GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 100,000 Max Cl/Cd: 63.86 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe369-il-100000-n5.txt Download as CSV file: xf-goe369-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2726 0.09145 0.08709 -0.0231 1.0000 0.0222
-6.750 -0.2677 0.08858 0.08429 -0.0230 1.0000 0.0226
-6.500 -0.2633 0.08599 0.08179 -0.0232 1.0000 0.0229
-6.250 -0.2596 0.08360 0.07949 -0.0234 1.0000 0.0233
-6.000 -0.2452 0.08049 0.07641 -0.0263 0.9942 0.0238
-5.750 -0.2140 0.07628 0.07219 -0.0332 0.9790 0.0248
-5.500 -0.1826 0.07230 0.06816 -0.0399 0.9617 0.0259
-5.250 -0.1471 0.06833 0.06414 -0.0474 0.9446 0.0279
-5.000 -0.0987 0.06494 0.06059 -0.0580 0.9265 0.0298
-4.750 -0.0477 0.06187 0.05728 -0.0680 0.9094 0.0303
-4.500 -0.0147 0.05755 0.05286 -0.0727 0.8935 0.0306
-4.250 0.0035 0.05289 0.04820 -0.0736 0.8783 0.0317
-4.000 0.0331 0.04958 0.04477 -0.0767 0.8632 0.0332
-3.750 0.0656 0.04659 0.04160 -0.0801 0.8487 0.0353
-3.500 0.1037 0.04413 0.03885 -0.0839 0.8353 0.0383
-3.250 0.1438 0.04197 0.03628 -0.0872 0.8233 0.0399
-3.000 0.1624 0.03847 0.03278 -0.0877 0.8115 0.0418
-2.750 0.1901 0.03624 0.03037 -0.0888 0.8005 0.0454
-2.500 0.2222 0.03412 0.02795 -0.0904 0.7909 0.0533
-2.250 0.2538 0.03275 0.02623 -0.0913 0.7814 0.0655
-2.000 0.2801 0.03105 0.02436 -0.0917 0.7720 0.0770
-1.750 0.3058 0.02864 0.02181 -0.0922 0.7642 0.0845
-1.500 0.3426 0.02674 0.01935 -0.0916 0.7556 0.0490
-1.250 0.3725 0.02438 0.01664 -0.0913 0.7486 0.0348
-1.000 0.4021 0.02281 0.01467 -0.0908 0.7402 0.0324
-0.750 0.4303 0.02167 0.01323 -0.0905 0.7329 0.0352
-0.500 0.4586 0.02046 0.01169 -0.0899 0.7240 0.0346
-0.250 0.4865 0.01938 0.01029 -0.0891 0.7147 0.0346
0.000 0.5140 0.01856 0.00917 -0.0883 0.7056 0.0376
0.250 0.5408 0.01774 0.00816 -0.0876 0.6958 0.0404
0.500 0.5673 0.01698 0.00732 -0.0870 0.6881 0.0429
0.750 0.5935 0.01659 0.00685 -0.0864 0.6797 0.0502
1.000 0.6199 0.01614 0.00629 -0.0857 0.6725 0.0547
1.250 0.6468 0.01600 0.00604 -0.0853 0.6642 0.0653
1.500 0.6737 0.01589 0.00581 -0.0849 0.6565 0.0768
1.750 0.7006 0.01568 0.00565 -0.0845 0.6485 0.1238
2.250 0.7605 0.01434 0.00558 -0.0851 0.6309 1.0000
2.500 0.7858 0.01450 0.00565 -0.0845 0.6194 1.0000
2.750 0.8110 0.01466 0.00570 -0.0837 0.6075 1.0000
3.000 0.8361 0.01480 0.00576 -0.0830 0.5951 1.0000
3.250 0.8612 0.01495 0.00585 -0.0823 0.5823 1.0000
3.500 0.8860 0.01509 0.00593 -0.0815 0.5683 1.0000
3.750 0.9107 0.01524 0.00605 -0.0807 0.5539 1.0000
4.000 0.9355 0.01541 0.00622 -0.0800 0.5398 1.0000
4.250 0.9599 0.01559 0.00639 -0.0793 0.5234 1.0000
4.500 0.9839 0.01576 0.00655 -0.0784 0.5034 1.0000
4.750 1.0073 0.01595 0.00672 -0.0774 0.4805 1.0000
5.000 1.0303 0.01619 0.00690 -0.0765 0.4539 1.0000
5.250 1.0531 0.01649 0.00714 -0.0755 0.4264 1.0000
5.500 1.0755 0.01687 0.00745 -0.0745 0.3991 1.0000
5.750 1.0968 0.01734 0.00784 -0.0734 0.3694 1.0000
6.000 1.1173 0.01793 0.00830 -0.0722 0.3388 1.0000
6.250 1.1370 0.01860 0.00885 -0.0710 0.3080 1.0000
6.500 1.1566 0.01931 0.00948 -0.0699 0.2781 1.0000
6.750 1.1760 0.02005 0.01019 -0.0687 0.2501 1.0000
7.000 1.1948 0.02084 0.01092 -0.0675 0.2251 1.0000
7.500 1.2301 0.02262 0.01258 -0.0650 0.1888 1.0000
7.750 1.2468 0.02359 0.01354 -0.0636 0.1758 1.0000
8.000 1.2643 0.02450 0.01451 -0.0623 0.1646 1.0000
8.250 1.2812 0.02545 0.01553 -0.0609 0.1553 1.0000
8.500 1.2966 0.02650 0.01660 -0.0594 0.1474 1.0000
8.750 1.3140 0.02740 0.01766 -0.0581 0.1395 1.0000
9.000 1.3291 0.02845 0.01881 -0.0567 0.1335 1.0000
9.250 1.3455 0.02945 0.01996 -0.0553 0.1276 1.0000
9.500 1.3608 0.03045 0.02111 -0.0539 0.1221 1.0000
9.750 1.3746 0.03162 0.02232 -0.0523 0.1179 1.0000
10.000 1.3904 0.03269 0.02366 -0.0510 0.1135 1.0000
10.250 1.4044 0.03383 0.02498 -0.0494 0.1099 1.0000
10.500 1.4134 0.03494 0.02616 -0.0474 0.1055 1.0000
10.750 1.4198 0.03594 0.02749 -0.0453 0.0984 1.0000
11.000 1.4208 0.03717 0.02874 -0.0432 0.0911 1.0000
11.250 1.4272 0.03839 0.03026 -0.0417 0.0829 1.0000
11.500 1.4303 0.04003 0.03202 -0.0404 0.0764 1.0000
11.750 1.4375 0.04155 0.03384 -0.0395 0.0684 1.0000
12.000 1.4418 0.04342 0.03583 -0.0388 0.0537 1.0000
12.250 1.4408 0.04608 0.03849 -0.0382 0.0366 1.0000
12.500 1.4338 0.04956 0.04194 -0.0377 0.0240 1.0000
12.750 1.4250 0.05346 0.04588 -0.0376 0.0201 1.0000
13.000 1.4141 0.05782 0.05033 -0.0379 0.0175 1.0000
13.250 1.4030 0.06241 0.05509 -0.0386 0.0162 1.0000
13.500 1.3910 0.06733 0.06019 -0.0397 0.0153 1.0000
13.750 1.3781 0.07263 0.06572 -0.0412 0.0146 1.0000
14.000 1.3638 0.07839 0.07170 -0.0432 0.0142 1.0000
14.250 1.3487 0.08462 0.07815 -0.0457 0.0141 1.0000
14.500 1.3312 0.09169 0.08544 -0.0489 0.0139 1.0000
14.750 1.3142 0.09911 0.09307 -0.0525 0.0140 1.0000
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Polar data table (+)
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