GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL (goe321-il) Reynolds number: 200,000 Max Cl/Cd: 73.73 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe321-il-200000-n5.txt Download as CSV file: xf-goe321-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2771 0.09016 0.08609 -0.0247 0.7544 0.0372
-7.750 -0.2704 0.08710 0.08300 -0.0267 0.7467 0.0380
-7.500 -0.2655 0.08393 0.07981 -0.0300 0.7395 0.0396
-7.250 -0.2544 0.07800 0.07375 -0.0452 0.7328 0.0410
-7.000 -0.2390 0.07340 0.06900 -0.0511 0.7270 0.0411
-6.750 -0.2278 0.06996 0.06558 -0.0507 0.7202 0.0414
-6.500 -0.2144 0.06727 0.06284 -0.0505 0.7138 0.0418
-6.250 -0.1988 0.06451 0.06004 -0.0515 0.7075 0.0423
-6.000 -0.1811 0.06157 0.05702 -0.0535 0.7006 0.0430
-5.750 -0.1618 0.05855 0.05389 -0.0559 0.6947 0.0440
-5.500 -0.1263 0.05361 0.04846 -0.0641 0.6883 0.0482
-5.250 -0.1033 0.05006 0.04465 -0.0660 0.6820 0.0482
-5.000 -0.0807 0.04683 0.04119 -0.0672 0.6764 0.0483
-4.750 -0.0621 0.04128 0.03557 -0.0682 0.6702 0.0414
-4.500 -0.0408 0.03974 0.03401 -0.0683 0.6641 0.0399
-4.250 -0.0154 0.03693 0.03097 -0.0692 0.6582 0.0397
-4.000 0.0111 0.03409 0.02786 -0.0700 0.6519 0.0398
-3.750 0.0371 0.03167 0.02518 -0.0705 0.6467 0.0391
-3.500 0.0642 0.02917 0.02240 -0.0709 0.6405 0.0384
-3.250 0.0918 0.02683 0.01973 -0.0711 0.6345 0.0380
-3.000 0.1196 0.02477 0.01731 -0.0712 0.6294 0.0379
-2.750 0.1479 0.02302 0.01526 -0.0713 0.6233 0.0381
-2.500 0.1763 0.02164 0.01358 -0.0712 0.6182 0.0393
-2.250 0.2046 0.02035 0.01197 -0.0712 0.6139 0.0397
-2.000 0.2333 0.01922 0.01061 -0.0712 0.6087 0.0399
-1.750 0.2619 0.01828 0.00944 -0.0711 0.6037 0.0402
-1.500 0.2902 0.01752 0.00844 -0.0709 0.5990 0.0407
-1.250 0.3187 0.01688 0.00767 -0.0709 0.5930 0.0411
-1.000 0.3467 0.01628 0.00702 -0.0708 0.5869 0.0418
-0.750 0.3745 0.01596 0.00665 -0.0708 0.5805 0.0432
-0.500 0.4026 0.01564 0.00629 -0.0707 0.5722 0.0448
-0.250 0.4303 0.01529 0.00584 -0.0705 0.5647 0.0461
0.000 0.4582 0.01494 0.00546 -0.0704 0.5567 0.0471
0.250 0.4860 0.01469 0.00512 -0.0702 0.5507 0.0482
0.500 0.5139 0.01440 0.00489 -0.0703 0.5456 0.0499
0.750 0.5420 0.01424 0.00476 -0.0703 0.5401 0.0522
1.000 0.5699 0.01416 0.00462 -0.0702 0.5346 0.0561
1.250 0.5979 0.01403 0.00452 -0.0702 0.5284 0.0605
1.500 0.6260 0.01396 0.00442 -0.0702 0.5215 0.0663
1.750 0.6538 0.01390 0.00432 -0.0701 0.5156 0.0772
2.000 0.6818 0.01377 0.00432 -0.0702 0.5080 0.1052
2.500 0.7369 0.01189 0.00442 -0.0700 0.4928 1.0000
2.750 0.7644 0.01202 0.00446 -0.0699 0.4855 1.0000
3.000 0.7919 0.01216 0.00453 -0.0698 0.4786 1.0000
3.250 0.8194 0.01228 0.00462 -0.0697 0.4705 1.0000
3.500 0.8467 0.01243 0.00471 -0.0696 0.4622 1.0000
3.750 0.8739 0.01256 0.00481 -0.0695 0.4522 1.0000
4.000 0.9011 0.01271 0.00493 -0.0694 0.4409 1.0000
4.250 0.9280 0.01287 0.00505 -0.0693 0.4275 1.0000
4.500 0.9545 0.01305 0.00518 -0.0691 0.4103 1.0000
4.750 0.9801 0.01330 0.00530 -0.0689 0.3885 1.0000
5.000 1.0049 0.01363 0.00550 -0.0685 0.3640 1.0000
5.500 1.0524 0.01454 0.00612 -0.0676 0.3221 1.0000
5.750 1.0759 0.01501 0.00650 -0.0671 0.3054 1.0000
6.000 1.0993 0.01549 0.00690 -0.0666 0.2908 1.0000
6.250 1.1224 0.01598 0.00733 -0.0661 0.2770 1.0000
6.500 1.1457 0.01644 0.00776 -0.0657 0.2637 1.0000
6.750 1.1686 0.01693 0.00820 -0.0651 0.2518 1.0000
7.000 1.1909 0.01743 0.00868 -0.0646 0.2414 1.0000
7.250 1.2125 0.01797 0.00918 -0.0639 0.2324 1.0000
7.500 1.2345 0.01847 0.00968 -0.0633 0.2250 1.0000
7.750 1.2553 0.01903 0.01023 -0.0625 0.2189 1.0000
8.000 1.2761 0.01957 0.01078 -0.0617 0.2142 1.0000
8.250 1.2968 0.02011 0.01136 -0.0610 0.2100 1.0000
8.500 1.3164 0.02070 0.01196 -0.0600 0.2064 1.0000
8.750 1.3347 0.02134 0.01262 -0.0590 0.2035 1.0000
9.000 1.3530 0.02197 0.01328 -0.0579 0.2011 1.0000
9.250 1.3716 0.02256 0.01395 -0.0569 0.1989 1.0000
9.500 1.3892 0.02319 0.01464 -0.0558 0.1968 1.0000
9.750 1.4042 0.02385 0.01537 -0.0543 0.1946 1.0000
10.000 1.4185 0.02459 0.01616 -0.0528 0.1925 1.0000
10.250 1.4322 0.02542 0.01703 -0.0513 0.1905 1.0000
10.500 1.4448 0.02636 0.01798 -0.0499 0.1881 1.0000
10.750 1.4593 0.02720 0.01891 -0.0488 0.1855 1.0000
11.000 1.4734 0.02807 0.01991 -0.0478 0.1825 1.0000
11.250 1.4863 0.02905 0.02099 -0.0467 0.1795 1.0000
11.500 1.4981 0.03017 0.02217 -0.0457 0.1766 1.0000
11.750 1.5085 0.03143 0.02344 -0.0447 0.1737 1.0000
12.000 1.5205 0.03261 0.02471 -0.0439 0.1712 1.0000
12.250 1.5323 0.03384 0.02610 -0.0433 0.1681 1.0000
12.500 1.5419 0.03526 0.02766 -0.0427 0.1641 1.0000
12.750 1.5491 0.03692 0.02937 -0.0421 0.1601 1.0000
13.000 1.5558 0.03866 0.03113 -0.0415 0.1565 1.0000
13.250 1.5644 0.04032 0.03301 -0.0412 0.1520 1.0000
13.500 1.5693 0.04235 0.03515 -0.0410 0.1463 1.0000
13.750 1.5718 0.04464 0.03751 -0.0407 0.1408 1.0000
14.000 1.5778 0.04668 0.03972 -0.0407 0.1334 1.0000
14.250 1.5807 0.04905 0.04219 -0.0406 0.1266 1.0000
14.500 1.5833 0.05152 0.04476 -0.0405 0.1151 1.0000
14.750 1.5746 0.05531 0.04849 -0.0408 0.0926 1.0000
15.000 1.5553 0.06050 0.05354 -0.0412 0.0757 1.0000
15.250 1.5380 0.06563 0.05864 -0.0417 0.0622 1.0000
15.500 1.5205 0.07102 0.06404 -0.0425 0.0508 1.0000
15.750 1.5029 0.07664 0.06970 -0.0435 0.0423 1.0000
16.000 1.4860 0.08232 0.07546 -0.0448 0.0366 1.0000
16.250 1.4694 0.08818 0.08141 -0.0462 0.0328 1.0000
16.500 1.4529 0.09419 0.08756 -0.0479 0.0304 1.0000
16.750 1.4354 0.10055 0.09405 -0.0499 0.0287 1.0000
17.000 1.4188 0.10699 0.10063 -0.0521 0.0274 1.0000
17.250 1.4009 0.11382 0.10761 -0.0547 0.0265 1.0000
17.500 1.3819 0.12102 0.11497 -0.0576 0.0259 1.0000
17.750 1.3624 0.12851 0.12262 -0.0608 0.0254 1.0000
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