A Digital Program for Calculating the Interaction Between Flexible Structures, Unsteady Aerodynamics and Active Controls [PDF]
A computer program, ISAC, is described which calculates the stability and response of a flexible airplane equipped with active controls. The equations of motion relative to a fixed inertial coordinate system are formulated in terms of the airplane's ...
Adams, W. M., Jr., Peele, E. L.
core +1 more source
Subsonic flutter analysis addition to NASTRAN [PDF]
, 1973 A subsonic flutter analysis capability has been developed for NASTRAN, and a developmental version of the program has been installed on the CDC 6000 series digital computers at the Langley Research Center.
Doggett, R. V., Jr., Harder, R. L.
core +1 more source
Developments in steady and unsteady aerodynamics for use in aeroelastic analysis and design [PDF]
A review is given of seven research projects which are aimed at improving the generality, accuracy, and computational efficiency of steady and unsteady aerodynamic theory for use in aeroelastic analysis and design.
Bland, S. R., Yates, E. C., Jr.
core +1 more source
Influence of blade aerodynamic model on prediction of helicopter rotor aeroacoustic signatures [PDF]
, 2011 Brown’s vorticity transport model has been used to investigate how the local blade aerodynamic model influences the quality of the prediction of the high-frequency airloads associated with blade–vortex interactions, and thus the accuracy with which the ...
Boyd D. D. +14 more
core +1 more source
Lifting surface theory for a helicopter rotor in forward flight [PDF]
, 1984 A lifting surface theory was developed for a helicopter rotor in forward flight for compressible and incompressible flow. The method utilizes the concept of the linearized acceleration potential and makes use of the vortex lattice procedure. Calculations
Runyan, H. L., Tai, H.
core +2 more sources
Unsteady transonic flow calculations for interfering lifting surface configurations [PDF]
Unsteady transonic flow calculations are presented for aerodynamically interfering lifting surface configurations. Calculations are performed by extending the XTRAN3S (Version 1.5) unsteady transonic small-disturbance code to allow the treatment of an ...
Batina, J. T.
core +1 more source
Finite difference modeling of rotor flows including wake effects [PDF]
Rotary wing finite difference methods are investigated. The main concern is the specification of boundary conditions to properly account for the effect of the wake on the blade.
Caradonna, F. X., Desopper, A., Tung, C.
core +1 more source
Calculation of viscous effects on transonic flow for oscillating airfoils and comparisons with experiment [PDF]
A method is described for calculating unsteady transonic flow with viscous interaction by coupling a steady integral boundary-layer code with an unsteady, transonic, inviscid small-disturbance computer code in a quasi-steady fashion. Explicit coupling of
Bland, Samuel R., Howlett, James T.
core +1 more source
Integral-equation methods in steady and unsteady subsonic, transonic and supersonic aerodynamics for interdisciplinary design [PDF]
Progress in the development of computational methods for steady and unsteady aerodynamics has perennially paced advancements in aeroelastic analysis and design capabilities. Since these capabilities are of growing importance in the analysis and design of
Yates, E. Carson, Jr.
core +1 more source
Measured unsteady transonic aerodynamic characteristics of an elastic supercritical wing with an oscillating control surface [PDF]
Transonic steady and unsteady aerodynamic data were measured on a large elastic wing in the NASA Langley Transonic Dynamics Tunnel. The wing had a supercritical airfoil shape and a leading-edge sweepback of 28.8 deg.
Brooks J. D. +7 more
core +2 more sources