GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 50,000 Max Cl/Cd: 38.82 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe392-il-50000-n5.txt Download as CSV file: xf-goe392-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 392 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3325 0.10407 0.09842 -0.0346 1.0000 0.1068
-7.250 -0.3563 0.10410 0.09864 -0.0323 1.0000 0.1086
-7.000 -0.3779 0.10387 0.09858 -0.0314 1.0000 0.1094
-6.750 -0.3805 0.10072 0.09553 -0.0288 1.0000 0.1115
-6.500 -0.3797 0.09812 0.09297 -0.0254 1.0000 0.1161
-6.000 -0.3430 0.08982 0.08461 -0.0454 0.9793 0.1386
-5.750 -0.3246 0.08545 0.08025 -0.0422 0.9738 0.1446
-5.500 -0.3049 0.08125 0.07602 -0.0482 0.9640 0.1567
-5.000 -0.2290 0.06425 0.05843 -0.0726 0.9453 0.0510
-4.500 -0.1579 0.05273 0.04592 -0.0868 0.9295 0.0412
-4.250 -0.1317 0.04872 0.04151 -0.0896 0.9202 0.0410
-4.000 -0.0984 0.04468 0.03699 -0.0930 0.9136 0.0407
-3.750 -0.0675 0.04117 0.03300 -0.0951 0.9058 0.0398
-3.500 -0.0324 0.03793 0.02917 -0.0974 0.8995 0.0391
-3.250 0.0005 0.03533 0.02600 -0.0986 0.8920 0.0390
-3.000 0.0374 0.03325 0.02316 -0.0999 0.8859 0.0413
-2.500 0.1050 0.02931 0.01862 -0.1018 0.8732 0.0487
-2.000 0.1729 0.02683 0.01544 -0.1034 0.8595 0.0668
-1.750 0.2055 0.02580 0.01429 -0.1044 0.8515 0.0902
-1.500 0.2465 0.02363 0.01346 -0.1072 0.8476 0.4354
-1.250 0.2737 0.02187 0.01319 -0.1055 0.8390 1.0000
-1.000 0.3119 0.02187 0.01250 -0.1074 0.8325 1.0000
-0.750 0.3418 0.02202 0.01218 -0.1080 0.8230 1.0000
-0.500 0.3721 0.02217 0.01193 -0.1086 0.8140 1.0000
-0.250 0.4078 0.02218 0.01155 -0.1100 0.8071 1.0000
0.000 0.4342 0.02242 0.01151 -0.1099 0.7968 1.0000
0.250 0.4671 0.02250 0.01133 -0.1109 0.7891 1.0000
0.500 0.4967 0.02265 0.01125 -0.1112 0.7799 1.0000
0.750 0.5230 0.02289 0.01132 -0.1111 0.7697 1.0000
1.000 0.5566 0.02292 0.01118 -0.1120 0.7621 1.0000
1.250 0.5827 0.02316 0.01131 -0.1118 0.7517 1.0000
1.500 0.6078 0.02343 0.01149 -0.1114 0.7412 1.0000
1.750 0.6379 0.02354 0.01152 -0.1117 0.7325 1.0000
2.000 0.6657 0.02371 0.01164 -0.1116 0.7228 1.0000
2.250 0.6891 0.02404 0.01198 -0.1110 0.7119 1.0000
2.500 0.7163 0.02424 0.01218 -0.1109 0.7025 1.0000
2.750 0.7455 0.02438 0.01234 -0.1110 0.6937 1.0000
3.000 0.7674 0.02479 0.01286 -0.1101 0.6828 1.0000
3.250 0.7927 0.02509 0.01323 -0.1097 0.6733 1.0000
3.500 0.8224 0.02523 0.01346 -0.1099 0.6650 1.0000
3.750 0.8431 0.02573 0.01410 -0.1088 0.6541 1.0000
4.000 0.8673 0.02611 0.01469 -0.1083 0.6446 1.0000
4.250 0.8968 0.02630 0.01508 -0.1084 0.6366 1.0000
4.500 0.9165 0.02690 0.01591 -0.1072 0.6259 1.0000
4.750 0.9405 0.02622 0.01535 -0.1049 0.6013 1.0000
5.000 0.9554 0.02498 0.01400 -0.1000 0.5517 1.0000
5.250 0.9663 0.02489 0.01380 -0.0959 0.5072 1.0000
5.500 0.9715 0.02527 0.01401 -0.0914 0.4497 1.0000
5.750 0.9722 0.02618 0.01438 -0.0866 0.3575 1.0000
6.000 0.9669 0.02797 0.01537 -0.0818 0.2317 1.0000
6.250 0.9458 0.03167 0.01785 -0.0764 0.0550 1.0000
6.500 0.9510 0.03351 0.01968 -0.0738 0.0433 1.0000
6.750 0.9560 0.03538 0.02169 -0.0713 0.0381 1.0000
7.000 0.9613 0.03722 0.02376 -0.0690 0.0345 1.0000
7.250 0.9631 0.03940 0.02624 -0.0668 0.0326 1.0000
7.500 0.9626 0.04185 0.02893 -0.0647 0.0317 1.0000
7.750 0.9630 0.04430 0.03160 -0.0629 0.0311 1.0000
8.000 0.9631 0.04687 0.03441 -0.0614 0.0307 1.0000
8.250 0.9624 0.04963 0.03740 -0.0600 0.0302 1.0000
8.500 0.9619 0.05244 0.04043 -0.0588 0.0295 1.0000
8.750 0.9621 0.05523 0.04341 -0.0576 0.0285 1.0000
9.000 0.9641 0.05784 0.04619 -0.0564 0.0276 1.0000
9.250 0.9692 0.06012 0.04861 -0.0549 0.0265 1.0000
9.500 0.9828 0.06152 0.05012 -0.0527 0.0256 1.0000
10.000 1.1764 0.06128 0.05064 -0.0506 0.0266 1.0000
10.250 1.2026 0.06475 0.05451 -0.0501 0.0265 1.0000
10.500 1.2150 0.06815 0.05828 -0.0486 0.0265 1.0000
10.750 1.2196 0.07151 0.06201 -0.0467 0.0268 1.0000
11.000 1.2186 0.07490 0.06574 -0.0446 0.0271 1.0000
11.250 1.2137 0.07840 0.06957 -0.0426 0.0276 1.0000
11.500 1.2060 0.08210 0.07356 -0.0409 0.0282 1.0000
11.750 1.1965 0.08590 0.07763 -0.0396 0.0287 1.0000
12.000 1.1854 0.09000 0.08199 -0.0388 0.0292 1.0000
12.250 1.1731 0.09438 0.08660 -0.0384 0.0297 1.0000
12.500 1.1610 0.09897 0.09139 -0.0386 0.0301 1.0000
12.750 1.1525 0.10390 0.09647 -0.0390 0.0307 1.0000
13.000 1.1499 0.10856 0.10132 -0.0394 0.0321 1.0000
13.250 1.1278 0.11349 0.10648 -0.0412 0.0322 1.0000
13.500 1.1069 0.11891 0.11211 -0.0438 0.0323 1.0000
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Polar data table (+)
Polar graphs
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