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pelafoil_T1_Re0.350_M0.00_N9.0.txt
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pelafoil_T1_Re0.350_M0.00_N9.0.txt
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XFLR5 v6.06
Calculated polar for: pelafoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.350 e 6 Ncrit = 9.000
alpha CL CD CDp Cm Top Xtr Bot Xtr Cpmin Chinge XCp
------- -------- --------- --------- -------- ------- ------- -------- --------- ---------
-2.000 0.2564 0.01041 0.00364 -0.1053 0.8279 0.0557 -1.4070 0.0000 0.6631
-1.500 0.3115 0.00905 0.00313 -0.1057 0.8154 0.3291 -1.1319 0.0000 0.5906
-1.000 0.3646 0.00817 0.00317 -0.1055 0.8028 0.6309 -0.8639 0.0000 0.5397
-0.500 0.4144 0.00725 0.00299 -0.1030 0.7888 1.0000 -0.6125 0.0000 0.4984
0.000 0.4710 0.00737 0.00288 -0.1031 0.7748 1.0000 -0.6461 0.0000 0.4680
0.500 0.5274 0.00741 0.00274 -0.1031 0.7588 1.0000 -0.6907 0.0000 0.4441
1.000 0.5837 0.00754 0.00270 -0.1030 0.7425 1.0000 -0.7397 0.0000 0.4247
1.500 0.6398 0.00762 0.00266 -0.1029 0.7240 1.0000 -0.7940 0.0000 0.4086
2.000 0.6957 0.00775 0.00272 -0.1028 0.7043 1.0000 -0.8547 0.0000 0.3951
2.500 0.7512 0.00792 0.00276 -0.1026 0.6830 1.0000 -0.9234 0.0000 0.3835
2.500 0.7512 0.00792 0.00276 -0.1026 0.6830 1.0000 -0.9234 0.0000 0.3835
3.500 0.8612 0.00835 0.00303 -0.1021 0.6324 1.0000 -1.0934 0.0000 0.3645
4.000 0.9154 0.00864 0.00325 -0.1017 0.6034 1.0000 -1.2854 0.0000 0.3565
4.500 0.9688 0.00901 0.00357 -0.1013 0.5716 1.0000 -1.5840 0.0000 0.3494
5.000 1.0214 0.00944 0.00393 -0.1007 0.5351 1.0000 -1.8900 0.0000 0.3429
5.500 1.0721 0.00999 0.00435 -0.0998 0.4855 1.0000 -2.2059 0.0000 0.3368
6.000 1.1201 0.01078 0.00496 -0.0986 0.4223 1.0000 -2.5201 0.0000 0.3312
6.500 1.1611 0.01222 0.00582 -0.0965 0.3098 1.0000 -2.8338 0.0000 0.3257
7.000 1.1965 0.01428 0.00712 -0.0940 0.1860 1.0000 -3.1360 0.0000 0.3205
7.500 1.2317 0.01631 0.00859 -0.0915 0.0942 1.0000 -3.4347 0.0000 0.3156
8.000 1.2612 0.01878 0.01059 -0.0880 0.0290 1.0000 -3.6551 0.0000 0.3104
8.500 1.2895 0.02110 0.01313 -0.0839 0.0198 1.0000 -3.8403 0.0000 0.3050
9.000 1.3231 0.02253 0.01471 -0.0809 0.0183 1.0000 -4.2940 0.0000 0.3004
9.500 1.3496 0.02421 0.01653 -0.0769 0.0161 1.0000 -4.7441 0.0000 0.2955
10.000 1.3732 0.02620 0.01862 -0.0732 0.0136 1.0000 -5.1871 0.0000 0.2911