YS-930 (ys930-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: YS-930 (ys930-il) Reynolds number: 50,000 Max Cl/Cd: 24.7 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys930-il-50000.txt Download as CSV file: xf-ys930-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: YS-930
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4353 0.10702 0.10068 -0.0274 1.0000 0.2351
-8.250 -0.4503 0.10561 0.09938 -0.0256 1.0000 0.2400
-8.000 -0.4840 0.10603 0.10000 -0.0234 1.0000 0.2421
-7.750 -0.4157 0.09573 0.09012 -0.0202 1.0000 0.2429
-7.500 -0.4240 0.09256 0.08701 -0.0189 1.0000 0.2430
-7.250 -0.4180 0.08796 0.08240 -0.0179 1.0000 0.2357
-7.000 -0.5491 0.08631 0.08061 -0.0289 1.0000 0.1374
-6.750 -0.5699 0.07644 0.07072 -0.0367 1.0000 0.1104
-6.500 -0.5712 0.07097 0.06517 -0.0382 1.0000 0.1038
-6.250 -0.5789 0.06083 0.05456 -0.0450 1.0000 0.0938
-6.000 -0.5715 0.05558 0.04908 -0.0458 1.0000 0.0915
-5.750 -0.5613 0.04960 0.04259 -0.0476 1.0000 0.0904
-5.500 -0.5456 0.04435 0.03667 -0.0488 1.0000 0.0915
-5.250 -0.5254 0.03983 0.03135 -0.0494 1.0000 0.0931
-5.000 -0.5015 0.03591 0.02657 -0.0494 1.0000 0.0954
-4.750 -0.4785 0.03306 0.02354 -0.0487 1.0000 0.1004
-4.500 -0.4541 0.03069 0.02085 -0.0478 1.0000 0.1118
-4.250 -0.4307 0.02917 0.01923 -0.0469 1.0000 0.1352
-4.000 -0.4067 0.02785 0.01802 -0.0456 1.0000 0.1782
-3.750 -0.3909 0.02784 0.01862 -0.0427 1.0000 0.3137
-3.500 -0.3781 0.02848 0.01947 -0.0392 1.0000 0.3829
-3.250 -0.3626 0.02850 0.01953 -0.0364 1.0000 0.4278
-3.000 -0.3417 0.02794 0.01877 -0.0350 1.0000 0.4550
-2.750 -0.3180 0.02730 0.01780 -0.0347 1.0000 0.4761
-2.500 -0.2954 0.02669 0.01701 -0.0340 1.0000 0.4932
-2.250 -0.2721 0.02613 0.01618 -0.0335 1.0000 0.5106
-2.000 -0.2481 0.02566 0.01548 -0.0332 1.0000 0.5298
-1.750 -0.2235 0.02524 0.01494 -0.0329 1.0000 0.5507
-1.500 -0.1985 0.02487 0.01446 -0.0328 1.0000 0.5761
-1.250 -0.1741 0.02449 0.01407 -0.0324 1.0000 0.6108
-1.000 -0.1510 0.02401 0.01378 -0.0315 1.0000 0.6610
-0.750 -0.1319 0.02312 0.01348 -0.0291 1.0000 0.7745
-0.500 -0.0884 0.02248 0.01256 -0.0341 1.0000 1.0000
-0.250 -0.0635 0.02280 0.01247 -0.0344 1.0000 1.0000
0.000 -0.0404 0.02314 0.01251 -0.0344 1.0000 1.0000
0.250 -0.0180 0.02350 0.01259 -0.0341 1.0000 1.0000
0.500 0.0039 0.02389 0.01278 -0.0339 1.0000 1.0000
0.750 0.0256 0.02429 0.01303 -0.0335 1.0000 1.0000
1.000 0.0469 0.02473 0.01333 -0.0332 1.0000 1.0000
1.250 0.0681 0.02519 0.01369 -0.0328 1.0000 1.0000
1.500 0.0889 0.02567 0.01409 -0.0324 1.0000 1.0000
1.750 0.1095 0.02619 0.01454 -0.0320 1.0000 1.0000
2.000 0.1299 0.02674 0.01504 -0.0317 1.0000 1.0000
2.250 0.1500 0.02732 0.01560 -0.0313 1.0000 1.0000
2.500 0.1698 0.02793 0.01621 -0.0309 1.0000 1.0000
2.750 0.1893 0.02859 0.01688 -0.0306 1.0000 1.0000
3.000 0.2085 0.02928 0.01763 -0.0302 1.0000 1.0000
3.250 0.2273 0.03002 0.01841 -0.0299 1.0000 1.0000
3.500 0.2458 0.03081 0.01926 -0.0296 1.0000 1.0000
3.750 0.2638 0.03165 0.02018 -0.0293 1.0000 1.0000
4.000 0.2814 0.03255 0.02118 -0.0290 1.0000 1.0000
4.250 0.2986 0.03351 0.02225 -0.0288 1.0000 1.0000
4.500 0.3154 0.03454 0.02347 -0.0286 1.0000 1.0000
4.750 0.3315 0.03564 0.02471 -0.0285 1.0000 1.0000
5.000 0.3470 0.03683 0.02606 -0.0284 1.0000 1.0000
5.250 0.3620 0.03812 0.02753 -0.0284 1.0000 1.0000
5.500 0.4517 0.04169 0.03174 -0.0421 0.9506 1.0000
5.750 0.5132 0.04347 0.03405 -0.0490 0.9116 1.0000
6.000 0.5799 0.04442 0.03566 -0.0552 0.8686 1.0000
6.250 0.7749 0.03137 0.01982 -0.0458 0.1146 1.0000
6.500 0.8926 0.03722 0.02540 -0.0579 0.0834 1.0000
6.750 0.9335 0.04066 0.02937 -0.0584 0.0818 1.0000
7.000 0.9661 0.04465 0.03380 -0.0580 0.0823 1.0000
7.250 0.9928 0.04855 0.03810 -0.0569 0.0842 1.0000
7.500 1.0028 0.05160 0.04213 -0.0526 0.0894 1.0000
7.750 1.0153 0.05576 0.04674 -0.0500 0.0934 1.0000
8.000 1.0298 0.06059 0.05190 -0.0483 0.0958 1.0000
8.250 1.0238 0.06386 0.05605 -0.0431 0.1051 1.0000
8.500 1.0216 0.06824 0.06095 -0.0397 0.1152 1.0000
8.750 1.0125 0.07312 0.06631 -0.0365 0.1289 1.0000
9.000 1.0193 0.08280 0.07642 -0.0369 0.1759 1.0000
9.250 0.9679 0.08433 0.07812 -0.0320 0.1727 1.0000
9.500 0.9288 0.08985 0.08380 -0.0317 0.1926 1.0000
9.750 0.8898 0.09555 0.08950 -0.0333 0.1955 1.0000
10.000 0.8490 0.10619 0.10009 -0.0422 0.2267 1.0000
10.250 0.7606 0.09813 0.09240 -0.0253 0.1530 1.0000
10.500 0.7258 0.10783 0.10205 -0.0320 0.1669 1.0000
|
Polar data table (+)
Polar graphs
<< Back to YS-930 (ys930-il)