GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.22 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe322-il-1000000.txt Download as CSV file: xf-goe322-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2227 0.08755 0.08484 -0.0396 0.6862 0.0219
-8.250 -0.2190 0.08340 0.08070 -0.0428 0.6831 0.0220
-8.000 -0.2170 0.07933 0.07663 -0.0462 0.6800 0.0220
-7.750 -0.2139 0.07466 0.07194 -0.0497 0.6768 0.0223
-7.500 -0.2011 0.07194 0.06920 -0.0522 0.6735 0.0225
-7.250 -0.1866 0.06923 0.06649 -0.0547 0.6702 0.0227
-7.000 -0.1709 0.06646 0.06370 -0.0576 0.6665 0.0229
-6.750 -0.1541 0.06345 0.06065 -0.0609 0.6627 0.0234
-6.500 -0.1360 0.05997 0.05711 -0.0649 0.6588 0.0240
-6.000 -0.0942 0.04304 0.03980 -0.0804 0.6532 0.0265
-5.750 -0.0726 0.04114 0.03783 -0.0813 0.6491 0.0267
-5.500 -0.0498 0.03951 0.03612 -0.0822 0.6446 0.0270
-5.250 -0.0259 0.03773 0.03425 -0.0831 0.6398 0.0275
-5.000 -0.0011 0.03540 0.03182 -0.0842 0.6344 0.0282
-4.750 0.0223 0.02498 0.02066 -0.0865 0.6309 0.0316
-4.500 0.0484 0.02405 0.01965 -0.0867 0.6251 0.0319
-4.250 0.0751 0.02304 0.01857 -0.0871 0.6189 0.0323
-4.000 0.1020 0.02193 0.01732 -0.0873 0.6125 0.0329
-3.750 0.1277 0.01574 0.01007 -0.0869 0.6081 0.0314
-3.500 0.1559 0.01451 0.00876 -0.0870 0.6025 0.0300
-3.250 0.1842 0.01344 0.00749 -0.0871 0.5970 0.0297
-3.000 0.2130 0.01265 0.00655 -0.0872 0.5916 0.0296
-2.750 0.2419 0.01202 0.00581 -0.0873 0.5855 0.0296
-2.500 0.2708 0.01163 0.00531 -0.0874 0.5795 0.0300
-2.250 0.2999 0.01129 0.00491 -0.0875 0.5743 0.0304
-2.000 0.3290 0.01096 0.00451 -0.0877 0.5686 0.0306
-1.500 0.3869 0.01030 0.00374 -0.0879 0.5573 0.0311
-1.250 0.4155 0.00989 0.00329 -0.0881 0.5514 0.0315
-1.000 0.4442 0.00965 0.00301 -0.0882 0.5460 0.0320
-0.750 0.4734 0.00944 0.00281 -0.0884 0.5409 0.0325
-0.500 0.5024 0.00932 0.00265 -0.0886 0.5343 0.0330
-0.250 0.5314 0.00921 0.00252 -0.0888 0.5274 0.0337
0.000 0.5605 0.00913 0.00241 -0.0890 0.5202 0.0347
0.250 0.5895 0.00909 0.00234 -0.0892 0.5140 0.0357
0.500 0.6188 0.00903 0.00227 -0.0894 0.5085 0.0365
0.750 0.6478 0.00896 0.00217 -0.0897 0.5024 0.0384
1.000 0.6768 0.00894 0.00213 -0.0899 0.4963 0.0408
1.250 0.7059 0.00891 0.00211 -0.0901 0.4890 0.0468
1.500 0.7347 0.00887 0.00215 -0.0904 0.4816 0.0836
1.750 0.7636 0.00880 0.00221 -0.0906 0.4733 0.1335
2.000 0.7922 0.00880 0.00226 -0.0909 0.4647 0.1731
2.250 0.8186 0.00704 0.00245 -0.0912 0.4555 1.0000
2.500 0.8469 0.00717 0.00250 -0.0913 0.4460 1.0000
2.750 0.8750 0.00732 0.00257 -0.0914 0.4354 1.0000
3.000 0.9033 0.00745 0.00264 -0.0916 0.4242 1.0000
3.250 0.9313 0.00762 0.00273 -0.0917 0.4123 1.0000
3.500 0.9590 0.00781 0.00283 -0.0918 0.3994 1.0000
3.750 0.9865 0.00802 0.00296 -0.0919 0.3861 1.0000
4.000 1.0138 0.00825 0.00311 -0.0920 0.3731 1.0000
4.250 1.0412 0.00847 0.00325 -0.0921 0.3614 1.0000
4.500 1.0685 0.00868 0.00340 -0.0921 0.3514 1.0000
4.750 1.0954 0.00892 0.00358 -0.0922 0.3418 1.0000
5.000 1.1227 0.00912 0.00374 -0.0923 0.3337 1.0000
5.250 1.1495 0.00936 0.00393 -0.0923 0.3259 1.0000
5.500 1.1767 0.00955 0.00410 -0.0924 0.3189 1.0000
5.750 1.2030 0.00981 0.00431 -0.0923 0.3113 1.0000
6.000 1.2299 0.01000 0.00448 -0.0924 0.3043 1.0000
6.250 1.2557 0.01030 0.00472 -0.0923 0.2946 1.0000
6.500 1.2821 0.01051 0.00491 -0.0923 0.2871 1.0000
6.750 1.3077 0.01079 0.00515 -0.0922 0.2788 1.0000
7.000 1.3334 0.01105 0.00537 -0.0921 0.2700 1.0000
7.250 1.3586 0.01134 0.00563 -0.0919 0.2605 1.0000
7.500 1.3827 0.01170 0.00592 -0.0916 0.2495 1.0000
7.750 1.4064 0.01208 0.00623 -0.0913 0.2365 1.0000
8.000 1.4291 0.01251 0.00659 -0.0908 0.2226 1.0000
8.250 1.4508 0.01299 0.00699 -0.0902 0.2084 1.0000
8.500 1.4715 0.01351 0.00743 -0.0894 0.1951 1.0000
8.750 1.4918 0.01402 0.00789 -0.0885 0.1839 1.0000
9.000 1.5107 0.01459 0.00839 -0.0875 0.1730 1.0000
9.250 1.5287 0.01517 0.00892 -0.0863 0.1637 1.0000
9.500 1.5453 0.01578 0.00948 -0.0850 0.1545 1.0000
9.750 1.5599 0.01642 0.01008 -0.0833 0.1437 1.0000
10.000 1.5652 0.01737 0.01092 -0.0801 0.1280 1.0000
10.250 1.5483 0.01981 0.01308 -0.0749 0.0841 1.0000
10.500 1.5216 0.02377 0.01683 -0.0706 0.0388 1.0000
10.750 1.5163 0.02658 0.01959 -0.0689 0.0178 1.0000
11.000 1.5250 0.02822 0.02127 -0.0681 0.0158 1.0000
11.250 1.5345 0.02981 0.02292 -0.0675 0.0150 1.0000
11.500 1.5420 0.03157 0.02475 -0.0667 0.0144 1.0000
11.750 1.5473 0.03355 0.02679 -0.0659 0.0137 1.0000
12.000 1.5503 0.03577 0.02909 -0.0651 0.0131 1.0000
12.250 1.5560 0.03771 0.03110 -0.0644 0.0128 1.0000
12.500 1.5607 0.03978 0.03323 -0.0637 0.0126 1.0000
12.750 1.5640 0.04201 0.03553 -0.0630 0.0122 1.0000
13.000 1.5658 0.04440 0.03799 -0.0623 0.0119 1.0000
13.250 1.5663 0.04697 0.04064 -0.0617 0.0116 1.0000
13.500 1.5658 0.04975 0.04350 -0.0612 0.0113 1.0000
13.750 1.5635 0.05285 0.04668 -0.0608 0.0111 1.0000
14.000 1.5577 0.05643 0.05036 -0.0605 0.0108 1.0000
14.250 1.5478 0.06067 0.05471 -0.0604 0.0105 1.0000
14.500 1.5455 0.06405 0.05817 -0.0604 0.0104 1.0000
14.750 1.5430 0.06748 0.06170 -0.0605 0.0103 1.0000
15.000 1.5393 0.07114 0.06544 -0.0607 0.0102 1.0000
15.250 1.5341 0.07506 0.06945 -0.0609 0.0100 1.0000
15.500 1.5279 0.07917 0.07366 -0.0613 0.0099 1.0000
15.750 1.5201 0.08353 0.07811 -0.0618 0.0098 1.0000
16.000 1.5114 0.08810 0.08278 -0.0625 0.0096 1.0000
16.250 1.5022 0.09283 0.08761 -0.0632 0.0095 1.0000
16.500 1.4916 0.09780 0.09267 -0.0641 0.0094 1.0000
16.750 1.4805 0.10292 0.09790 -0.0652 0.0093 1.0000
17.000 1.4690 0.10821 0.10329 -0.0664 0.0092 1.0000
17.250 1.4573 0.11359 0.10877 -0.0677 0.0091 1.0000
17.500 1.4455 0.11903 0.11431 -0.0692 0.0091 1.0000
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