Add to ORKGContains theoretical and experimental analysis of circular inlets having a central body at Mach numbers of 3.30, 2.75, and 2.45. The inlets have been designed in order to have low drag and high pressure recovery. The pressure recoveries obtained are of the same order of magnitude as those previously obtained by inlets having very large external drag
An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum f...
A general discussion of the air-inlet problem is presented. Recently obtained drag and pressure-reco...
Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-...
A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is conside...
A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is conside...
A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is conside...
Contains theoretical and experimental analysis of circular inlets having a central body at Mach numb...
An extensive program was undertaken to investigate the effect of several geometric variables on the ...
The effects of inlet circumferential position around the fuselage on the characteristics of a half-c...
An investigation has been made with rocket-propelled models in free flight to determine the external...
An analysis of inlet-turbojet-engine matching for a range of Mach numbers up to 2.0 indicates large ...
Detailed pressure measurements were made of the flow distortion just inside the cowl lip of a fixed-...
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspe...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
The drag and pressure recovery of an NACA submerged-inlet model and an NACA series I nose-inlet mode...
An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum f...
A general discussion of the air-inlet problem is presented. Recently obtained drag and pressure-reco...
Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-...
A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is conside...
A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is conside...
A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is conside...
Contains theoretical and experimental analysis of circular inlets having a central body at Mach numb...
An extensive program was undertaken to investigate the effect of several geometric variables on the ...
The effects of inlet circumferential position around the fuselage on the characteristics of a half-c...
An investigation has been made with rocket-propelled models in free flight to determine the external...
An analysis of inlet-turbojet-engine matching for a range of Mach numbers up to 2.0 indicates large ...
Detailed pressure measurements were made of the flow distortion just inside the cowl lip of a fixed-...
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspe...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
The drag and pressure recovery of an NACA submerged-inlet model and an NACA series I nose-inlet mode...
An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum f...
A general discussion of the air-inlet problem is presented. Recently obtained drag and pressure-reco...
Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-...