GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 500,000 Max Cl/Cd: 100.52 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe316-il-500000.txt Download as CSV file: xf-goe316-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3219 0.09985 0.09783 -0.0081 1.0000 0.0204
-9.250 -0.3155 0.09669 0.09469 -0.0084 1.0000 0.0207
-9.000 -0.4323 0.10401 0.10190 -0.0038 1.0000 0.0201
-8.750 -0.4218 0.10018 0.09808 -0.0016 1.0000 0.0203
-8.500 -0.4135 0.09720 0.09511 -0.0019 1.0000 0.0206
-8.250 -0.4062 0.09427 0.09220 -0.0031 1.0000 0.0209
-8.000 -0.3997 0.09121 0.08917 -0.0048 1.0000 0.0214
-7.750 -0.3939 0.08798 0.08597 -0.0069 1.0000 0.0220
-7.500 -0.3882 0.08451 0.08253 -0.0099 1.0000 0.0226
-7.250 -0.3757 0.07997 0.07799 -0.0168 1.0000 0.0238
-6.750 -0.3255 0.06626 0.06407 -0.0397 0.9541 0.0245
-6.500 -0.3180 0.06307 0.06081 -0.0385 0.9103 0.0248
-6.250 -0.3077 0.06086 0.05847 -0.0375 0.8695 0.0251
-6.000 -0.2923 0.05834 0.05579 -0.0383 0.8423 0.0257
-5.750 -0.2729 0.05529 0.05259 -0.0403 0.8227 0.0265
-5.500 -0.2499 0.05174 0.04885 -0.0431 0.8072 0.0279
-5.250 -0.2094 0.04692 0.04350 -0.0480 0.7949 0.0297
-5.000 -0.1935 0.04167 0.03811 -0.0495 0.7834 0.0302
-4.750 -0.1734 0.03965 0.03600 -0.0498 0.7710 0.0307
-4.500 -0.1505 0.03764 0.03389 -0.0504 0.7591 0.0315
-4.250 -0.1254 0.03543 0.03152 -0.0511 0.7486 0.0327
-4.000 -0.0898 0.03401 0.02960 -0.0511 0.7390 0.0361
-3.750 -0.0655 0.02937 0.02462 -0.0519 0.7298 0.0369
-3.500 -0.0416 0.02740 0.02260 -0.0524 0.7201 0.0376
-3.250 -0.0161 0.02594 0.02103 -0.0527 0.7101 0.0385
-3.000 0.0108 0.02454 0.01948 -0.0529 0.6995 0.0399
-2.750 0.0395 0.02329 0.01800 -0.0528 0.6892 0.0426
-2.500 0.0712 0.02385 0.01815 -0.0520 0.6779 0.0447
-2.250 0.0964 0.01990 0.01405 -0.0527 0.6665 0.0466
-2.000 0.1238 0.01887 0.01293 -0.0529 0.6535 0.0480
-1.750 0.1519 0.01800 0.01191 -0.0530 0.6394 0.0503
-1.500 0.1820 0.01884 0.01248 -0.0524 0.6226 0.0548
-1.250 0.2093 0.01613 0.00954 -0.0528 0.6056 0.0574
-1.000 0.2371 0.01540 0.00870 -0.0529 0.5859 0.0596
-0.750 0.2654 0.01500 0.00814 -0.0528 0.5647 0.0636
-0.500 0.2934 0.01431 0.00726 -0.0529 0.5437 0.0711
-0.250 0.3215 0.01390 0.00673 -0.0529 0.5223 0.0755
0.000 0.3524 0.01219 0.00455 -0.0517 0.5019 0.0458
0.250 0.3803 0.01187 0.00410 -0.0517 0.4766 0.0456
0.500 0.4079 0.01152 0.00363 -0.0516 0.4482 0.0461
0.750 0.4355 0.01131 0.00332 -0.0516 0.4205 0.0477
1.000 0.4633 0.01118 0.00309 -0.0516 0.4002 0.0486
1.250 0.4912 0.01109 0.00292 -0.0517 0.3865 0.0498
1.500 0.5193 0.01103 0.00280 -0.0517 0.3767 0.0514
1.750 0.5475 0.01100 0.00273 -0.0518 0.3697 0.0532
2.000 0.5756 0.01102 0.00271 -0.0518 0.3636 0.0550
2.250 0.6036 0.01099 0.00263 -0.0519 0.3583 0.0610
2.500 0.6320 0.01099 0.00263 -0.0519 0.3543 0.0669
2.750 0.6562 0.00892 0.00277 -0.0516 0.3508 1.0000
3.000 0.6841 0.00910 0.00284 -0.0516 0.3474 1.0000
3.250 0.7117 0.00933 0.00298 -0.0516 0.3441 1.0000
3.500 0.7396 0.00950 0.00312 -0.0516 0.3417 1.0000
3.750 0.7676 0.00965 0.00327 -0.0516 0.3393 1.0000
4.000 0.7955 0.00982 0.00343 -0.0517 0.3370 1.0000
4.250 0.8232 0.01000 0.00359 -0.0517 0.3347 1.0000
4.500 0.8507 0.01021 0.00376 -0.0517 0.3309 1.0000
4.750 0.8781 0.01043 0.00396 -0.0517 0.3257 1.0000
5.000 0.9059 0.01053 0.00409 -0.0518 0.3209 1.0000
5.250 0.9334 0.01071 0.00425 -0.0518 0.3172 1.0000
5.500 0.9605 0.01097 0.00450 -0.0518 0.3142 1.0000
5.750 0.9878 0.01120 0.00474 -0.0518 0.3114 1.0000
6.000 1.0154 0.01134 0.00494 -0.0518 0.3090 1.0000
6.250 1.0429 0.01150 0.00515 -0.0518 0.3060 1.0000
6.500 1.0701 0.01166 0.00533 -0.0518 0.3019 1.0000
6.750 1.0966 0.01195 0.00560 -0.0518 0.2968 1.0000
7.000 1.1242 0.01200 0.00575 -0.0518 0.2925 1.0000
7.250 1.1515 0.01210 0.00590 -0.0519 0.2865 1.0000
7.500 1.1781 0.01230 0.00611 -0.0518 0.2805 1.0000
7.750 1.2056 0.01234 0.00625 -0.0519 0.2736 1.0000
8.000 1.2322 0.01251 0.00644 -0.0518 0.2656 1.0000
8.250 1.2592 0.01262 0.00660 -0.0518 0.2547 1.0000
8.500 1.2857 0.01279 0.00677 -0.0518 0.2366 1.0000
8.750 1.3087 0.01341 0.00714 -0.0515 0.1844 1.0000
9.000 1.3268 0.01469 0.00812 -0.0507 0.1365 1.0000
9.250 1.3452 0.01590 0.00910 -0.0499 0.0969 1.0000
9.500 1.3617 0.01723 0.01020 -0.0489 0.0632 1.0000
9.750 1.3814 0.01812 0.01108 -0.0482 0.0528 1.0000
10.000 1.4007 0.01898 0.01198 -0.0473 0.0429 1.0000
10.250 1.4172 0.02008 0.01301 -0.0462 0.0313 1.0000
10.500 1.4336 0.02111 0.01402 -0.0451 0.0253 1.0000
10.750 1.4496 0.02208 0.01507 -0.0438 0.0225 1.0000
11.000 1.4628 0.02320 0.01622 -0.0424 0.0205 1.0000
11.250 1.4714 0.02456 0.01770 -0.0404 0.0191 1.0000
11.500 1.4785 0.02572 0.01896 -0.0381 0.0183 1.0000
11.750 1.4827 0.02714 0.02049 -0.0360 0.0176 1.0000
12.000 1.4854 0.02891 0.02237 -0.0344 0.0170 1.0000
12.250 1.4858 0.03117 0.02474 -0.0334 0.0165 1.0000
12.500 1.4825 0.03413 0.02781 -0.0330 0.0160 1.0000
12.750 1.4751 0.03784 0.03164 -0.0331 0.0156 1.0000
13.000 1.4636 0.04222 0.03616 -0.0336 0.0153 1.0000
13.250 1.4599 0.04579 0.03986 -0.0341 0.0151 1.0000
13.500 1.4567 0.04939 0.04358 -0.0347 0.0149 1.0000
13.750 1.4516 0.05329 0.04760 -0.0355 0.0146 1.0000
14.000 1.4455 0.05738 0.05181 -0.0363 0.0144 1.0000
14.250 1.4387 0.06156 0.05611 -0.0372 0.0141 1.0000
14.500 1.4316 0.06583 0.06048 -0.0382 0.0138 1.0000
14.750 1.4240 0.07017 0.06492 -0.0391 0.0136 1.0000
15.000 1.4173 0.07450 0.06935 -0.0402 0.0134 1.0000
15.250 1.4110 0.07886 0.07379 -0.0413 0.0131 1.0000
15.500 1.4050 0.08317 0.07818 -0.0424 0.0129 1.0000
15.750 1.3994 0.08742 0.08251 -0.0435 0.0128 1.0000
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