GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 100,000 Max Cl/Cd: 57.11 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe328-il-100000-n5.txt Download as CSV file: xf-goe328-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3699 0.10595 0.10095 -0.0203 1.0000 0.0511
-8.250 -0.3706 0.10391 0.09897 -0.0241 1.0000 0.0515
-8.000 -0.3693 0.10146 0.09657 -0.0284 1.0000 0.0518
-7.750 -0.3624 0.09842 0.09355 -0.0339 1.0000 0.0519
-7.500 -0.3556 0.09369 0.08888 -0.0339 1.0000 0.0525
-7.250 -0.3460 0.08954 0.08476 -0.0288 1.0000 0.0538
-7.000 -0.3379 0.08655 0.08181 -0.0285 1.0000 0.0551
-6.750 -0.3318 0.08376 0.07907 -0.0296 1.0000 0.0564
-6.500 -0.3279 0.08115 0.07651 -0.0306 1.0000 0.0576
-6.250 -0.3267 0.07880 0.07423 -0.0312 1.0000 0.0589
-6.000 -0.3206 0.07618 0.07162 -0.0333 0.9978 0.0606
-5.750 -0.2639 0.07178 0.06678 -0.0532 0.9851 0.0642
-5.500 -0.2430 0.06614 0.06118 -0.0559 0.9779 0.0652
-5.250 -0.2226 0.06243 0.05753 -0.0563 0.9721 0.0673
-5.000 -0.1943 0.05912 0.05416 -0.0599 0.9637 0.0706
-4.750 -0.1402 0.05664 0.05105 -0.0715 0.9532 0.0781
-4.500 -0.1136 0.05150 0.04591 -0.0746 0.9467 0.0793
-4.250 -0.0903 0.04817 0.04261 -0.0759 0.9363 0.0809
-4.000 -0.0613 0.04537 0.03972 -0.0781 0.9263 0.0836
-3.750 -0.0168 0.04359 0.03729 -0.0834 0.9162 0.0934
-3.500 0.0036 0.04004 0.03389 -0.0837 0.9033 0.0960
-3.250 0.0359 0.03857 0.03202 -0.0856 0.8898 0.1087
-3.000 0.0723 0.03353 0.02646 -0.0865 0.8786 0.0625
-2.750 0.1000 0.03111 0.02385 -0.0871 0.8674 0.0590
-2.250 0.1626 0.02710 0.01879 -0.0875 0.8462 0.0517
-2.000 0.1906 0.02547 0.01692 -0.0876 0.8361 0.0513
-1.750 0.2191 0.02422 0.01537 -0.0875 0.8259 0.0515
-1.500 0.2469 0.02291 0.01383 -0.0875 0.8149 0.0531
-1.250 0.2744 0.02188 0.01265 -0.0874 0.8045 0.0542
-1.000 0.3026 0.02093 0.01144 -0.0870 0.7945 0.0539
-0.750 0.3303 0.02011 0.01044 -0.0867 0.7831 0.0538
-0.500 0.3578 0.01936 0.00955 -0.0863 0.7721 0.0540
-0.250 0.3852 0.01869 0.00877 -0.0858 0.7616 0.0545
0.000 0.4123 0.01811 0.00812 -0.0854 0.7499 0.0552
0.250 0.4392 0.01760 0.00758 -0.0849 0.7377 0.0562
0.500 0.4659 0.01716 0.00712 -0.0844 0.7255 0.0577
0.750 0.4925 0.01685 0.00676 -0.0839 0.7127 0.0615
1.000 0.5188 0.01659 0.00642 -0.0832 0.6985 0.0645
1.250 0.5449 0.01624 0.00602 -0.0826 0.6829 0.0671
1.500 0.5715 0.01606 0.00575 -0.0821 0.6666 0.0707
1.750 0.5986 0.01595 0.00553 -0.0816 0.6501 0.0761
2.000 0.6257 0.01583 0.00537 -0.0812 0.6338 0.0871
2.250 0.6485 0.01374 0.00532 -0.0800 0.6185 1.0000
2.500 0.6753 0.01390 0.00525 -0.0795 0.6021 1.0000
2.750 0.7019 0.01409 0.00527 -0.0791 0.5853 1.0000
3.000 0.7285 0.01428 0.00534 -0.0787 0.5684 1.0000
3.250 0.7549 0.01449 0.00543 -0.0783 0.5517 1.0000
3.500 0.7813 0.01472 0.00556 -0.0780 0.5351 1.0000
4.000 0.8336 0.01524 0.00590 -0.0772 0.5026 1.0000
4.250 0.8596 0.01554 0.00612 -0.0769 0.4876 1.0000
4.750 0.9114 0.01620 0.00668 -0.0762 0.4609 1.0000
5.000 0.9372 0.01657 0.00703 -0.0758 0.4493 1.0000
5.250 0.9630 0.01695 0.00740 -0.0755 0.4387 1.0000
5.500 0.9886 0.01737 0.00781 -0.0752 0.4288 1.0000
5.750 1.0144 0.01778 0.00828 -0.0749 0.4188 1.0000
6.000 1.0400 0.01823 0.00873 -0.0745 0.4102 1.0000
6.250 1.0655 0.01867 0.00927 -0.0742 0.4007 1.0000
6.500 1.0906 0.01912 0.00979 -0.0738 0.3904 1.0000
6.750 1.1150 0.01956 0.01028 -0.0733 0.3784 1.0000
7.000 1.1387 0.01997 0.01078 -0.0727 0.3638 1.0000
7.250 1.1616 0.02034 0.01125 -0.0721 0.3463 1.0000
7.500 1.1836 0.02073 0.01170 -0.0712 0.3254 1.0000
7.750 1.2040 0.02117 0.01215 -0.0703 0.2968 1.0000
8.000 1.2229 0.02181 0.01273 -0.0691 0.2629 1.0000
8.250 1.2401 0.02270 0.01351 -0.0679 0.2180 1.0000
8.500 1.2421 0.02529 0.01519 -0.0653 0.0963 1.0000
8.750 1.2499 0.02738 0.01707 -0.0631 0.0645 1.0000
9.000 1.2593 0.02911 0.01883 -0.0611 0.0542 1.0000
9.250 1.2669 0.03082 0.02063 -0.0589 0.0476 1.0000
9.500 1.2729 0.03247 0.02243 -0.0565 0.0433 1.0000
9.750 1.2759 0.03407 0.02421 -0.0537 0.0404 1.0000
10.000 1.2761 0.03594 0.02621 -0.0511 0.0384 1.0000
10.250 1.2725 0.03826 0.02863 -0.0487 0.0368 1.0000
10.500 1.2733 0.04043 0.03094 -0.0469 0.0352 1.0000
10.750 1.2751 0.04263 0.03330 -0.0455 0.0334 1.0000
11.000 1.2765 0.04499 0.03578 -0.0443 0.0318 1.0000
11.250 1.2775 0.04749 0.03835 -0.0433 0.0305 1.0000
11.500 1.2784 0.05005 0.04097 -0.0423 0.0296 1.0000
11.750 1.2807 0.05256 0.04347 -0.0409 0.0288 1.0000
12.000 1.2884 0.05464 0.04571 -0.0397 0.0280 1.0000
12.250 1.2960 0.05681 0.04805 -0.0385 0.0269 1.0000
12.500 1.3019 0.05919 0.05059 -0.0376 0.0257 1.0000
12.750 1.3064 0.06173 0.05327 -0.0370 0.0247 1.0000
13.000 1.3100 0.06438 0.05603 -0.0364 0.0239 1.0000
13.250 1.3143 0.06705 0.05879 -0.0358 0.0232 1.0000
13.500 1.3199 0.06975 0.06157 -0.0350 0.0227 1.0000
13.750 1.3246 0.07279 0.06476 -0.0342 0.0223 1.0000
14.000 1.3224 0.07655 0.06880 -0.0341 0.0220 1.0000
14.250 1.3174 0.08071 0.07323 -0.0344 0.0218 1.0000
14.500 1.3095 0.08528 0.07808 -0.0351 0.0216 1.0000
14.750 1.2990 0.09029 0.08336 -0.0364 0.0215 1.0000
15.000 1.2865 0.09573 0.08906 -0.0382 0.0213 1.0000
15.250 1.2726 0.10165 0.09523 -0.0407 0.0212 1.0000
15.500 1.2576 0.10808 0.10190 -0.0437 0.0211 1.0000
15.750 1.2418 0.11504 0.10910 -0.0474 0.0210 1.0000
16.000 1.2247 0.12264 0.11692 -0.0519 0.0210 1.0000
16.250 1.2070 0.13084 0.12533 -0.0569 0.0211 1.0000
16.500 1.1883 0.13984 0.13452 -0.0628 0.0212 1.0000
16.750 1.1693 0.14960 0.14444 -0.0693 0.0214 1.0000
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Polar data table (+)
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