GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 100,000 Max Cl/Cd: 49.76 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe368-il-100000.txt Download as CSV file: xf-goe368-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4055 0.10573 0.10101 -0.0019 1.0000 0.0875
-8.250 -0.4142 0.10498 0.10037 -0.0060 1.0000 0.0911
-8.000 -0.4274 0.10452 0.10005 -0.0105 1.0000 0.0917
-7.750 -0.3942 0.09656 0.09201 -0.0052 1.0000 0.0960
-7.500 -0.3892 0.09382 0.08932 -0.0058 1.0000 0.1005
-7.250 -0.3987 0.09272 0.08835 -0.0098 1.0000 0.1040
-7.000 -0.4004 0.09037 0.08607 -0.0185 1.0000 0.1053
-6.750 -0.3850 0.08487 0.08061 -0.0115 1.0000 0.1075
-6.500 -0.3750 0.08157 0.07734 -0.0112 1.0000 0.1106
-6.250 -0.3672 0.07853 0.07431 -0.0141 1.0000 0.1151
-6.000 -0.3576 0.07534 0.07112 -0.0249 1.0000 0.1192
-5.750 -0.3475 0.07111 0.06693 -0.0221 1.0000 0.1205
-5.500 -0.3357 0.06762 0.06347 -0.0218 1.0000 0.1224
-5.250 -0.3222 0.06415 0.06000 -0.0232 1.0000 0.1246
-5.000 -0.3064 0.06051 0.05634 -0.0258 1.0000 0.1268
-4.750 -0.2708 0.04243 0.03743 -0.0431 1.0000 0.0683
-4.500 -0.2531 0.03953 0.03451 -0.0424 1.0000 0.0647
-4.250 -0.2264 0.02767 0.02130 -0.0466 1.0000 0.0549
-4.000 -0.2031 0.02410 0.01709 -0.0463 1.0000 0.0551
-3.750 -0.1797 0.02138 0.01390 -0.0458 1.0000 0.0571
-3.500 -0.1563 0.01953 0.01184 -0.0448 1.0000 0.0593
-3.250 -0.1330 0.01813 0.01025 -0.0438 1.0000 0.0616
-3.000 -0.1102 0.01703 0.00900 -0.0426 1.0000 0.0658
-2.750 -0.0889 0.01629 0.00831 -0.0415 1.0000 0.0749
-2.500 -0.0689 0.01598 0.00811 -0.0402 1.0000 0.0953
-2.250 -0.0522 0.01683 0.00909 -0.0385 1.0000 0.1514
-2.000 -0.0014 0.01921 0.01140 -0.0439 0.9834 0.2143
-1.750 0.0490 0.01961 0.01184 -0.0488 0.9652 0.2569
-1.500 0.1008 0.01864 0.01068 -0.0534 0.9487 0.2591
-1.250 0.1513 0.01783 0.00974 -0.0574 0.9311 0.2640
-1.000 0.1978 0.01713 0.00882 -0.0604 0.9100 0.2684
-0.750 0.2407 0.01643 0.00798 -0.0624 0.8857 0.2727
-0.500 0.2773 0.01587 0.00733 -0.0631 0.8571 0.2784
-0.250 0.3078 0.01558 0.00683 -0.0625 0.8247 0.2852
0.000 0.3344 0.01529 0.00648 -0.0613 0.7915 0.2933
0.250 0.3594 0.01508 0.00619 -0.0599 0.7590 0.3044
0.500 0.3837 0.01487 0.00592 -0.0584 0.7259 0.3179
0.750 0.4082 0.01468 0.00567 -0.0570 0.6938 0.3344
1.000 0.4328 0.01454 0.00544 -0.0557 0.6631 0.3571
1.250 0.4569 0.01432 0.00529 -0.0546 0.6337 0.4026
1.500 0.4925 0.01310 0.00514 -0.0551 0.6029 1.0000
1.750 0.5174 0.01342 0.00516 -0.0541 0.5746 1.0000
2.000 0.5422 0.01370 0.00521 -0.0531 0.5472 1.0000
2.250 0.5671 0.01397 0.00529 -0.0522 0.5210 1.0000
2.500 0.5919 0.01426 0.00538 -0.0513 0.4957 1.0000
2.750 0.6166 0.01462 0.00554 -0.0505 0.4720 1.0000
3.000 0.6413 0.01504 0.00575 -0.0496 0.4489 1.0000
3.250 0.6661 0.01554 0.00608 -0.0489 0.4266 1.0000
3.500 0.6910 0.01609 0.00645 -0.0483 0.4069 1.0000
3.750 0.7162 0.01669 0.00693 -0.0477 0.3897 1.0000
4.000 0.7416 0.01727 0.00746 -0.0471 0.3737 1.0000
4.250 0.7671 0.01788 0.00799 -0.0466 0.3601 1.0000
4.500 0.7927 0.01847 0.00852 -0.0462 0.3482 1.0000
4.750 0.8181 0.01905 0.00916 -0.0457 0.3369 1.0000
5.000 0.8438 0.01969 0.00990 -0.0452 0.3277 1.0000
5.250 0.8698 0.02036 0.01053 -0.0449 0.3206 1.0000
5.500 0.8950 0.02105 0.01140 -0.0444 0.3127 1.0000
5.750 0.9190 0.02128 0.01164 -0.0437 0.2998 1.0000
6.000 0.9424 0.02138 0.01179 -0.0429 0.2857 1.0000
6.250 0.9665 0.02164 0.01208 -0.0423 0.2748 1.0000
6.500 0.9908 0.02194 0.01245 -0.0417 0.2652 1.0000
6.750 1.0125 0.02181 0.01237 -0.0407 0.2480 1.0000
7.000 1.0349 0.02184 0.01256 -0.0398 0.2328 1.0000
7.250 1.0579 0.02204 0.01294 -0.0389 0.2205 1.0000
7.500 1.0804 0.02210 0.01324 -0.0380 0.2024 1.0000
7.750 1.1027 0.02216 0.01342 -0.0372 0.1729 1.0000
8.000 1.1249 0.02275 0.01389 -0.0363 0.1052 1.0000
8.250 1.1334 0.02562 0.01613 -0.0346 0.0470 1.0000
8.500 1.1505 0.02719 0.01790 -0.0331 0.0427 1.0000
8.750 1.1660 0.02882 0.01985 -0.0316 0.0403 1.0000
9.000 1.1783 0.03063 0.02191 -0.0300 0.0387 1.0000
9.250 1.1857 0.03272 0.02423 -0.0281 0.0372 1.0000
9.500 1.1873 0.03508 0.02677 -0.0258 0.0359 1.0000
9.750 1.1925 0.03696 0.02880 -0.0238 0.0350 1.0000
10.000 1.1952 0.03886 0.03083 -0.0214 0.0342 1.0000
10.250 1.1972 0.04086 0.03293 -0.0191 0.0339 1.0000
10.500 1.2030 0.04294 0.03508 -0.0172 0.0339 1.0000
10.750 1.2150 0.04510 0.03729 -0.0155 0.0339 1.0000
11.000 1.2348 0.04755 0.03981 -0.0141 0.0342 1.0000
11.250 1.2576 0.05070 0.04309 -0.0132 0.0347 1.0000
11.500 1.2799 0.05494 0.04756 -0.0129 0.0354 1.0000
11.750 1.2929 0.05845 0.05131 -0.0120 0.0361 1.0000
12.000 1.2864 0.06050 0.05367 -0.0099 0.0367 1.0000
12.250 1.2745 0.06334 0.05683 -0.0089 0.0373 1.0000
12.500 1.2596 0.06718 0.06101 -0.0091 0.0380 1.0000
12.750 1.2437 0.07181 0.06594 -0.0105 0.0386 1.0000
13.000 1.2230 0.07732 0.07174 -0.0133 0.0390 1.0000
13.250 1.2018 0.08355 0.07821 -0.0171 0.0393 1.0000
13.500 1.1797 0.09054 0.08542 -0.0218 0.0395 1.0000
13.750 1.1556 0.09850 0.09358 -0.0275 0.0397 1.0000
14.000 1.1312 0.10713 0.10233 -0.0338 0.0397 1.0000
14.250 1.1034 0.11721 0.11256 -0.0412 0.0398 1.0000
14.500 1.0724 0.12912 0.12459 -0.0498 0.0399 1.0000
14.750 1.0331 0.14498 0.14052 -0.0607 0.0405 1.0000
15.000 1.0019 0.16075 0.15624 -0.0699 0.0424 1.0000
15.250 0.9950 0.16930 0.16476 -0.0740 0.0442 1.0000
15.500 0.9989 0.17387 0.16932 -0.0753 0.0456 1.0000
15.750 0.9787 0.19091 0.18623 -0.0848 0.0543 1.0000
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Polar data table (+)
Polar graphs
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