GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 500,000 Max Cl/Cd: 106.69 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe323-il-500000.txt Download as CSV file: xf-goe323-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3366 0.09923 0.09580 -0.0007 0.6434 0.0275
-8.250 -0.3419 0.09435 0.09092 -0.0098 0.6410 0.0284
-8.000 -0.3391 0.09003 0.08660 -0.0155 0.6380 0.0284
-7.750 -0.3310 0.08628 0.08286 -0.0156 0.6343 0.0286
-7.500 -0.3198 0.08349 0.08007 -0.0154 0.6305 0.0288
-7.250 -0.3079 0.08064 0.07720 -0.0167 0.6271 0.0290
-7.000 -0.2952 0.07766 0.07418 -0.0190 0.6240 0.0292
-6.750 -0.2811 0.07447 0.07097 -0.0221 0.6210 0.0296
-6.500 -0.2654 0.07107 0.06756 -0.0258 0.6179 0.0301
-6.250 -0.2478 0.06747 0.06392 -0.0299 0.6147 0.0309
-6.000 -0.2100 0.05881 0.05491 -0.0453 0.6125 0.0330
-5.750 -0.1965 0.05508 0.05116 -0.0460 0.6097 0.0333
-5.500 -0.1788 0.05272 0.04874 -0.0466 0.6067 0.0335
-5.250 -0.1588 0.05042 0.04641 -0.0475 0.6037 0.0338
-5.000 -0.1369 0.04804 0.04398 -0.0487 0.6005 0.0343
-4.750 -0.1133 0.04552 0.04138 -0.0502 0.5976 0.0350
-4.500 -0.0742 0.04054 0.03582 -0.0540 0.5952 0.0383
-4.250 -0.0545 0.03667 0.03189 -0.0550 0.5927 0.0388
-4.000 -0.0318 0.03494 0.03010 -0.0553 0.5900 0.0391
-3.750 -0.0076 0.03336 0.02846 -0.0557 0.5873 0.0396
-3.500 0.0178 0.03171 0.02674 -0.0561 0.5844 0.0404
-3.250 0.0445 0.02990 0.02479 -0.0565 0.5813 0.0418
-3.000 0.0752 0.02646 0.02074 -0.0565 0.5784 0.0452
-2.750 0.1005 0.02493 0.01917 -0.0567 0.5748 0.0457
-2.500 0.1266 0.02386 0.01804 -0.0568 0.5708 0.0466
-2.250 0.1538 0.02278 0.01689 -0.0568 0.5669 0.0482
-2.000 0.1836 0.02142 0.01499 -0.0563 0.5633 0.0527
-1.750 0.2101 0.01993 0.01352 -0.0565 0.5602 0.0537
-1.500 0.2374 0.01907 0.01259 -0.0565 0.5572 0.0551
-1.250 0.2656 0.01839 0.01179 -0.0564 0.5541 0.0578
-0.250 0.3820 0.01392 0.00636 -0.0548 0.5414 0.0449
0.000 0.4103 0.01343 0.00580 -0.0546 0.5381 0.0448
0.250 0.4385 0.01272 0.00510 -0.0545 0.5346 0.0451
0.500 0.4664 0.01216 0.00457 -0.0543 0.5307 0.0457
0.750 0.4944 0.01180 0.00422 -0.0542 0.5270 0.0466
1.000 0.5223 0.01163 0.00402 -0.0540 0.5230 0.0483
1.250 0.5506 0.01141 0.00384 -0.0539 0.5189 0.0501
1.500 0.5789 0.01119 0.00363 -0.0538 0.5140 0.0513
1.750 0.6068 0.01092 0.00335 -0.0537 0.5092 0.0531
2.000 0.6349 0.01076 0.00320 -0.0536 0.5045 0.0560
2.250 0.6634 0.01063 0.00312 -0.0536 0.4993 0.0598
2.500 0.6917 0.01049 0.00298 -0.0535 0.4941 0.0663
2.750 0.7198 0.01042 0.00291 -0.0534 0.4888 0.0795
3.000 0.7526 0.00833 0.00303 -0.0548 0.4824 1.0000
3.250 0.7803 0.00840 0.00301 -0.0546 0.4762 1.0000
3.500 0.8082 0.00846 0.00304 -0.0545 0.4696 1.0000
3.750 0.8360 0.00852 0.00307 -0.0544 0.4619 1.0000
4.000 0.8637 0.00860 0.00311 -0.0543 0.4538 1.0000
4.250 0.8913 0.00869 0.00315 -0.0542 0.4440 1.0000
4.500 0.9189 0.00879 0.00322 -0.0541 0.4315 1.0000
4.750 0.9461 0.00892 0.00329 -0.0540 0.4159 1.0000
5.000 0.9730 0.00912 0.00340 -0.0538 0.3980 1.0000
5.250 0.9994 0.00938 0.00356 -0.0537 0.3801 1.0000
5.500 1.0257 0.00967 0.00376 -0.0535 0.3633 1.0000
5.750 1.0517 0.00999 0.00400 -0.0533 0.3482 1.0000
6.000 1.0774 0.01034 0.00427 -0.0531 0.3347 1.0000
6.250 1.1035 0.01066 0.00454 -0.0530 0.3226 1.0000
6.500 1.1294 0.01098 0.00482 -0.0528 0.3116 1.0000
6.750 1.1549 0.01134 0.00513 -0.0526 0.3016 1.0000
7.000 1.1808 0.01164 0.00542 -0.0525 0.2925 1.0000
7.250 1.2064 0.01198 0.00574 -0.0523 0.2841 1.0000
7.500 1.2319 0.01231 0.00605 -0.0522 0.2759 1.0000
7.750 1.2572 0.01265 0.00638 -0.0520 0.2688 1.0000
8.000 1.2825 0.01298 0.00671 -0.0518 0.2615 1.0000
8.250 1.3071 0.01337 0.00709 -0.0515 0.2548 1.0000
8.500 1.3323 0.01369 0.00743 -0.0514 0.2473 1.0000
8.750 1.3563 0.01411 0.00782 -0.0511 0.2392 1.0000
9.000 1.3807 0.01447 0.00820 -0.0509 0.2312 1.0000
9.250 1.4041 0.01491 0.00863 -0.0505 0.2246 1.0000
9.500 1.4282 0.01528 0.00902 -0.0503 0.2178 1.0000
9.750 1.4502 0.01581 0.00953 -0.0499 0.2110 1.0000
10.000 1.4740 0.01616 0.00994 -0.0496 0.2050 1.0000
10.250 1.4953 0.01672 0.01048 -0.0491 0.1983 1.0000
10.500 1.5176 0.01716 0.01097 -0.0487 0.1926 1.0000
10.750 1.5380 0.01773 0.01155 -0.0482 0.1854 1.0000
11.000 1.5583 0.01829 0.01213 -0.0476 0.1787 1.0000
11.250 1.5768 0.01894 0.01280 -0.0469 0.1715 1.0000
11.500 1.5946 0.01962 0.01350 -0.0461 0.1647 1.0000
11.750 1.6094 0.02043 0.01433 -0.0451 0.1573 1.0000
12.000 1.6217 0.02132 0.01525 -0.0438 0.1501 1.0000
12.250 1.6288 0.02273 0.01666 -0.0428 0.1411 1.0000
12.500 1.6377 0.02425 0.01820 -0.0424 0.1311 1.0000
12.750 1.6428 0.02638 0.02033 -0.0424 0.1195 1.0000
13.000 1.6438 0.02910 0.02301 -0.0426 0.1067 1.0000
13.250 1.6408 0.03217 0.02604 -0.0426 0.0956 1.0000
13.500 1.6371 0.03522 0.02908 -0.0425 0.0875 1.0000
13.750 1.6320 0.03838 0.03226 -0.0423 0.0808 1.0000
14.000 1.6256 0.04166 0.03555 -0.0420 0.0738 1.0000
14.250 1.6178 0.04511 0.03900 -0.0418 0.0639 1.0000
14.500 1.6009 0.04956 0.04339 -0.0416 0.0471 1.0000
14.750 1.5761 0.05498 0.04872 -0.0417 0.0330 1.0000
15.000 1.5590 0.05988 0.05365 -0.0420 0.0273 1.0000
15.250 1.5465 0.06445 0.05829 -0.0426 0.0246 1.0000
15.500 1.5385 0.06858 0.06252 -0.0431 0.0232 1.0000
15.750 1.5292 0.07299 0.06701 -0.0438 0.0222 1.0000
16.000 1.5185 0.07767 0.07180 -0.0447 0.0214 1.0000
16.250 1.5064 0.08270 0.07693 -0.0458 0.0207 1.0000
16.500 1.4977 0.08731 0.08165 -0.0468 0.0202 1.0000
16.750 1.4875 0.09221 0.08668 -0.0480 0.0198 1.0000
17.000 1.4763 0.09738 0.09196 -0.0495 0.0194 1.0000
17.250 1.4639 0.10282 0.09752 -0.0511 0.0191 1.0000
17.500 1.4505 0.10849 0.10330 -0.0528 0.0187 1.0000
17.750 1.4368 0.11432 0.10924 -0.0548 0.0185 1.0000
18.000 1.4227 0.12032 0.11535 -0.0570 0.0182 1.0000
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Polar data table (+)
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