GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 500,000 Max Cl/Cd: 101.59 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe328-il-500000.txt Download as CSV file: xf-goe328-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 328 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3633 0.09359 0.09136 -0.0176 1.0000 0.0237
-7.750 -0.3609 0.09048 0.08829 -0.0224 1.0000 0.0248
-7.500 -0.3545 0.08661 0.08445 -0.0298 1.0000 0.0250
-7.250 -0.3434 0.08255 0.08039 -0.0353 1.0000 0.0251
-6.750 -0.3161 0.07307 0.07091 -0.0429 0.9936 0.0255
-6.500 -0.2939 0.06961 0.06743 -0.0455 0.9853 0.0258
-6.250 -0.2692 0.06612 0.06391 -0.0496 0.9744 0.0262
-6.000 -0.2441 0.06268 0.06043 -0.0540 0.9606 0.0268
-5.750 -0.2213 0.05927 0.05694 -0.0579 0.9437 0.0277
-5.500 -0.1994 0.05579 0.05334 -0.0614 0.9265 0.0288
-5.250 -0.1581 0.05107 0.04830 -0.0694 0.9103 0.0307
-5.000 -0.1329 0.04772 0.04474 -0.0716 0.8961 0.0308
-4.750 -0.1146 0.04220 0.03905 -0.0738 0.8827 0.0313
-4.500 -0.0954 0.03994 0.03672 -0.0742 0.8693 0.0317
-4.250 -0.0736 0.03801 0.03470 -0.0747 0.8562 0.0323
-4.000 -0.0494 0.03596 0.03251 -0.0755 0.8443 0.0330
-3.750 -0.0232 0.03378 0.03016 -0.0765 0.8334 0.0341
-3.500 0.0057 0.03144 0.02762 -0.0775 0.8224 0.0360
-3.250 0.0416 0.03029 0.02600 -0.0777 0.8121 0.0381
-3.000 0.0664 0.02554 0.02097 -0.0792 0.8025 0.0391
-2.750 0.0923 0.02401 0.01937 -0.0797 0.7919 0.0398
-2.500 0.1188 0.02284 0.01810 -0.0800 0.7822 0.0409
-2.250 0.1464 0.02170 0.01680 -0.0803 0.7722 0.0426
-2.000 0.1760 0.02067 0.01554 -0.0804 0.7621 0.0458
-1.750 0.2066 0.01900 0.01340 -0.0805 0.7529 0.0487
-1.500 0.2337 0.01756 0.01192 -0.0809 0.7420 0.0502
-1.250 0.2616 0.01674 0.01100 -0.0811 0.7300 0.0522
-1.000 0.2902 0.01618 0.01028 -0.0811 0.7177 0.0563
-0.750 0.3196 0.01727 0.01114 -0.0805 0.7051 0.0594
-0.250 0.3759 0.01410 0.00776 -0.0814 0.6838 0.0696
0.000 0.4074 0.01218 0.00544 -0.0806 0.6741 0.0458
0.250 0.4360 0.01125 0.00437 -0.0805 0.6635 0.0431
0.500 0.4645 0.01071 0.00376 -0.0805 0.6518 0.0426
0.750 0.4929 0.01035 0.00336 -0.0804 0.6402 0.0430
1.000 0.5212 0.01009 0.00305 -0.0804 0.6282 0.0437
1.250 0.5494 0.00989 0.00281 -0.0804 0.6152 0.0446
1.500 0.5777 0.00979 0.00267 -0.0805 0.6010 0.0463
1.750 0.6059 0.00971 0.00255 -0.0805 0.5851 0.0475
2.000 0.6343 0.00952 0.00231 -0.0806 0.5672 0.0496
2.250 0.6625 0.00948 0.00221 -0.0806 0.5467 0.0538
2.500 0.6904 0.00953 0.00217 -0.0806 0.5246 0.0593
2.750 0.7110 0.00757 0.00229 -0.0795 0.5039 1.0000
3.000 0.7385 0.00780 0.00234 -0.0794 0.4833 1.0000
3.250 0.7660 0.00802 0.00244 -0.0794 0.4659 1.0000
3.500 0.7934 0.00825 0.00256 -0.0794 0.4510 1.0000
4.000 0.8484 0.00867 0.00285 -0.0793 0.4263 1.0000
4.250 0.8759 0.00887 0.00302 -0.0793 0.4160 1.0000
4.500 0.9031 0.00912 0.00320 -0.0793 0.4060 1.0000
4.750 0.9305 0.00931 0.00337 -0.0793 0.3944 1.0000
5.000 0.9576 0.00952 0.00355 -0.0792 0.3797 1.0000
5.250 0.9847 0.00973 0.00372 -0.0792 0.3660 1.0000
5.500 1.0116 0.00996 0.00391 -0.0791 0.3502 1.0000
5.750 1.0382 0.01022 0.00410 -0.0791 0.3323 1.0000
6.000 1.0647 0.01049 0.00432 -0.0790 0.3164 1.0000
6.250 1.0911 0.01076 0.00456 -0.0788 0.2990 1.0000
6.500 1.1172 0.01106 0.00481 -0.0787 0.2829 1.0000
6.750 1.1428 0.01142 0.00510 -0.0785 0.2635 1.0000
7.000 1.1676 0.01187 0.00545 -0.0782 0.2393 1.0000
7.250 1.1909 0.01250 0.00591 -0.0778 0.2019 1.0000
7.500 1.2009 0.01491 0.00742 -0.0759 0.0580 1.0000
7.750 1.2208 0.01597 0.00838 -0.0748 0.0383 1.0000
8.000 1.2430 0.01664 0.00906 -0.0741 0.0322 1.0000
8.250 1.2644 0.01739 0.00987 -0.0732 0.0285 1.0000
8.500 1.2859 0.01806 0.01058 -0.0724 0.0261 1.0000
8.750 1.3025 0.01922 0.01180 -0.0710 0.0240 1.0000
9.000 1.3227 0.01991 0.01257 -0.0700 0.0229 1.0000
9.250 1.3419 0.02065 0.01337 -0.0689 0.0216 1.0000
9.500 1.3595 0.02147 0.01424 -0.0676 0.0204 1.0000
9.750 1.3726 0.02260 0.01543 -0.0658 0.0195 1.0000
10.000 1.3761 0.02439 0.01732 -0.0626 0.0188 1.0000
10.250 1.3874 0.02531 0.01833 -0.0604 0.0184 1.0000
10.500 1.3951 0.02643 0.01954 -0.0578 0.0179 1.0000
10.750 1.4016 0.02774 0.02096 -0.0554 0.0175 1.0000
11.000 1.4080 0.02919 0.02250 -0.0533 0.0170 1.0000
11.250 1.4147 0.03070 0.02409 -0.0515 0.0165 1.0000
11.500 1.4212 0.03231 0.02577 -0.0500 0.0161 1.0000
11.750 1.4270 0.03405 0.02757 -0.0486 0.0156 1.0000
12.000 1.4298 0.03619 0.02976 -0.0471 0.0152 1.0000
12.250 1.4276 0.03903 0.03268 -0.0450 0.0148 1.0000
12.500 1.4322 0.04123 0.03500 -0.0436 0.0146 1.0000
12.750 1.4379 0.04326 0.03716 -0.0427 0.0143 1.0000
13.000 1.4427 0.04547 0.03950 -0.0417 0.0141 1.0000
13.250 1.4466 0.04783 0.04200 -0.0407 0.0139 1.0000
13.500 1.4494 0.05035 0.04466 -0.0398 0.0137 1.0000
13.750 1.4513 0.05304 0.04749 -0.0390 0.0134 1.0000
14.000 1.4519 0.05592 0.05052 -0.0383 0.0133 1.0000
14.250 1.4511 0.05899 0.05375 -0.0378 0.0131 1.0000
14.500 1.4489 0.06232 0.05723 -0.0375 0.0129 1.0000
14.750 1.4450 0.06590 0.06097 -0.0374 0.0128 1.0000
15.000 1.4398 0.06970 0.06492 -0.0376 0.0127 1.0000
15.250 1.4338 0.07367 0.06904 -0.0381 0.0125 1.0000
15.500 1.4284 0.07767 0.07317 -0.0389 0.0124 1.0000
15.750 1.4221 0.08189 0.07751 -0.0399 0.0122 1.0000
16.000 1.4139 0.08659 0.08234 -0.0414 0.0121 1.0000
16.250 1.4049 0.09159 0.08747 -0.0432 0.0120 1.0000
16.500 1.3949 0.09690 0.09292 -0.0452 0.0119 1.0000
16.750 1.3838 0.10254 0.09871 -0.0476 0.0118 1.0000
17.000 1.3706 0.10878 0.10511 -0.0505 0.0118 1.0000
17.250 1.3568 0.11538 0.11186 -0.0537 0.0117 1.0000
17.500 1.3406 0.12274 0.11939 -0.0577 0.0117 1.0000
17.750 1.3206 0.13130 0.12816 -0.0626 0.0118 1.0000
18.000 1.2931 0.14226 0.13939 -0.0695 0.0119 1.0000
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