Add to ORKGFixed geometry wind tunnel model of auxiliary inlet ejector with clamshell flow diverter from Mach 0 to 1.
The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height ...
An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft superson...
Performance of vortex generators installed aft of inlet throat on centerbody evaluated at Mach numbe...
Performance of aerodynamically positioned auxiliary inlet ejector nozzle at Mach numbers from 0 to 2...
Simulated take-off, transonic acceleration, and supersonic flight conditions using auxiliary inlet e...
Auxiliary inlet ejector nozzle with fixed doors and single-hinge trailing-edge flap
Performance of auxiliary inlet ejector nozzle with floating inlet doors and floating single hinge tr...
Performance of auxiliary inlet ejector nozzle with fixed inlet doors and triple-hinge trailing edge ...
Static performance of an auxiliary inlet ejector nozzle for supersonic-cruise aircraf
Flight performance of auxiliary inlet ejector and plug nozzle at transonic speed
Wind tunnel model tests were conducted to demonstrate the aerodynamic performance improvements of a ...
A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-sc...
Wind-tunnel tests were conducted on a baseline scramjet inlet model having fixed geometry and swept...
Pressure-recovery characteristics of a nacelle-type-spike inlet in combination with a vertical-wedge...
NASA Lewis is currently engaged in a research effort as a team member of the High Alpha Technology P...
The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height ...
An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft superson...
Performance of vortex generators installed aft of inlet throat on centerbody evaluated at Mach numbe...
Performance of aerodynamically positioned auxiliary inlet ejector nozzle at Mach numbers from 0 to 2...
Simulated take-off, transonic acceleration, and supersonic flight conditions using auxiliary inlet e...
Auxiliary inlet ejector nozzle with fixed doors and single-hinge trailing-edge flap
Performance of auxiliary inlet ejector nozzle with floating inlet doors and floating single hinge tr...
Performance of auxiliary inlet ejector nozzle with fixed inlet doors and triple-hinge trailing edge ...
Static performance of an auxiliary inlet ejector nozzle for supersonic-cruise aircraf
Flight performance of auxiliary inlet ejector and plug nozzle at transonic speed
Wind tunnel model tests were conducted to demonstrate the aerodynamic performance improvements of a ...
A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-sc...
Wind-tunnel tests were conducted on a baseline scramjet inlet model having fixed geometry and swept...
Pressure-recovery characteristics of a nacelle-type-spike inlet in combination with a vertical-wedge...
NASA Lewis is currently engaged in a research effort as a team member of the High Alpha Technology P...
The results indicated increases in auxiliary-inlet pressure recovery with increases in scoop height ...
An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft superson...
Performance of vortex generators installed aft of inlet throat on centerbody evaluated at Mach numbe...