GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 100,000 Max Cl/Cd: 51.99 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe316-il-100000-n5.txt Download as CSV file: xf-goe316-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3729 0.09919 0.09456 -0.0096 1.0000 0.0445
-8.000 -0.3686 0.09603 0.09146 -0.0121 1.0000 0.0459
-7.750 -0.3669 0.09312 0.08862 -0.0162 1.0000 0.0472
-7.500 -0.3597 0.08969 0.08522 -0.0245 1.0000 0.0479
-7.250 -0.3475 0.08594 0.08141 -0.0330 1.0000 0.0482
-7.000 -0.3405 0.08113 0.07671 -0.0311 1.0000 0.0490
-6.750 -0.3318 0.07788 0.07353 -0.0286 1.0000 0.0505
-6.500 -0.3211 0.07463 0.07031 -0.0301 1.0000 0.0520
-6.250 -0.3105 0.07139 0.06709 -0.0323 1.0000 0.0536
-6.000 -0.2885 0.06743 0.06306 -0.0381 0.9878 0.0565
-5.750 -0.2449 0.06193 0.05713 -0.0505 0.9639 0.0598
-5.500 -0.2252 0.05800 0.05331 -0.0509 0.9454 0.0622
-5.250 -0.1976 0.05459 0.04976 -0.0541 0.9232 0.0659
-5.000 -0.1576 0.05160 0.04607 -0.0606 0.9017 0.0721
-4.750 -0.1398 0.04749 0.04204 -0.0608 0.8818 0.0738
-4.500 -0.1191 0.04500 0.03947 -0.0609 0.8627 0.0781
-4.250 -0.0916 0.04252 0.03655 -0.0626 0.8453 0.0878
-4.000 -0.0706 0.04006 0.03400 -0.0624 0.8284 0.0913
-3.750 -0.0430 0.03826 0.03170 -0.0631 0.8121 0.1019
-3.500 -0.0115 0.03452 0.02748 -0.0629 0.7975 0.0689
-3.250 0.0134 0.03251 0.02518 -0.0630 0.7828 0.0748
-3.000 0.0461 0.03012 0.02207 -0.0624 0.7702 0.0583
-2.750 0.0721 0.02816 0.01990 -0.0623 0.7575 0.0570
-2.500 0.0992 0.02655 0.01799 -0.0621 0.7450 0.0560
-2.250 0.1266 0.02516 0.01626 -0.0617 0.7324 0.0553
-2.000 0.1547 0.02405 0.01483 -0.0614 0.7190 0.0563
-1.750 0.1828 0.02315 0.01362 -0.0611 0.7057 0.0578
-1.500 0.2106 0.02215 0.01237 -0.0607 0.6924 0.0577
-1.250 0.2383 0.02124 0.01124 -0.0604 0.6785 0.0575
-1.000 0.2659 0.02044 0.01025 -0.0600 0.6638 0.0576
-0.750 0.2935 0.01972 0.00937 -0.0596 0.6482 0.0579
-0.500 0.3208 0.01911 0.00860 -0.0591 0.6316 0.0584
-0.250 0.3480 0.01857 0.00794 -0.0587 0.6142 0.0595
0.000 0.3743 0.01793 0.00730 -0.0583 0.5963 0.0625
0.250 0.4007 0.01753 0.00683 -0.0579 0.5786 0.0650
0.500 0.4271 0.01717 0.00639 -0.0573 0.5604 0.0663
0.750 0.4535 0.01691 0.00602 -0.0569 0.5423 0.0679
1.000 0.4801 0.01677 0.00572 -0.0564 0.5245 0.0700
1.250 0.5068 0.01668 0.00547 -0.0561 0.5073 0.0726
1.500 0.5339 0.01664 0.00531 -0.0559 0.4906 0.0786
1.750 0.5611 0.01667 0.00523 -0.0557 0.4751 0.0892
2.000 0.5886 0.01667 0.00518 -0.0555 0.4612 0.1080
2.250 0.6156 0.01474 0.00518 -0.0553 0.4495 1.0000
2.750 0.6694 0.01529 0.00535 -0.0548 0.4304 1.0000
3.000 0.6961 0.01559 0.00549 -0.0546 0.4232 1.0000
3.250 0.7231 0.01588 0.00571 -0.0545 0.4160 1.0000
3.500 0.7498 0.01621 0.00591 -0.0543 0.4104 1.0000
3.750 0.7767 0.01652 0.00620 -0.0542 0.4046 1.0000
4.000 0.8035 0.01685 0.00647 -0.0541 0.3992 1.0000
4.250 0.8301 0.01721 0.00674 -0.0540 0.3948 1.0000
4.500 0.8570 0.01756 0.00713 -0.0539 0.3903 1.0000
4.750 0.8838 0.01793 0.00751 -0.0538 0.3864 1.0000
5.000 0.9106 0.01832 0.00789 -0.0537 0.3829 1.0000
5.250 0.9372 0.01873 0.00828 -0.0536 0.3800 1.0000
5.500 0.9639 0.01916 0.00879 -0.0536 0.3768 1.0000
5.750 0.9904 0.01959 0.00931 -0.0535 0.3731 1.0000
6.000 1.0168 0.02004 0.00982 -0.0534 0.3696 1.0000
6.250 1.0433 0.02050 0.01034 -0.0533 0.3664 1.0000
6.500 1.0693 0.02098 0.01087 -0.0532 0.3624 1.0000
6.750 1.0944 0.02139 0.01143 -0.0530 0.3554 1.0000
7.000 1.1198 0.02179 0.01179 -0.0527 0.3484 1.0000
7.250 1.1440 0.02220 0.01242 -0.0523 0.3406 1.0000
7.500 1.1691 0.02262 0.01287 -0.0520 0.3344 1.0000
7.750 1.1933 0.02310 0.01353 -0.0517 0.3281 1.0000
8.000 1.2174 0.02352 0.01411 -0.0513 0.3210 1.0000
8.250 1.2413 0.02397 0.01467 -0.0509 0.3142 1.0000
8.500 1.2644 0.02443 0.01536 -0.0504 0.3069 1.0000
8.750 1.2879 0.02485 0.01587 -0.0500 0.3001 1.0000
9.000 1.3097 0.02532 0.01667 -0.0493 0.2916 1.0000
9.250 1.3315 0.02571 0.01725 -0.0486 0.2827 1.0000
9.500 1.3511 0.02601 0.01777 -0.0477 0.2687 1.0000
9.750 1.3694 0.02634 0.01839 -0.0467 0.2477 1.0000
10.000 1.3862 0.02678 0.01898 -0.0456 0.2117 1.0000
10.250 1.3924 0.02806 0.01986 -0.0436 0.1628 1.0000
10.500 1.3937 0.03015 0.02174 -0.0415 0.1296 1.0000
10.750 1.3932 0.03233 0.02386 -0.0392 0.1044 1.0000
11.000 1.3882 0.03456 0.02608 -0.0366 0.0854 1.0000
11.250 1.3797 0.03732 0.02883 -0.0346 0.0738 1.0000
11.500 1.3697 0.04063 0.03219 -0.0337 0.0667 1.0000
11.750 1.3580 0.04456 0.03621 -0.0336 0.0616 1.0000
12.250 1.3322 0.05380 0.04574 -0.0352 0.0545 1.0000
12.500 1.3181 0.05901 0.05111 -0.0366 0.0517 1.0000
12.750 1.3021 0.06468 0.05691 -0.0384 0.0496 1.0000
13.000 1.2854 0.07058 0.06292 -0.0402 0.0478 1.0000
13.250 1.2708 0.07616 0.06859 -0.0418 0.0459 1.0000
13.500 1.2615 0.08100 0.07359 -0.0430 0.0431 1.0000
13.750 1.2518 0.08592 0.07863 -0.0443 0.0405 1.0000
14.000 1.2424 0.09089 0.08369 -0.0458 0.0384 1.0000
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Polar data table (+)
Polar graphs
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