SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 50,000 Max Cl/Cd: 35.55 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7084-il-50000-n5.txt Download as CSV file: xf-sd7084-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7084 (9.6%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4512 0.08876 0.08199 -0.0377 1.0000 0.0553
-8.500 -0.4493 0.08523 0.07847 -0.0377 1.0000 0.0545
-8.250 -0.4534 0.08138 0.07470 -0.0389 1.0000 0.0538
-8.000 -0.4587 0.07745 0.07083 -0.0401 1.0000 0.0530
-7.750 -0.4647 0.07333 0.06675 -0.0412 1.0000 0.0523
-7.500 -0.4710 0.06935 0.06277 -0.0418 1.0000 0.0516
-7.250 -0.4773 0.06534 0.05871 -0.0419 1.0000 0.0509
-7.000 -0.4820 0.06140 0.05468 -0.0416 1.0000 0.0504
-6.750 -0.4848 0.05747 0.05058 -0.0410 1.0000 0.0499
-6.500 -0.4849 0.05360 0.04646 -0.0400 1.0000 0.0495
-6.250 -0.4818 0.04990 0.04246 -0.0389 1.0000 0.0492
-6.000 -0.4754 0.04639 0.03861 -0.0376 1.0000 0.0492
-5.750 -0.4660 0.04321 0.03503 -0.0363 1.0000 0.0499
-5.500 -0.4540 0.04039 0.03176 -0.0349 1.0000 0.0517
-5.250 -0.4396 0.03770 0.02852 -0.0335 1.0000 0.0540
-5.000 -0.4228 0.03529 0.02554 -0.0320 1.0000 0.0552
-4.750 -0.4043 0.03298 0.02286 -0.0307 1.0000 0.0560
-4.500 -0.3852 0.03098 0.02065 -0.0295 1.0000 0.0574
-4.250 -0.3650 0.02935 0.01881 -0.0283 1.0000 0.0593
-4.000 -0.3441 0.02793 0.01714 -0.0270 1.0000 0.0616
-3.750 -0.3228 0.02669 0.01566 -0.0257 1.0000 0.0653
-3.500 -0.3020 0.02563 0.01449 -0.0245 1.0000 0.0716
-3.250 -0.2811 0.02477 0.01351 -0.0233 1.0000 0.0795
-3.000 -0.2590 0.02382 0.01250 -0.0224 1.0000 0.0881
-2.750 -0.2375 0.02301 0.01164 -0.0215 1.0000 0.1057
-2.500 -0.2162 0.02209 0.01088 -0.0208 1.0000 0.1441
-2.250 -0.1892 0.02050 0.01031 -0.0218 0.9969 0.3052
-2.000 -0.1630 0.01914 0.01041 -0.0212 0.9891 0.6149
-1.750 -0.0893 0.01857 0.01033 -0.0276 0.9878 1.0000
-1.500 -0.0479 0.01884 0.01011 -0.0310 0.9772 1.0000
-1.250 -0.0065 0.01910 0.00999 -0.0343 0.9666 1.0000
-1.000 0.0360 0.01936 0.00992 -0.0377 0.9560 1.0000
-0.750 0.0752 0.01956 0.00984 -0.0403 0.9440 1.0000
-0.500 0.1133 0.01973 0.00980 -0.0427 0.9314 1.0000
-0.250 0.1513 0.01988 0.00976 -0.0449 0.9185 1.0000
0.000 0.1894 0.01999 0.00970 -0.0470 0.9053 1.0000
0.250 0.2274 0.02006 0.00966 -0.0490 0.8917 1.0000
0.500 0.2633 0.02011 0.00959 -0.0504 0.8775 1.0000
0.750 0.2976 0.02011 0.00951 -0.0514 0.8626 1.0000
1.000 0.3309 0.02008 0.00942 -0.0521 0.8472 1.0000
1.250 0.3636 0.02001 0.00931 -0.0526 0.8314 1.0000
1.500 0.3934 0.01994 0.00920 -0.0524 0.8141 1.0000
1.750 0.4210 0.01990 0.00913 -0.0519 0.7951 1.0000
2.000 0.4508 0.01981 0.00902 -0.0516 0.7770 1.0000
2.250 0.4802 0.01972 0.00892 -0.0512 0.7581 1.0000
2.500 0.5072 0.01970 0.00888 -0.0504 0.7369 1.0000
2.750 0.5364 0.01964 0.00878 -0.0498 0.7165 1.0000
3.000 0.5625 0.01969 0.00884 -0.0489 0.6935 1.0000
3.250 0.5892 0.01976 0.00888 -0.0480 0.6704 1.0000
3.500 0.6159 0.01986 0.00892 -0.0471 0.6471 1.0000
3.750 0.6404 0.02007 0.00910 -0.0460 0.6220 1.0000
4.000 0.6649 0.02032 0.00935 -0.0449 0.5971 1.0000
4.250 0.6894 0.02061 0.00958 -0.0439 0.5728 1.0000
4.500 0.7133 0.02095 0.00988 -0.0428 0.5485 1.0000
4.750 0.7364 0.02136 0.01028 -0.0417 0.5241 1.0000
5.000 0.7596 0.02179 0.01073 -0.0407 0.5008 1.0000
5.250 0.7827 0.02227 0.01119 -0.0396 0.4783 1.0000
5.500 0.8052 0.02279 0.01174 -0.0386 0.4562 1.0000
5.750 0.8281 0.02334 0.01228 -0.0376 0.4355 1.0000
6.000 0.8505 0.02393 0.01292 -0.0366 0.4151 1.0000
6.250 0.8727 0.02455 0.01365 -0.0357 0.3957 1.0000
6.500 0.8952 0.02519 0.01432 -0.0347 0.3776 1.0000
6.750 0.9167 0.02590 0.01513 -0.0337 0.3594 1.0000
7.000 0.9380 0.02663 0.01596 -0.0327 0.3418 1.0000
7.250 0.9591 0.02739 0.01682 -0.0316 0.3250 1.0000
7.500 0.9797 0.02816 0.01769 -0.0305 0.3086 1.0000
7.750 1.0000 0.02897 0.01865 -0.0294 0.2926 1.0000
8.000 1.0187 0.02986 0.01970 -0.0281 0.2759 1.0000
8.250 1.0362 0.03077 0.02078 -0.0267 0.2589 1.0000
8.500 1.0527 0.03169 0.02187 -0.0251 0.2419 1.0000
8.750 1.0675 0.03260 0.02289 -0.0235 0.2247 1.0000
9.000 1.0800 0.03358 0.02399 -0.0215 0.2068 1.0000
9.250 1.0894 0.03465 0.02526 -0.0194 0.1874 1.0000
9.500 1.0958 0.03574 0.02646 -0.0170 0.1683 1.0000
9.750 1.0992 0.03709 0.02794 -0.0144 0.1477 1.0000
10.000 1.0984 0.03859 0.02944 -0.0116 0.1290 1.0000
10.250 1.0952 0.04045 0.03131 -0.0089 0.1113 1.0000
10.500 1.0910 0.04270 0.03358 -0.0066 0.0952 1.0000
10.750 1.0854 0.04534 0.03622 -0.0047 0.0823 1.0000
11.000 1.0793 0.04823 0.03911 -0.0034 0.0726 1.0000
11.250 1.0724 0.05139 0.04228 -0.0026 0.0651 1.0000
11.500 1.0673 0.05483 0.04589 -0.0021 0.0585 1.0000
11.750 1.0609 0.05839 0.04948 -0.0022 0.0541 1.0000
12.000 1.0548 0.06230 0.05353 -0.0025 0.0503 1.0000
12.250 1.0498 0.06635 0.05781 -0.0030 0.0470 1.0000
12.500 1.0446 0.07051 0.06211 -0.0038 0.0447 1.0000
12.750 1.0386 0.07478 0.06642 -0.0049 0.0426 1.0000
13.000 1.0329 0.07935 0.07111 -0.0061 0.0411 1.0000
13.250 1.0232 0.08500 0.07707 -0.0083 0.0398 1.0000
13.500 1.0123 0.09101 0.08334 -0.0110 0.0389 1.0000
13.750 1.0000 0.09758 0.09014 -0.0141 0.0386 1.0000
14.000 0.9855 0.10495 0.09772 -0.0180 0.0385 1.0000
14.250 0.9681 0.11340 0.10636 -0.0226 0.0387 1.0000
14.500 0.9491 0.12281 0.11593 -0.0278 0.0394 1.0000
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Polar data table (+)
Polar graphs
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