Add to ORKGAn MSC/NASTRAN finite element model of the higher harmonic control configured OH-6A helicopter fuselage was developed. This finite element model was verified by performing various model checkouts and correlation with results from a ground vibration test
To support the reusable launch vehicle concept study, the aerodynamic data and surface pressure for ...
Viewgraphs on finite element model and identification procedure are presented. Topics covered includ...
The Space Station structure has been baselined to be a 5 M (16.4 ft) erectable truss. This structure...
A computational procedure is described which can be used efficiently in identifying modeling errors ...
This paper deals with the application of a three-dimensional, unsteady Navier-Stokes code for predic...
An outline of the organization and capabilities of the Engine Structures Computational Simulator (Si...
The design of turbomachinery blades requires the prevention of flutter for all operating conditions....
A summary of findings of the Flight Elements Subpanel is given in viewgraph form. Topics covered inc...
The current program is aimed at providing a physical picture of the flow physics and quantitative tu...
As a result of high cycle fatigue, hydrogen embrittlement, and extended engine use, it was observed ...
Vugraphs are presented on the effect of cruise Mach number on the maximum takeoff weight of the High...
Complexities of liquid rocket engine heat transfer which involve the injector faceplate and regenera...
Extensively axisymmetric and non-axisymmetric Single Stage To Orbit (SSTO) vehicles are considered. ...
Film/dump cooling a rocket nozzle with fuel rich gas, as in the National Launch System (NLS) Space T...
The linearization and simplification of a nonlinear, literal model for flexible aircraft is highligh...
To support the reusable launch vehicle concept study, the aerodynamic data and surface pressure for ...
Viewgraphs on finite element model and identification procedure are presented. Topics covered includ...
The Space Station structure has been baselined to be a 5 M (16.4 ft) erectable truss. This structure...
A computational procedure is described which can be used efficiently in identifying modeling errors ...
This paper deals with the application of a three-dimensional, unsteady Navier-Stokes code for predic...
An outline of the organization and capabilities of the Engine Structures Computational Simulator (Si...
The design of turbomachinery blades requires the prevention of flutter for all operating conditions....
A summary of findings of the Flight Elements Subpanel is given in viewgraph form. Topics covered inc...
The current program is aimed at providing a physical picture of the flow physics and quantitative tu...
As a result of high cycle fatigue, hydrogen embrittlement, and extended engine use, it was observed ...
Vugraphs are presented on the effect of cruise Mach number on the maximum takeoff weight of the High...
Complexities of liquid rocket engine heat transfer which involve the injector faceplate and regenera...
Extensively axisymmetric and non-axisymmetric Single Stage To Orbit (SSTO) vehicles are considered. ...
Film/dump cooling a rocket nozzle with fuel rich gas, as in the National Launch System (NLS) Space T...
The linearization and simplification of a nonlinear, literal model for flexible aircraft is highligh...
To support the reusable launch vehicle concept study, the aerodynamic data and surface pressure for ...
Viewgraphs on finite element model and identification procedure are presented. Topics covered includ...
The Space Station structure has been baselined to be a 5 M (16.4 ft) erectable truss. This structure...