taper ratio

taper ratio

The ratio of the chord at the tip to the chord at the root of the wing.
An Illustrated Dictionary of Aviation Copyright © 2005 by The McGraw-Hill Companies, Inc. All rights reserved
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Variable Lower bound Baseline Wing area ([m.sup.2]) 300 355.49 Wing sweep ([degrees]) 27 32.4 Wing aspect ratio 8 10.4672 Wing taper ratio 0.1 0.1062 Thickness to chord ratio at wing root 0.11 0.135 Maximum takeoff thrust (kN) 280 334 Engine bypass ratio 8 11 Fan pressure ratio 1.5 1.58 Low-pressure compressor pressure ratio 2.5 3.2 Overall pressure ratio 40 52 Turbine inlet temperature (K) 1650 1800 Variable Upper bound Wing area ([m.sup.2]) 400 Wing sweep ([degrees]) 36 Wing aspect ratio 13 Wing taper ratio 0.12 Thickness to chord ratio at wing root 0.15 Maximum takeoff thrust (kN) 420 Engine bypass ratio 15 Fan pressure ratio 1.75 Low-pressure compressor pressure ratio 4.5 Overall pressure ratio 60 Turbine inlet temperature (K) 1900 Table 4: Optimization problem constraints.
In this section, the effects of the wing platform, such as the taper ratio, AR, as well as the aspect ratio, [lambda], on the lift coefficient and the induced drag are analyzed with the wing-canard configuration indicated in Figure 8.
As shown in Figure 18, the taper ratio of the fore wing has a significant effect on the lift coefficient of the hind wing, the lift coefficient of the hind wing decreases with the taper ratio of the fore wing increasing, but it is opposite for that of the fore wing, when the taper ratio is about 0.6, and the effects on the lift coefficient are similar to that by the elliptical wing.
Caption: Figure 18: Effect of taper ratio on lift coefficient and induced drag for tandem wing configuration.
NOMENCLATURE AR = aspect ratio S = wing wetted area [C.sub.R] = root chord length b = span length [[lambda].sub.R-B] = inboard taper ratio [[lambda].sub.B-T] = outboard taper ratio [[LAMBDA].sub.R-B] = inboard sweep angle [[lambda].sub.B-T] = outboard sweep angle [BP.sub.Inboard] = inboard break point [BP.sub.Outboard] = outboard break point [[GAMMA].sub.R-B] = inboard dihedral angle [[GAMMA].sub.B-T] = outboard dihedral angle [M.sub.[infinity] = free stream Mach number Re = Reynolds number [alpha] = angle of attack [PSI] = yaw angle [C.sub.L] = lift coefficient [C.sub.D] = drag coefficient [C.sub.D0] = drag coefficient at zero lift L/D = lift to drag ratio
As wing design variables, three sweep angles, three taper ratio and two break positions are considered to generate wing model.
For the wing design variables, sweep angles, taper ratios and the break points are considered.
Moreover, in [7], the taper ratio was studied in order to optimize the hover performance.
Take-up packages with different taper ratios with electronic on/off anti-patterning system.
Single direction tapering is well suited for tapering fibers with small taper ratios of less than 50 percent.
allowing for unlimited taper ratios with very low insertion loss.