Fuselage Lift Distribution for a Swept-Back Wing Aircraft

1953 ◽  
Vol 57 (511) ◽  
pp. 464-467
Author(s):  
W. Taylor
Keyword(s):  
Mach Number ◽  
Approximate Method ◽  
Load Distribution ◽  
Numerical Example

This note suggests a method, suitable for stressing purposes, of obtaining a fuselage air-load distribution, for a swept-back wing aircraft. The method is basically that given in Ref. 1. Mach number effect on the aerodynamic centre position is discussed and an approximate method of allowing for this is suggested. A numerical example is given.

On parachutes of optimum shape in a subsonic gas flow

2007 ◽  
Vol 18 (1) ◽  
pp. 81-102 ◽  
Author(s):  
D. V. MAKLAKOV ◽  
A. M. ELIZAROV ◽  
R. R. SHARIPOV
Keyword(s):  
Mach Number ◽  
Exact Solutions ◽  
Drag Coefficient ◽  
Approximate Method ◽  
Drag Force ◽  
Gas Flow ◽  
Optimum Shape ◽  
Global Maximum ◽  
Bluff Bodies ◽  
Subsonic Gas Flow

In this paper the problem of finding the impermeable parachute of optimum shape in a subsonic gas flow has been solved. The effects of compressibility have been taken into account out by making use of ideas of Chaplygin's approximate method. A formula for the drag coefficient has been deduced and by comparison with exact solutions it has been demonstrated that for bluff bodies its related error is no more than 0.5% for any Mach number at infinity less than unity. On the basis of the formula a functional for the drag force has been constructed and its global maximum has been found analytically. It has been shown that the optimum shape is slightly affected by compressibility.

On oscillations in a compressible laminar boundary layer

1981 ◽  
Vol 91 (1-2) ◽  
pp. 1-13 ◽  
Author(s):  
R. J. Gribben
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Mach Number ◽  
Approximate Method ◽  
Skin Friction ◽  
Laminar Boundary Layer ◽  
High Frequency ◽  
Unsteady Heat Transfer ◽  
Reasonable Description

SynopsisThe behaviour of heat transfer and skin friction is analysed in a compressible laminar boundary layer with external velocity Ue(x)(l + α sin ωt The Mach number M is assumed small but finite so that high frequency flows (s ≫1) in which c =αγM2s/2 = O(1) are considered. Solutions, obtained by matching in the Stokes and Prandtl layers, involve summation of Fourier-like series to give the dominant terms in the heat transfer and skin friction. Results, for c =½, verify that a previous approximate method gives a reasonable description of unsteady heat transfer and skin friction; forc =1 there is a substantial increase in amplitude of heat transfer but little change of phase.

Approximation for Determining Harmonically Excited Response of Nonclassically Damped Systems

1976 ◽  
Vol 98 (1) ◽  
pp. 43-47 ◽  
Author(s):  
D. L. Cronin
Keyword(s):  
Load Distribution ◽  
Classical Analysis ◽  
Frequency Dependent ◽  
Approximate Approach ◽  
Numerical Example ◽  
Damping Matrix ◽  
Damped Systems ◽  
A Current

The straightforward task of generating response plots for harmonically excited, nonclassically damped systems involves substantial computation. A current approximate approach based on classical analysis reduces computation but is shown to perform poorly in resonance regions when resonances are closely spaced. An improved approximation also based on classical analysis is developed and is shown to behave well in these regions for a numerical example. An inquiry concerning a “best” diagonalizable damping representation leads to a frequency dependent, load distribution dependent damping matrix that may in some cases aid computation and support visualization.

Investigating Vertical Load Distribution and Shoring Systems of Reinforced Concrete Buildings during Construction

2010 ◽  
Vol 163-167 ◽  
pp. 1369-1374
Author(s):  
Shu Ping Cong ◽  
Jin Sheng Han ◽  
Shu Ting Liang
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Reinforced Concrete ◽  
Approximate Method ◽  
Load Distribution ◽  
Vertical Load ◽  
The Finite Element Method ◽  
Reinforced Concrete Buildings ◽  
Concrete Buildings ◽  
Concrete Members

The loads of reinforced concrete buildings are bore by shores and early age concrete members during construction. In order to analysis the distribution of vertical load between concrete members and shores, the approximate method was developed based on the finite element method and simplified method. According to the process of construction, seven primary structures were brought forward in the approximate method. The coefficients of vertical load distribution between concrete members and shores are confirmed through the finite element method. The loads of concrete members and shores could be obtained conveniently through the distribution coefficients. Three shoring systems (2S, 2S1R and 3S) could be calculated by the approximate method, so the suitable shoring systems for reinforced concrete buildings would be confirmed.

Influence of Deformation of the Wheel Disk-Type Body on the Tooth Load Distribution over the Facewidth in Helical Gears

2014 ◽  
Vol 680 ◽  
pp. 210-215
Author(s):  
Maciej Krasiński
Keyword(s):  
Load Distribution ◽  
Helical Gears ◽  
Numerical Example ◽  
Gear Wheels ◽  
Wheel Disk ◽  
Selection Of

The article demonstrates one of the ways to reduce uneven load distribution along the width of the gear wheels which can be used in place of expensive modifications of the tooth flanks (crowning). This can be achieved by appropriate selection of the shape of the gear wheels for example the disk shape. The presented numerical example illustrates the above possibility taking into account deformability of the wheel body.

SIMPLIFIED MATHEMATICS FOR MULTIPLE BIOASSAYS

1960 ◽  
Vol XXXV (III) ◽  
pp. 454-468 ◽  
Author(s):  
R. Borth
Keyword(s):  
Parallel Line ◽  
Numerical Example ◽  
Dose Levels

ABSTRACT Gaddum's simplified system of computation for the analysis of biological parallel-line assays is extended to the assay of several unknown preparations simultaneously against the same standard, using up to four dose levels of each preparation. Complete working directions and formulae are provided and illustrated by a numerical example. Limiting conditions are briefly discussed.

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