GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 500,000 Max Cl/Cd: 92.1 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe318-il-500000-n5.txt Download as CSV file: xf-goe318-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4676 0.09262 0.08972 0.0114 0.7001 0.0117
-8.000 -0.4699 0.08706 0.08415 0.0074 0.6941 0.0123
-7.750 -0.4709 0.07950 0.07657 -0.0006 0.6893 0.0128
-7.500 -0.4571 0.07617 0.07321 -0.0045 0.6828 0.0130
-7.250 -0.4415 0.07289 0.06988 -0.0084 0.6767 0.0133
-7.000 -0.4246 0.06919 0.06611 -0.0126 0.6711 0.0136
-6.750 -0.4061 0.06494 0.06179 -0.0174 0.6655 0.0143
-6.500 -0.3865 0.05175 0.04832 -0.0300 0.6624 0.0164
-6.250 -0.3636 0.04929 0.04574 -0.0321 0.6572 0.0167
-6.000 -0.3399 0.04697 0.04332 -0.0338 0.6518 0.0171
-5.750 -0.3154 0.04425 0.04046 -0.0356 0.6468 0.0179
-5.250 -0.2633 0.02881 0.02407 -0.0417 0.6396 0.0215
-5.000 -0.2369 0.02806 0.02323 -0.0420 0.6346 0.0220
-4.750 -0.2104 0.02643 0.02139 -0.0424 0.6302 0.0228
-4.500 -0.1834 0.02312 0.01768 -0.0428 0.6259 0.0238
-4.250 -0.1558 0.02049 0.01462 -0.0431 0.6207 0.0252
-4.000 -0.1279 0.01886 0.01263 -0.0431 0.6151 0.0259
-3.750 -0.0997 0.01774 0.01125 -0.0432 0.6091 0.0262
-3.500 -0.0714 0.01694 0.01023 -0.0433 0.6031 0.0265
-3.000 -0.0152 0.01456 0.00747 -0.0435 0.5936 0.0279
-2.750 0.0132 0.01395 0.00676 -0.0436 0.5880 0.0283
-2.500 0.0417 0.01344 0.00614 -0.0437 0.5823 0.0287
-2.250 0.0703 0.01295 0.00558 -0.0437 0.5759 0.0292
-2.000 0.0989 0.01253 0.00506 -0.0438 0.5695 0.0297
-1.750 0.1275 0.01213 0.00460 -0.0438 0.5625 0.0301
-1.500 0.1561 0.01178 0.00418 -0.0439 0.5548 0.0306
-1.250 0.1847 0.01145 0.00380 -0.0439 0.5474 0.0310
-1.000 0.2133 0.01116 0.00345 -0.0440 0.5382 0.0314
-0.750 0.2420 0.01093 0.00319 -0.0441 0.5295 0.0322
-0.500 0.2707 0.01074 0.00295 -0.0442 0.5219 0.0329
-0.250 0.2995 0.01053 0.00271 -0.0443 0.5135 0.0334
0.000 0.3283 0.01036 0.00250 -0.0444 0.5050 0.0338
0.250 0.3571 0.01023 0.00233 -0.0445 0.4952 0.0343
0.500 0.3859 0.01012 0.00218 -0.0446 0.4851 0.0349
0.750 0.4147 0.00998 0.00199 -0.0448 0.4746 0.0364
1.000 0.4434 0.00993 0.00190 -0.0449 0.4631 0.0379
1.250 0.4722 0.00992 0.00185 -0.0451 0.4511 0.0396
1.500 0.5009 0.00994 0.00183 -0.0453 0.4386 0.0418
1.750 0.5296 0.00998 0.00182 -0.0454 0.4251 0.0452
2.000 0.5582 0.01000 0.00183 -0.0456 0.4110 0.0618
2.250 0.5866 0.00965 0.00196 -0.0461 0.3965 0.2778
2.500 0.6105 0.00803 0.00205 -0.0455 0.3825 1.0000
2.750 0.6389 0.00821 0.00213 -0.0456 0.3671 1.0000
3.000 0.6672 0.00841 0.00223 -0.0458 0.3508 1.0000
3.250 0.6954 0.00863 0.00235 -0.0460 0.3336 1.0000
3.500 0.7235 0.00887 0.00249 -0.0461 0.3168 1.0000
3.750 0.7516 0.00911 0.00264 -0.0463 0.3013 1.0000
4.000 0.7796 0.00935 0.00280 -0.0465 0.2883 1.0000
4.250 0.8076 0.00957 0.00297 -0.0466 0.2782 1.0000
4.500 0.8355 0.00980 0.00316 -0.0468 0.2700 1.0000
4.750 0.8635 0.01000 0.00334 -0.0469 0.2637 1.0000
5.000 0.8913 0.01023 0.00354 -0.0471 0.2581 1.0000
5.250 0.9191 0.01044 0.00376 -0.0472 0.2540 1.0000
5.500 0.9469 0.01063 0.00397 -0.0473 0.2506 1.0000
5.750 0.9745 0.01085 0.00419 -0.0475 0.2468 1.0000
6.000 1.0019 0.01112 0.00445 -0.0476 0.2420 1.0000
6.250 1.0293 0.01134 0.00469 -0.0477 0.2373 1.0000
6.500 1.0567 0.01157 0.00494 -0.0478 0.2328 1.0000
6.750 1.0836 0.01187 0.00524 -0.0479 0.2267 1.0000
7.000 1.1107 0.01211 0.00550 -0.0480 0.2209 1.0000
7.250 1.1376 0.01237 0.00577 -0.0480 0.2145 1.0000
7.500 1.1641 0.01268 0.00609 -0.0481 0.2075 1.0000
7.750 1.1909 0.01293 0.00638 -0.0482 0.2001 1.0000
8.000 1.2172 0.01325 0.00670 -0.0482 0.1891 1.0000
8.250 1.2418 0.01382 0.00710 -0.0482 0.1500 1.0000
8.500 1.2573 0.01578 0.00855 -0.0477 0.0701 1.0000
8.750 1.2773 0.01693 0.00955 -0.0473 0.0435 1.0000
9.000 1.2978 0.01791 0.01044 -0.0469 0.0251 1.0000
9.250 1.3187 0.01877 0.01127 -0.0465 0.0179 1.0000
9.500 1.3399 0.01952 0.01206 -0.0461 0.0152 1.0000
9.750 1.3608 0.02026 0.01288 -0.0456 0.0138 1.0000
10.000 1.3797 0.02115 0.01383 -0.0451 0.0124 1.0000
10.250 1.3975 0.02209 0.01485 -0.0444 0.0113 1.0000
10.500 1.4152 0.02297 0.01582 -0.0437 0.0107 1.0000
10.750 1.4307 0.02398 0.01692 -0.0429 0.0101 1.0000
11.000 1.4433 0.02513 0.01815 -0.0419 0.0096 1.0000
11.250 1.4494 0.02658 0.01972 -0.0406 0.0092 1.0000
11.500 1.4539 0.02857 0.02180 -0.0401 0.0088 1.0000
11.750 1.4549 0.03119 0.02453 -0.0400 0.0085 1.0000
12.000 1.4601 0.03345 0.02690 -0.0401 0.0083 1.0000
12.250 1.4645 0.03585 0.02941 -0.0402 0.0080 1.0000
12.500 1.4670 0.03850 0.03217 -0.0404 0.0078 1.0000
12.750 1.4680 0.04134 0.03512 -0.0406 0.0075 1.0000
13.000 1.4674 0.04439 0.03827 -0.0409 0.0073 1.0000
13.250 1.4652 0.04766 0.04165 -0.0412 0.0071 1.0000
13.500 1.4613 0.05117 0.04526 -0.0416 0.0069 1.0000
13.750 1.4560 0.05491 0.04912 -0.0421 0.0068 1.0000
14.000 1.4494 0.05888 0.05320 -0.0428 0.0067 1.0000
14.250 1.4419 0.06304 0.05746 -0.0435 0.0066 1.0000
14.500 1.4337 0.06750 0.06203 -0.0446 0.0065 1.0000
14.750 1.4253 0.07213 0.06676 -0.0457 0.0064 1.0000
15.000 1.4160 0.07702 0.07176 -0.0470 0.0063 1.0000
15.250 1.4059 0.08215 0.07699 -0.0485 0.0062 1.0000
15.500 1.3953 0.08736 0.08229 -0.0500 0.0061 1.0000
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Polar data table (+)
Polar graphs
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