Several topics in optimal symmetric flight of airbreathing vehicles are examined. In one study, an approximation scheme designed for onboard real-time energy management of climb-dash is developed and calculations for a high-performance aircraft presented. In another, a vehicle model intermediate in complexity between energy and point-mass models is explored and some quirks in optimal flight characteristics peculiar to the model uncovered. In yet another study, energy-modelling procedures are re-examined with a view to stretching the range of validity of zeroth-order approximation by special choice of state variables. In a final study, time-fuel tradeoffs in cruise-dash are examined for the consequences of nonconvexities appearing in the cla...
Two separated flow computer programs and a semiempirical method for incorporating the experimentally...
The objective of the second phase of the Euler Technology Assessment program was to evaluate the abi...
The NASA Dryden Flight Research Center has flight tested two X-29A aircraft at low and high angles o...
The mathematical model and associated computer program to simulate a twin-tailed high performance fi...
NASA Dryden Flight Research Center has developed a second-generation flight test fixture for use as ...
Wind-borne debris is considered as a major source of damage to civil structures during strong wind s...
The work completed to date is comprised of the following: a simple vehicle model representative of t...
A new computer code was developed to solve the two-dimensional or axisymmetric, Reynolds averaged, u...
A study of the full-potential modeling of a blade-vortex interaction was made. A primary goal of thi...
This project is intended to research and develop new nonlinear methodologies for the control and sta...
The Local Flow Management/Profile Descent (LFM/PD) algorithm designed for the NASA Transport System ...
The design and development of an airborne flight-test experiment to study nonreacting gas jets injec...
The general rotorcraft aeromechanical stability program (GRASP) was developed to calculate aeroelast...
The separated flow method is evaluated. This method was developed for moderately swept wings with mu...
The HSCT Flight Controls Group has developed longitudinal control laws, utilizing PTC aeroelastic fl...
Two separated flow computer programs and a semiempirical method for incorporating the experimentally...
The objective of the second phase of the Euler Technology Assessment program was to evaluate the abi...
The NASA Dryden Flight Research Center has flight tested two X-29A aircraft at low and high angles o...
The mathematical model and associated computer program to simulate a twin-tailed high performance fi...
NASA Dryden Flight Research Center has developed a second-generation flight test fixture for use as ...
Wind-borne debris is considered as a major source of damage to civil structures during strong wind s...
The work completed to date is comprised of the following: a simple vehicle model representative of t...
A new computer code was developed to solve the two-dimensional or axisymmetric, Reynolds averaged, u...
A study of the full-potential modeling of a blade-vortex interaction was made. A primary goal of thi...
This project is intended to research and develop new nonlinear methodologies for the control and sta...
The Local Flow Management/Profile Descent (LFM/PD) algorithm designed for the NASA Transport System ...
The design and development of an airborne flight-test experiment to study nonreacting gas jets injec...
The general rotorcraft aeromechanical stability program (GRASP) was developed to calculate aeroelast...
The separated flow method is evaluated. This method was developed for moderately swept wings with mu...
The HSCT Flight Controls Group has developed longitudinal control laws, utilizing PTC aeroelastic fl...
Two separated flow computer programs and a semiempirical method for incorporating the experimentally...
The objective of the second phase of the Euler Technology Assessment program was to evaluate the abi...
The NASA Dryden Flight Research Center has flight tested two X-29A aircraft at low and high angles o...