GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 500,000 Max Cl/Cd: 96.28 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe323-il-500000-n5.txt Download as CSV file: xf-goe323-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3594 0.10579 0.10217 0.0028 0.6062 0.0198
-9.000 -0.3540 0.10233 0.09870 0.0011 0.6032 0.0200
-8.750 -0.3515 0.09811 0.09448 -0.0018 0.6005 0.0215
-8.500 -0.3411 0.09607 0.09243 -0.0025 0.5972 0.0220
-7.500 -0.3146 0.08307 0.07943 -0.0114 0.5854 0.0230
-7.250 -0.3073 0.07913 0.07549 -0.0156 0.5827 0.0228
-7.000 -0.2953 0.07491 0.07123 -0.0206 0.5801 0.0228
-6.500 -0.2633 0.06636 0.06259 -0.0310 0.5754 0.0238
-6.250 -0.2446 0.06191 0.05807 -0.0359 0.5729 0.0238
-6.000 -0.2242 0.05752 0.05360 -0.0404 0.5703 0.0238
-5.750 -0.2020 0.05309 0.04905 -0.0445 0.5678 0.0238
-5.500 -0.1785 0.04853 0.04433 -0.0482 0.5654 0.0240
-5.250 -0.1513 0.03952 0.03490 -0.0536 0.5635 0.0248
-5.000 -0.1279 0.03611 0.03128 -0.0549 0.5610 0.0249
-4.750 -0.1034 0.03367 0.02870 -0.0557 0.5585 0.0251
-4.500 -0.0783 0.03122 0.02609 -0.0564 0.5558 0.0252
-4.250 -0.0527 0.02873 0.02340 -0.0568 0.5532 0.0254
-4.000 -0.0266 0.02705 0.02157 -0.0571 0.5507 0.0258
-3.750 -0.0002 0.02529 0.01963 -0.0573 0.5483 0.0262
-3.500 0.0262 0.02241 0.01638 -0.0573 0.5461 0.0265
-3.000 0.0800 0.01802 0.01131 -0.0569 0.5410 0.0273
-2.750 0.1075 0.01641 0.00941 -0.0567 0.5374 0.0277
-2.500 0.1353 0.01518 0.00793 -0.0565 0.5335 0.0282
-2.250 0.1633 0.01441 0.00692 -0.0563 0.5295 0.0287
-2.000 0.1911 0.01374 0.00612 -0.0562 0.5256 0.0292
-1.750 0.2193 0.01325 0.00560 -0.0561 0.5216 0.0295
-1.500 0.2475 0.01288 0.00519 -0.0560 0.5178 0.0298
-1.250 0.2757 0.01256 0.00483 -0.0559 0.5146 0.0302
-1.000 0.3038 0.01227 0.00448 -0.0558 0.5115 0.0307
-0.750 0.3321 0.01199 0.00416 -0.0557 0.5085 0.0312
-0.500 0.3604 0.01171 0.00387 -0.0556 0.5051 0.0318
-0.250 0.3886 0.01146 0.00360 -0.0555 0.5014 0.0324
0.000 0.4168 0.01125 0.00337 -0.0554 0.4977 0.0330
0.250 0.4449 0.01111 0.00318 -0.0553 0.4941 0.0337
0.500 0.4732 0.01091 0.00302 -0.0552 0.4902 0.0347
0.750 0.5016 0.01078 0.00292 -0.0552 0.4859 0.0356
1.000 0.5299 0.01067 0.00281 -0.0552 0.4810 0.0366
1.250 0.5581 0.01059 0.00270 -0.0551 0.4763 0.0377
1.500 0.5866 0.01050 0.00262 -0.0551 0.4702 0.0388
1.750 0.6148 0.01041 0.00254 -0.0551 0.4633 0.0403
2.000 0.6432 0.01037 0.00251 -0.0550 0.4565 0.0424
2.250 0.6715 0.01036 0.00249 -0.0550 0.4489 0.0451
2.500 0.6997 0.01032 0.00247 -0.0550 0.4419 0.0487
2.750 0.7279 0.01033 0.00246 -0.0550 0.4323 0.0532
3.000 0.7560 0.01035 0.00248 -0.0550 0.4210 0.0610
3.250 0.7825 0.00984 0.00261 -0.0551 0.4077 0.3692
3.500 0.8140 0.00858 0.00275 -0.0560 0.3917 1.0000
3.750 0.8409 0.00879 0.00286 -0.0558 0.3754 1.0000
4.000 0.8676 0.00905 0.00299 -0.0557 0.3582 1.0000
4.250 0.8940 0.00934 0.00317 -0.0555 0.3412 1.0000
4.500 0.9205 0.00963 0.00336 -0.0553 0.3269 1.0000
4.750 0.9470 0.00991 0.00356 -0.0552 0.3148 1.0000
5.000 0.9734 0.01020 0.00378 -0.0551 0.3045 1.0000
5.250 1.0002 0.01043 0.00398 -0.0550 0.2957 1.0000
5.500 1.0266 0.01071 0.00420 -0.0548 0.2872 1.0000
5.750 1.0532 0.01095 0.00442 -0.0547 0.2785 1.0000
6.000 1.0794 0.01124 0.00467 -0.0546 0.2704 1.0000
6.250 1.1059 0.01149 0.00489 -0.0545 0.2631 1.0000
6.500 1.1318 0.01179 0.00516 -0.0543 0.2563 1.0000
6.750 1.1582 0.01203 0.00541 -0.0542 0.2502 1.0000
7.000 1.1840 0.01234 0.00569 -0.0541 0.2434 1.0000
7.250 1.2098 0.01263 0.00597 -0.0540 0.2372 1.0000
7.500 1.2354 0.01294 0.00628 -0.0538 0.2302 1.0000
7.750 1.2605 0.01329 0.00661 -0.0536 0.2235 1.0000
8.000 1.2857 0.01360 0.00692 -0.0535 0.2170 1.0000
8.250 1.3102 0.01399 0.00730 -0.0532 0.2114 1.0000
8.500 1.3351 0.01432 0.00765 -0.0530 0.2052 1.0000
8.750 1.3585 0.01478 0.00807 -0.0527 0.1969 1.0000
9.000 1.3825 0.01517 0.00848 -0.0524 0.1898 1.0000
9.250 1.4050 0.01569 0.00895 -0.0521 0.1819 1.0000
9.500 1.4282 0.01610 0.00939 -0.0517 0.1754 1.0000
9.750 1.4499 0.01664 0.00991 -0.0513 0.1683 1.0000
10.000 1.4721 0.01712 0.01041 -0.0509 0.1626 1.0000
10.250 1.4928 0.01768 0.01098 -0.0503 0.1557 1.0000
10.500 1.5127 0.01829 0.01159 -0.0497 0.1483 1.0000
10.750 1.5301 0.01907 0.01233 -0.0489 0.1383 1.0000
11.000 1.5464 0.01987 0.01313 -0.0481 0.1278 1.0000
11.250 1.5583 0.02088 0.01411 -0.0468 0.1157 1.0000
11.500 1.5633 0.02233 0.01551 -0.0452 0.1022 1.0000
11.750 1.5673 0.02421 0.01736 -0.0444 0.0926 1.0000
12.000 1.5736 0.02619 0.01937 -0.0443 0.0868 1.0000
12.250 1.5786 0.02848 0.02169 -0.0445 0.0816 1.0000
12.500 1.5849 0.03062 0.02388 -0.0446 0.0770 1.0000
12.750 1.5885 0.03298 0.02628 -0.0446 0.0725 1.0000
13.000 1.5911 0.03540 0.02874 -0.0444 0.0685 1.0000
13.250 1.5920 0.03795 0.03133 -0.0442 0.0616 1.0000
13.500 1.5769 0.04216 0.03544 -0.0440 0.0437 1.0000
13.750 1.5539 0.04726 0.04047 -0.0437 0.0272 1.0000
14.000 1.5398 0.05152 0.04476 -0.0437 0.0210 1.0000
14.250 1.5325 0.05507 0.04839 -0.0437 0.0187 1.0000
14.500 1.5273 0.05855 0.05194 -0.0438 0.0174 1.0000
14.750 1.5224 0.06214 0.05562 -0.0441 0.0163 1.0000
15.000 1.5195 0.06559 0.05916 -0.0445 0.0156 1.0000
15.250 1.5155 0.06924 0.06290 -0.0450 0.0150 1.0000
15.500 1.5106 0.07306 0.06682 -0.0456 0.0144 1.0000
15.750 1.5043 0.07714 0.07100 -0.0463 0.0140 1.0000
16.000 1.4969 0.08147 0.07543 -0.0472 0.0136 1.0000
16.250 1.4881 0.08608 0.08014 -0.0482 0.0132 1.0000
16.500 1.4816 0.09042 0.08459 -0.0492 0.0130 1.0000
16.750 1.4740 0.09499 0.08927 -0.0504 0.0128 1.0000
17.000 1.4657 0.09975 0.09414 -0.0517 0.0126 1.0000
17.250 1.4566 0.10467 0.09918 -0.0531 0.0124 1.0000
17.500 1.4468 0.10978 0.10439 -0.0547 0.0121 1.0000
17.750 1.4365 0.11504 0.10977 -0.0564 0.0120 1.0000
18.000 1.4261 0.12041 0.11524 -0.0583 0.0118 1.0000
18.250 1.4156 0.12582 0.12076 -0.0603 0.0116 1.0000
18.500 1.4053 0.13126 0.12630 -0.0625 0.0114 1.0000
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