GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 500,000 Max Cl/Cd: 86.27 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe711-il-500000.txt Download as CSV file: xf-goe711-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0501 0.08665 0.08433 -0.1036 0.9717 0.0264
-8.500 -0.0514 0.08152 0.07922 -0.1093 0.9639 0.0265
-8.250 -0.0460 0.07657 0.07428 -0.1126 0.9595 0.0268
-8.000 -0.0303 0.07408 0.07178 -0.1129 0.9569 0.0271
-7.750 -0.0283 0.07189 0.06960 -0.1124 0.9483 0.0273
-7.500 -0.0179 0.06877 0.06646 -0.1148 0.9430 0.0277
-7.250 -0.0121 0.06563 0.06330 -0.1168 0.9344 0.0282
-7.000 -0.0019 0.06189 0.05951 -0.1200 0.9280 0.0290
-6.750 0.0106 0.05338 0.05067 -0.1302 0.9178 0.0315
-6.500 0.0192 0.04775 0.04486 -0.1318 0.9122 0.0319
-6.250 0.0328 0.04578 0.04290 -0.1313 0.9038 0.0322
-6.000 0.0505 0.04392 0.04099 -0.1314 0.8978 0.0327
-5.750 0.0685 0.04191 0.03891 -0.1316 0.8891 0.0334
-5.500 0.0896 0.03931 0.03615 -0.1324 0.8822 0.0346
-5.250 0.1120 0.03352 0.02966 -0.1333 0.8724 0.0381
-5.000 0.1337 0.03138 0.02750 -0.1336 0.8639 0.0386
-4.750 0.1568 0.02997 0.02604 -0.1338 0.8536 0.0393
-4.500 0.1808 0.02857 0.02452 -0.1339 0.8421 0.0405
-4.000 0.2335 0.02426 0.01937 -0.1337 0.8189 0.0460
-3.750 0.2588 0.02285 0.01789 -0.1339 0.8054 0.0469
-3.000 0.3395 0.01975 0.01400 -0.1338 0.7606 0.0556
-2.750 0.3658 0.01866 0.01284 -0.1339 0.7450 0.0571
-2.500 0.3926 0.01796 0.01199 -0.1339 0.7287 0.0593
-2.250 0.4204 0.01789 0.01170 -0.1336 0.7120 0.0635
-2.000 0.4467 0.01657 0.01017 -0.1337 0.6960 0.0685
-1.750 0.4735 0.01604 0.00954 -0.1337 0.6798 0.0719
-1.500 0.5002 0.01558 0.00890 -0.1336 0.6631 0.0820
-1.250 0.5312 0.01387 0.00660 -0.1320 0.6476 0.0449
-1.000 0.5576 0.01344 0.00606 -0.1317 0.6302 0.0450
-0.750 0.5836 0.01286 0.00538 -0.1314 0.6133 0.0455
-0.500 0.6093 0.01244 0.00491 -0.1312 0.5967 0.0468
-0.250 0.6353 0.01226 0.00466 -0.1309 0.5799 0.0476
0.000 0.6612 0.01216 0.00448 -0.1306 0.5629 0.0486
0.250 0.6870 0.01212 0.00434 -0.1303 0.5461 0.0499
0.500 0.7128 0.01211 0.00425 -0.1301 0.5300 0.0514
0.750 0.7386 0.01213 0.00419 -0.1298 0.5148 0.0530
1.000 0.7643 0.01213 0.00410 -0.1295 0.5003 0.0560
1.250 0.7899 0.01217 0.00407 -0.1292 0.4860 0.0602
1.500 0.8152 0.01228 0.00408 -0.1289 0.4721 0.0650
1.750 0.8406 0.01178 0.00418 -0.1290 0.4589 0.3392
2.000 0.8589 0.01044 0.00440 -0.1270 0.4477 1.0000
2.250 0.8838 0.01067 0.00450 -0.1266 0.4366 1.0000
2.750 0.9336 0.01112 0.00475 -0.1259 0.4163 1.0000
3.000 0.9578 0.01137 0.00491 -0.1254 0.4074 1.0000
3.250 0.9826 0.01159 0.00506 -0.1250 0.3987 1.0000
3.500 1.0067 0.01184 0.00523 -0.1245 0.3910 1.0000
3.750 1.0311 0.01206 0.00540 -0.1241 0.3835 1.0000
4.000 1.0543 0.01235 0.00561 -0.1234 0.3771 1.0000
4.250 1.0790 0.01254 0.00579 -0.1231 0.3710 1.0000
4.500 1.1017 0.01283 0.00600 -0.1224 0.3645 1.0000
4.750 1.1253 0.01307 0.00621 -0.1218 0.3586 1.0000
5.000 1.1483 0.01331 0.00643 -0.1211 0.3524 1.0000
5.250 1.1684 0.01365 0.00669 -0.1199 0.3462 1.0000
5.500 1.1909 0.01384 0.00690 -0.1191 0.3407 1.0000
5.750 1.2113 0.01414 0.00717 -0.1180 0.3353 1.0000
6.000 1.2311 0.01450 0.00749 -0.1168 0.3304 1.0000
6.250 1.2537 0.01473 0.00775 -0.1161 0.3262 1.0000
6.500 1.2750 0.01503 0.00804 -0.1152 0.3219 1.0000
6.750 1.2950 0.01539 0.00839 -0.1141 0.3180 1.0000
7.000 1.3156 0.01575 0.00874 -0.1131 0.3142 1.0000
7.250 1.3378 0.01601 0.00905 -0.1125 0.3103 1.0000
7.500 1.3584 0.01635 0.00939 -0.1116 0.3057 1.0000
7.750 1.3764 0.01683 0.00982 -0.1102 0.3006 1.0000
8.000 1.3985 0.01709 0.01014 -0.1096 0.2955 1.0000
8.250 1.4183 0.01747 0.01052 -0.1087 0.2899 1.0000
8.500 1.4356 0.01799 0.01101 -0.1073 0.2851 1.0000
8.750 1.4574 0.01828 0.01137 -0.1067 0.2808 1.0000
9.000 1.4768 0.01870 0.01181 -0.1058 0.2752 1.0000
9.250 1.4938 0.01925 0.01234 -0.1045 0.2692 1.0000
9.500 1.5138 0.01964 0.01278 -0.1037 0.2627 1.0000
9.750 1.5296 0.02026 0.01337 -0.1023 0.2560 1.0000
10.000 1.5485 0.02073 0.01388 -0.1014 0.2483 1.0000
10.250 1.5633 0.02144 0.01456 -0.1000 0.2400 1.0000
10.500 1.5795 0.02208 0.01521 -0.0988 0.2306 1.0000
10.750 1.5932 0.02290 0.01600 -0.0973 0.2190 1.0000
11.000 1.6024 0.02400 0.01702 -0.0952 0.2022 1.0000
11.250 1.6059 0.02551 0.01839 -0.0925 0.1774 1.0000
11.500 1.5970 0.02796 0.02060 -0.0885 0.1408 1.0000
11.750 1.5850 0.03077 0.02323 -0.0845 0.1128 1.0000
12.000 1.5691 0.03408 0.02637 -0.0806 0.0704 1.0000
12.250 1.5567 0.03736 0.02961 -0.0774 0.0529 1.0000
12.500 1.5577 0.03964 0.03197 -0.0757 0.0458 1.0000
12.750 1.5591 0.04199 0.03439 -0.0743 0.0374 1.0000
13.250 1.5529 0.04792 0.04034 -0.0716 0.0206 1.0000
13.500 1.5507 0.05095 0.04347 -0.0706 0.0192 1.0000
13.750 1.5479 0.05417 0.04680 -0.0698 0.0182 1.0000
14.000 1.5455 0.05746 0.05022 -0.0692 0.0176 1.0000
14.250 1.5410 0.06109 0.05397 -0.0688 0.0171 1.0000
14.500 1.5340 0.06512 0.05813 -0.0685 0.0167 1.0000
14.750 1.5253 0.06948 0.06262 -0.0684 0.0163 1.0000
15.000 1.5142 0.07429 0.06757 -0.0685 0.0160 1.0000
15.250 1.5009 0.07951 0.07293 -0.0688 0.0158 1.0000
15.500 1.4856 0.08510 0.07865 -0.0692 0.0155 1.0000
15.750 1.4688 0.09104 0.08475 -0.0700 0.0154 1.0000
16.000 1.4510 0.09724 0.09109 -0.0709 0.0152 1.0000
16.250 1.4333 0.10351 0.09750 -0.0720 0.0151 1.0000
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Polar data table (+)
Polar graphs
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