By David J. Peery
Suitable for undergraduate scholars, this quantity covers equilibrium of forces, house buildings, inertia forces and cargo elements, shear and bending stresses, and beams with unsymmetrical move sections. extra subject matters comprise spanwise air-load distribution, exterior quite a bit at the aircraft, joints and fittings, deflections of constructions, and targeted tools of study. issues concerning a data of aerodynamics seem in ultimate chapters, permitting scholars to check the prerequisite aerodynamics subject matters in concurrent courses.
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Additional resources for Aircraft Structures
This interference, which is actually part of the profile drag, usually varies with the lift coefficient in such a manner that it may be treated as of the form (a + bCL2 ). The part of this profile drag coefficient that is represented by the term (bCL2 ) may be added to the induced drag. ” If this datum lift coefficient is taken to be zero, the total drag coefficient of a complete airplane may be taken, to a good approximation in most cases, as CD = CD0 + kCL2 where CD0 is the drag coefficient at zero lift, and kCL2 is the lift-dependent drag coefficient, denoted by CDL .
The term VD/ν may also be written, from the definition of ν, as ρVD/µ, as earlier in the problem relating to eddy frequency in the flow behind a circular cylinder. It is a very important parameter in fluid flows and is called the Reynolds number. Now consider any parameter representing the geometry of the flow around the bodies at any point relative to them. If this parameter is expressed in a suitable nondimensional form, it can easily be shown by dimensional analysis that it is a function of the Reynolds number and the Mach number only.
For a flat or curved plate in inviscid, incompressible flow the aerodynamic center is theoretically exactly one-quarter of the chord behind the leading edge; however, thickness of the section and viscosity of the fluid tend to place it a few percent further forward as indicated earlier, while compressibility tends to move it backward. For a thin airfoil (or infinite aspect ratio wing) in supersonic flow, the aerodynamic center is theoretically at 50% of the chord. Knowledge of how the pitching moment coefficient about a point distance a behind the leading edge varies with CL may be used to find the position of the aerodynamic center behind the leading edge and the value of the pitching moment coefficient there CMAC .
Aircraft Structures by David J. Peery