GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 797 AIRFOIL (goe797-il) Reynolds number: 200,000 Max Cl/Cd: 73.32 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe797-il-200000-n5.txt Download as CSV file: xf-goe797-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 797 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6100 0.04556 0.04073 -0.1203 0.9710 0.0450
-11.750 -0.6307 0.04031 0.03508 -0.1230 0.9588 0.0453
-11.500 -0.6332 0.03715 0.03158 -0.1230 0.9489 0.0458
-11.250 -0.6256 0.03451 0.02859 -0.1232 0.9420 0.0464
-11.000 -0.6150 0.03239 0.02615 -0.1228 0.9340 0.0470
-10.750 -0.5987 0.03063 0.02412 -0.1226 0.9277 0.0476
-10.500 -0.5796 0.02957 0.02301 -0.1221 0.9200 0.0482
-10.250 -0.5557 0.02863 0.02200 -0.1223 0.9150 0.0489
-10.000 -0.5366 0.02782 0.02112 -0.1214 0.9064 0.0497
-9.750 -0.5137 0.02687 0.02003 -0.1213 0.9002 0.0507
-9.500 -0.4931 0.02592 0.01893 -0.1206 0.8922 0.0517
-9.250 -0.4707 0.02491 0.01772 -0.1202 0.8848 0.0527
-9.000 -0.4481 0.02396 0.01656 -0.1198 0.8773 0.0537
-8.750 -0.4251 0.02308 0.01555 -0.1193 0.8693 0.0546
-8.500 -0.4004 0.02238 0.01479 -0.1191 0.8628 0.0556
-8.250 -0.3764 0.02182 0.01419 -0.1187 0.8541 0.0568
-8.000 -0.3504 0.02124 0.01350 -0.1185 0.8475 0.0583
-7.750 -0.3259 0.02069 0.01284 -0.1181 0.8384 0.0600
-7.500 -0.2997 0.02010 0.01207 -0.1179 0.8315 0.0616
-7.250 -0.2747 0.01950 0.01143 -0.1176 0.8237 0.0632
-7.000 -0.2484 0.01904 0.01092 -0.1175 0.8166 0.0648
-6.750 -0.2219 0.01863 0.01043 -0.1173 0.8097 0.0668
-6.500 -0.1953 0.01824 0.00995 -0.1172 0.8023 0.0692
-6.250 -0.1678 0.01785 0.00940 -0.1171 0.7964 0.0716
-6.000 -0.1417 0.01745 0.00902 -0.1170 0.7893 0.0743
-5.750 -0.1143 0.01717 0.00868 -0.1169 0.7835 0.0772
-5.500 -0.0865 0.01688 0.00830 -0.1169 0.7783 0.0806
-5.250 -0.0594 0.01659 0.00794 -0.1169 0.7720 0.0842
-5.000 -0.0318 0.01634 0.00769 -0.1169 0.7665 0.0882
-4.750 -0.0037 0.01615 0.00742 -0.1169 0.7618 0.0928
-4.500 0.0239 0.01596 0.00717 -0.1169 0.7564 0.0975
-4.250 0.0516 0.01577 0.00700 -0.1169 0.7514 0.1026
-4.000 0.0801 0.01564 0.00679 -0.1170 0.7470 0.1084
-3.750 0.1081 0.01550 0.00659 -0.1171 0.7424 0.1139
-3.500 0.1357 0.01537 0.00649 -0.1171 0.7374 0.1196
-3.250 0.1641 0.01528 0.00633 -0.1172 0.7332 0.1259
-3.000 0.1926 0.01516 0.00616 -0.1173 0.7293 0.1315
-2.750 0.2205 0.01506 0.00606 -0.1174 0.7250 0.1376
-2.500 0.2484 0.01499 0.00595 -0.1174 0.7198 0.1437
-2.250 0.2762 0.01485 0.00582 -0.1174 0.7148 0.1495
-2.000 0.3048 0.01477 0.00567 -0.1175 0.7099 0.1563
-1.750 0.3317 0.01467 0.00560 -0.1174 0.7037 0.1628
-1.500 0.3593 0.01455 0.00550 -0.1174 0.6981 0.1703
-1.250 0.3877 0.01448 0.00538 -0.1174 0.6933 0.1780
-1.000 0.4148 0.01437 0.00534 -0.1174 0.6875 0.1869
-0.750 0.4420 0.01429 0.00528 -0.1173 0.6812 0.1965
-0.500 0.4701 0.01420 0.00518 -0.1173 0.6756 0.2090
-0.250 0.4969 0.01410 0.00517 -0.1172 0.6692 0.2271
0.000 0.5239 0.01398 0.00517 -0.1171 0.6635 0.2552
0.250 0.5516 0.01385 0.00515 -0.1171 0.6590 0.2965
0.500 0.5785 0.01367 0.00516 -0.1171 0.6543 0.3547
0.750 0.6034 0.01334 0.00525 -0.1167 0.6486 0.4665
1.000 0.6262 0.01286 0.00535 -0.1157 0.6434 0.6367
1.250 0.6472 0.01252 0.00546 -0.1136 0.6390 0.8004
1.500 0.6774 0.01247 0.00562 -0.1135 0.6331 0.9110
1.750 0.7178 0.01252 0.00566 -0.1160 0.6272 0.9689
2.000 0.7607 0.01260 0.00564 -0.1193 0.6219 1.0000
2.250 0.7841 0.01270 0.00574 -0.1185 0.6153 1.0000
2.500 0.8086 0.01280 0.00578 -0.1178 0.6087 1.0000
2.750 0.8333 0.01290 0.00583 -0.1172 0.6021 1.0000
3.000 0.8573 0.01302 0.00592 -0.1165 0.5942 1.0000
3.250 0.8822 0.01313 0.00596 -0.1159 0.5870 1.0000
3.500 0.9060 0.01327 0.00609 -0.1152 0.5785 1.0000
3.750 0.9306 0.01340 0.00615 -0.1146 0.5706 1.0000
4.000 0.9541 0.01355 0.00631 -0.1138 0.5611 1.0000
4.250 0.9778 0.01371 0.00641 -0.1130 0.5517 1.0000
4.500 1.0009 0.01388 0.00656 -0.1121 0.5408 1.0000
4.750 1.0235 0.01408 0.00672 -0.1112 0.5293 1.0000
5.000 1.0454 0.01429 0.00688 -0.1101 0.5169 1.0000
5.250 1.0661 0.01454 0.00706 -0.1088 0.5026 1.0000
5.500 1.0854 0.01483 0.00726 -0.1073 0.4865 1.0000
5.750 1.1035 0.01516 0.00751 -0.1056 0.4696 1.0000
6.000 1.1202 0.01554 0.00780 -0.1036 0.4528 1.0000
6.250 1.1356 0.01597 0.00813 -0.1014 0.4370 1.0000
6.500 1.1497 0.01640 0.00848 -0.0990 0.4234 1.0000
6.750 1.1647 0.01683 0.00888 -0.0969 0.4120 1.0000
7.000 1.1798 0.01732 0.00931 -0.0948 0.4022 1.0000
7.250 1.1945 0.01784 0.00978 -0.0927 0.3917 1.0000
7.500 1.2100 0.01837 0.01027 -0.0908 0.3821 1.0000
7.750 1.2251 0.01894 0.01080 -0.0889 0.3738 1.0000
8.000 1.2425 0.01945 0.01132 -0.0875 0.3673 1.0000
8.250 1.2588 0.02002 0.01188 -0.0859 0.3601 1.0000
8.500 1.2743 0.02064 0.01248 -0.0843 0.3534 1.0000
8.750 1.2913 0.02120 0.01307 -0.0829 0.3468 1.0000
9.000 1.3069 0.02185 0.01371 -0.0814 0.3408 1.0000
9.250 1.3235 0.02248 0.01435 -0.0801 0.3357 1.0000
9.500 1.3406 0.02308 0.01501 -0.0788 0.3303 1.0000
9.750 1.3558 0.02378 0.01573 -0.0774 0.3246 1.0000
10.000 1.3705 0.02453 0.01648 -0.0759 0.3192 1.0000
10.250 1.3861 0.02523 0.01726 -0.0747 0.3131 1.0000
10.500 1.3998 0.02606 0.01811 -0.0732 0.3072 1.0000
10.750 1.4136 0.02689 0.01898 -0.0718 0.3017 1.0000
11.000 1.4273 0.02774 0.01992 -0.0705 0.2949 1.0000
11.250 1.4381 0.02878 0.02096 -0.0689 0.2882 1.0000
11.500 1.4508 0.02974 0.02201 -0.0676 0.2809 1.0000
11.750 1.4604 0.03090 0.02321 -0.0660 0.2730 1.0000
12.000 1.4708 0.03206 0.02444 -0.0646 0.2643 1.0000
12.250 1.4775 0.03349 0.02589 -0.0630 0.2550 1.0000
12.500 1.4865 0.03484 0.02731 -0.0617 0.2441 1.0000
12.750 1.4924 0.03644 0.02894 -0.0603 0.2326 1.0000
13.000 1.4964 0.03826 0.03076 -0.0588 0.2203 1.0000
13.250 1.4986 0.04030 0.03280 -0.0574 0.2080 1.0000
13.500 1.4991 0.04258 0.03504 -0.0560 0.1965 1.0000
13.750 1.5001 0.04485 0.03732 -0.0547 0.1868 1.0000
14.000 1.5004 0.04725 0.03972 -0.0535 0.1788 1.0000
14.250 1.5005 0.04974 0.04220 -0.0523 0.1716 1.0000
14.500 1.5015 0.05217 0.04466 -0.0513 0.1652 1.0000
14.750 1.5022 0.05469 0.04721 -0.0504 0.1591 1.0000
15.000 1.5016 0.05737 0.04990 -0.0496 0.1540 1.0000
15.250 1.5058 0.05963 0.05225 -0.0489 0.1488 1.0000
15.500 1.5061 0.06234 0.05500 -0.0483 0.1441 1.0000
15.750 1.5064 0.06506 0.05777 -0.0477 0.1400 1.0000
16.000 1.5105 0.06745 0.06026 -0.0474 0.1353 1.0000
16.250 1.5107 0.07029 0.06317 -0.0470 0.1308 1.0000
16.500 1.5084 0.07347 0.06636 -0.0467 0.1269 1.0000
16.750 1.5123 0.07600 0.06903 -0.0466 0.1229 1.0000
17.000 1.5131 0.07893 0.07205 -0.0466 0.1186 1.0000
17.250 1.5104 0.08231 0.07548 -0.0466 0.1145 1.0000
17.500 1.5085 0.08565 0.07888 -0.0467 0.1106 1.0000
17.750 1.5089 0.08875 0.08210 -0.0470 0.1062 1.0000
18.000 1.5057 0.09236 0.08578 -0.0474 0.1019 1.0000
18.250 1.4994 0.09643 0.08989 -0.0479 0.0982 1.0000
18.500 1.4994 0.09967 0.09326 -0.0484 0.0945 1.0000
18.750 1.4965 0.10334 0.09702 -0.0491 0.0906 1.0000
19.000 1.4906 0.10748 0.10122 -0.0500 0.0869 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 797 AIRFOIL (goe797-il)