.1181 0.5277 1.0000
5.250 1.1198 0.01029 0.00486 -0.1171 0.5183 1.0000
5.750 1.1625 0.01067 0.00517 -0.1147 0.4980 1.0000
6.000 1.1830 0.01089 0.00536 -0.1134 0.4884 1.0000
6.250 1.2030 0.01112 0.00555 -0.1119 0.4779 1.0000
6.500 1.2219 0.01135 0.00577 -0.1103 0.4677 1.0000
6.750 1.2379 0.01166 0.00602 -0.1081 0.4573 1.0000
7.000 1.2563 0.01193 0.00628 -0.1065 0.4464 1.0000
7.250 1.2737 0.01226 0.00659 -0.1046 0.4359 1.0000
7.500 1.2897 0.01266 0.00693 -0.1026 0.4247 1.0000
7.750 1.3079 0.01301 0.00728 -0.1011 0.4133 1.0000
8.000 1.3244 0.01344 0.00768 -0.0993 0.4020 1.0000
8.250 1.3390 0.01395 0.00814 -0.0972 0.3898 1.0000
8.500 1.3551 0.01443 0.00860 -0.0955 0.3766 1.0000
8.750 1.3701 0.01499 0.00913 -0.0936 0.3630 1.0000
9.000 1.3840 0.01561 0.00971 -0.0917 0.3490 1.0000
9.250 1.3969 0.01631 0.01036 -0.0897 0.3347 1.0000
9.500 1.4087 0.01710 0.01110 -0.0876 0.3201 1.0000
9.750 1.4197 0.01796 0.01191 -0.0855 0.3053 1.0000
10.000 1.4297 0.01892 0.01281 -0.0833 0.2907 1.0000
10.250 1.4404 0.01989 0.01374 -0.0814 0.2769 1.0000
10.500 1.4509 0.02090 0.01473 -0.0795 0.2642 1.0000
10.750 1.4606 0.02200 0.01579 -0.0776 0.2525 1.0000
11.000 1.4685 0.02324 0.01699 -0.0756 0.2412 1.0000
11.250 1.4770 0.02448 0.01820 -0.0738 0.2299 1.0000
11.500 1.4860 0.02571 0.01942 -0.0721 0.2194 1.0000
11.750 1.4925 0.02715 0.02082 -0.0702 0.2095 1.0000
12.000 1.5005 0.02852 0.02218 -0.0686 0.2000 1.0000
12.250 1.5085 0.02993 0.02359 -0.0671 0.1916 1.0000
12.500 1.5141 0.03155 0.02519 -0.0654 0.1834 1.0000
12.750 1.5231 0.03295 0.02661 -0.0641 0.1761 1.0000
13.000 1.5283 0.03470 0.02834 -0.0626 0.1692 1.0000
13.250 1.5366 0.03623 0.02990 -0.0614 0.1636 1.0000
13.500 1.5440 0.03785 0.03154 -0.0603 0.1585 1.0000
13.750 1.5478 0.03983 0.03352 -0.0589 0.1539 1.0000
14.000 1.5570 0.04136 0.03511 -0.0580 0.1503 1.0000
14.250 1.5648 0.04307 0.03686 -0.0571 0.1464 1.0000
14.500 1.5693 0.04510 0.03890 -0.0561 0.1427 1.0000
14.750 1.5727 0.04724 0.04106 -0.0550 0.1392 1.0000
15.000 1.5825 0.04883 0.04274 -0.0544 0.1363 1.0000
15.250 1.5892 0.05074 0.04469 -0.0537 0.1331 1.0000
15.500 1.5931 0.05295 0.04693 -0.0530 0.1301 1.0000
15.750 1.5947 0.05541 0.04942 -0.0521 0.1273 1.0000
16.000 1.6025 0.05726 0.05134 -0.0516 0.1251 1.0000
16.250 1.6096 0.05920 0.05338 -0.0512 0.1225 1.0000
16.500 1.6143 0.06141 0.05563 -0.0507 0.1196 1.0000
16.750 1.6152 0.06407 0.05833 -0.0502 0.1167 1.0000
17.000 1.6168 0.06666 0.06096 -0.0497 0.1138 1.0000
17.250 1.6243 0.06866 0.06306 -0.0495 0.1108 1.0000
17.500 1.6274 0.07112 0.06559 -0.0492 0.1074 1.0000
17.750 1.6256 0.07420 0.06869 -0.0489 0.1039 1.0000
18.000 1.6297 0.07662 0.07120 -0.0488 0.1004 1.0000
18.250 1.6318 0.07931 0.07394 -0.0488 0.0954 1.0000
18.500 1.6300 0.08251 0.07718 -0.0488 0.0900 1.0000
18.750 1.6268 0.08592 0.08060 -0.0489 0.0807 1.0000
19.000 1.6146 0.09048 0.08510 -0.0491 0.0676 1.0000
19.250 1.5958 0.09597 0.09055 -0.0496 0.0573 1.0000
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Polar data table (+)
Polar graphs
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