GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.23 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe711-il-1000000-n5.txt Download as CSV file: xf-goe711-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1165 0.08981 0.08793 -0.0917 0.9259 0.0104
-9.750 -0.1104 0.08695 0.08507 -0.0931 0.9201 0.0107
-9.250 -0.1330 0.07405 0.07215 -0.1002 0.9064 0.0125
-9.000 -0.1289 0.07109 0.06916 -0.1022 0.8985 0.0126
-8.000 -0.1933 0.02112 0.01737 -0.1311 0.8562 0.0190
-7.750 -0.1663 0.02088 0.01705 -0.1312 0.8447 0.0191
-7.500 -0.1394 0.02067 0.01675 -0.1313 0.8310 0.0192
-7.250 -0.1131 0.02043 0.01637 -0.1313 0.8127 0.0193
-7.000 -0.0867 0.02026 0.01607 -0.1312 0.7920 0.0195
-6.750 -0.0599 0.02020 0.01589 -0.1312 0.7722 0.0196
-6.500 -0.0335 0.01979 0.01533 -0.1313 0.7562 0.0199
-6.250 -0.0083 0.01857 0.01387 -0.1313 0.7404 0.0204
-6.000 0.0158 0.01643 0.01133 -0.1313 0.7254 0.0213
-5.750 0.0419 0.01525 0.00987 -0.1313 0.7106 0.0220
-5.500 0.0689 0.01449 0.00887 -0.1314 0.6962 0.0224
-5.250 0.0962 0.01399 0.00819 -0.1314 0.6806 0.0226
-5.000 0.1237 0.01360 0.00763 -0.1315 0.6643 0.0228
-4.750 0.1506 0.01286 0.00672 -0.1316 0.6490 0.0232
-4.500 0.1784 0.01267 0.00643 -0.1318 0.6342 0.0236
-4.250 0.2062 0.01254 0.00621 -0.1319 0.6184 0.0239
-4.000 0.2339 0.01238 0.00594 -0.1320 0.6013 0.0242
-3.750 0.2615 0.01219 0.00564 -0.1321 0.5848 0.0245
-3.500 0.2892 0.01200 0.00534 -0.1322 0.5696 0.0247
-3.250 0.3170 0.01181 0.00506 -0.1323 0.5550 0.0251
-3.000 0.3446 0.01165 0.00480 -0.1324 0.5397 0.0254
-2.750 0.3721 0.01151 0.00456 -0.1325 0.5238 0.0257
-2.500 0.3997 0.01139 0.00434 -0.1325 0.5084 0.0260
-2.250 0.4274 0.01128 0.00415 -0.1326 0.4953 0.0264
-2.000 0.4551 0.01120 0.00398 -0.1328 0.4828 0.0267
-1.750 0.4827 0.01116 0.00386 -0.1329 0.4696 0.0270
-1.500 0.5101 0.01116 0.00378 -0.1329 0.4557 0.0273
-1.250 0.5377 0.01112 0.00366 -0.1330 0.4427 0.0277
-1.000 0.5653 0.01101 0.00349 -0.1332 0.4319 0.0283
-0.750 0.5929 0.01100 0.00342 -0.1333 0.4218 0.0289
-0.500 0.6204 0.01101 0.00338 -0.1334 0.4112 0.0294
-0.250 0.6479 0.01104 0.00336 -0.1335 0.4011 0.0300
0.000 0.6751 0.01110 0.00336 -0.1336 0.3910 0.0306
0.250 0.7027 0.01112 0.00335 -0.1337 0.3825 0.0312
0.500 0.7299 0.01118 0.00336 -0.1337 0.3748 0.0320
0.750 0.7575 0.01122 0.00337 -0.1339 0.3680 0.0327
1.250 0.8118 0.01135 0.00343 -0.1340 0.3542 0.0357
1.500 0.8385 0.01144 0.00349 -0.1340 0.3469 0.0378
1.750 0.8655 0.01152 0.00356 -0.1340 0.3414 0.0400
2.000 0.8925 0.01159 0.00362 -0.1340 0.3364 0.0450
2.250 0.9190 0.01168 0.00371 -0.1340 0.3313 0.0545
2.500 0.9430 0.01021 0.00409 -0.1344 0.3272 0.8266
2.750 0.9642 0.00998 0.00417 -0.1328 0.3236 1.0000
3.000 0.9901 0.01017 0.00428 -0.1326 0.3169 1.0000
3.250 1.0156 0.01036 0.00441 -0.1324 0.3100 1.0000
3.500 1.0411 0.01055 0.00454 -0.1322 0.3028 1.0000
3.750 1.0659 0.01078 0.00469 -0.1319 0.2958 1.0000
4.000 1.0915 0.01094 0.00483 -0.1317 0.2909 1.0000
4.250 1.1166 0.01112 0.00498 -0.1314 0.2869 1.0000
4.500 1.1411 0.01133 0.00514 -0.1311 0.2827 1.0000
4.750 1.1659 0.01151 0.00530 -0.1308 0.2796 1.0000
5.000 1.1905 0.01168 0.00547 -0.1304 0.2762 1.0000
5.250 1.2145 0.01188 0.00565 -0.1300 0.2723 1.0000
5.500 1.2367 0.01211 0.00585 -0.1292 0.2682 1.0000
5.750 1.2583 0.01234 0.00607 -0.1282 0.2641 1.0000
6.000 1.2800 0.01258 0.00629 -0.1273 0.2595 1.0000
6.250 1.3008 0.01287 0.00655 -0.1263 0.2537 1.0000
6.500 1.3218 0.01316 0.00682 -0.1253 0.2487 1.0000
6.750 1.3433 0.01344 0.00709 -0.1245 0.2435 1.0000
7.000 1.3622 0.01385 0.00744 -0.1232 0.2338 1.0000
7.250 1.3797 0.01435 0.00785 -0.1217 0.2203 1.0000
7.500 1.3965 0.01489 0.00831 -0.1201 0.2065 1.0000
7.750 1.4127 0.01548 0.00881 -0.1185 0.1926 1.0000
8.000 1.4263 0.01621 0.00943 -0.1164 0.1735 1.0000
8.250 1.4225 0.01794 0.01084 -0.1116 0.1249 1.0000
8.500 1.4328 0.01890 0.01172 -0.1092 0.1084 1.0000
8.750 1.4442 0.01981 0.01256 -0.1070 0.0947 1.0000
9.000 1.4438 0.02147 0.01406 -0.1031 0.0563 1.0000
9.250 1.4590 0.02220 0.01480 -0.1017 0.0517 1.0000
9.500 1.4737 0.02296 0.01560 -0.1003 0.0484 1.0000
9.750 1.4889 0.02369 0.01636 -0.0989 0.0458 1.0000
10.000 1.5038 0.02446 0.01715 -0.0977 0.0431 1.0000
10.250 1.5165 0.02539 0.01809 -0.0961 0.0385 1.0000
10.750 1.5318 0.02802 0.02067 -0.0920 0.0147 1.0000
11.000 1.5428 0.02915 0.02184 -0.0905 0.0131 1.0000
11.250 1.5542 0.03028 0.02301 -0.0892 0.0121 1.0000
11.500 1.5644 0.03153 0.02430 -0.0878 0.0113 1.0000
11.750 1.5733 0.03293 0.02575 -0.0863 0.0105 1.0000
12.000 1.5831 0.03430 0.02718 -0.0851 0.0100 1.0000
12.250 1.5922 0.03576 0.02869 -0.0839 0.0096 1.0000
12.500 1.6002 0.03737 0.03036 -0.0827 0.0090 1.0000
12.750 1.6070 0.03914 0.03218 -0.0816 0.0086 1.0000
13.000 1.6120 0.04115 0.03425 -0.0804 0.0081 1.0000
13.250 1.6173 0.04320 0.03636 -0.0794 0.0078 1.0000
13.500 1.6225 0.04532 0.03855 -0.0786 0.0076 1.0000
13.750 1.6262 0.04762 0.04093 -0.0777 0.0073 1.0000
14.000 1.6290 0.05010 0.04348 -0.0770 0.0071 1.0000
14.250 1.6305 0.05278 0.04623 -0.0763 0.0068 1.0000
14.500 1.6306 0.05569 0.04923 -0.0757 0.0066 1.0000
14.750 1.6293 0.05886 0.05248 -0.0753 0.0064 1.0000
15.000 1.6260 0.06231 0.05601 -0.0749 0.0062 1.0000
15.250 1.6202 0.06614 0.05994 -0.0746 0.0060 1.0000
15.500 1.6133 0.07021 0.06411 -0.0745 0.0059 1.0000
15.750 1.6075 0.07422 0.06822 -0.0745 0.0058 1.0000
16.000 1.6004 0.07846 0.07257 -0.0746 0.0057 1.0000
16.250 1.5921 0.08290 0.07711 -0.0749 0.0056 1.0000
16.500 1.5816 0.08771 0.08203 -0.0753 0.0055 1.0000
16.750 1.5704 0.09269 0.08712 -0.0758 0.0054 1.0000
17.000 1.5589 0.09778 0.09231 -0.0765 0.0053 1.0000
17.250 1.5468 0.10298 0.09762 -0.0773 0.0052 1.0000
17.500 1.5341 0.10830 0.10305 -0.0782 0.0051 1.0000
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