Add to ORKGThe results of a theoretical investigation of geometric variables for lift-cruise-fan, tilting nacelle inlets operating at high incidence angles are presented. These geometric variables are investigated for their effects on surface static to free stream pressure ratio, and the separation parameters of maximum to diffuser exit surface velocity ratio and maximum surface Mach number for low speed operating conditions. The geometric parameters varied were the internal lip contraction ratio, external forebody to diffuser exit diameter ratio external forebody length to diameter ratio and internal lip major to minor axis ratio
Concepts are investigated for obtaining both low cowl drag and good inlet performance at high angles...
Pressure distributions on three inlets having different cowl lengths were obtained in the Langley 16...
Experimental results are presented on aerodynamic effects of geometric variations in upper surface b...
A systematic theoretical study of VTOL tilt-nacelle inlet design parameters is reported. The paramet...
Inlets for tilt-nacelle VTOL aircraft must operate over a wide range of incidence angles and engine ...
Experimental data from several model inlets are used to generate two parameters which are related to...
Low speed wind tunnel tests were conducted to establish a procedure for determining inlet-lip flow s...
Test data were obtained with a 1/4 scale cold flow model of the inlet at freestream velocities from ...
The results of an analytical study to investigate internal and external surface Mach numbers on seve...
The theoretical analysis methods, potential flow, and boundary layer, used at Lewis are described. R...
Pressure distributions on three NACA 1-series inlets have been obtained in the Langley 16-Foot Trans...
Engine inlets for subsonic V/STOL aircraft must operate over a wide range of conditions without inte...
Flow distortions were measured at the inlet face and diffuser exit of three axisymmetric inlets oper...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
An investigation was conducted in the Langley V/STOL tunnel to determine the upwash flow angles in t...
Concepts are investigated for obtaining both low cowl drag and good inlet performance at high angles...
Pressure distributions on three inlets having different cowl lengths were obtained in the Langley 16...
Experimental results are presented on aerodynamic effects of geometric variations in upper surface b...
A systematic theoretical study of VTOL tilt-nacelle inlet design parameters is reported. The paramet...
Inlets for tilt-nacelle VTOL aircraft must operate over a wide range of incidence angles and engine ...
Experimental data from several model inlets are used to generate two parameters which are related to...
Low speed wind tunnel tests were conducted to establish a procedure for determining inlet-lip flow s...
Test data were obtained with a 1/4 scale cold flow model of the inlet at freestream velocities from ...
The results of an analytical study to investigate internal and external surface Mach numbers on seve...
The theoretical analysis methods, potential flow, and boundary layer, used at Lewis are described. R...
Pressure distributions on three NACA 1-series inlets have been obtained in the Langley 16-Foot Trans...
Engine inlets for subsonic V/STOL aircraft must operate over a wide range of conditions without inte...
Flow distortions were measured at the inlet face and diffuser exit of three axisymmetric inlets oper...
An investigation was conducted in the Langley 16-foot transonic tunnel to determine the performance ...
An investigation was conducted in the Langley V/STOL tunnel to determine the upwash flow angles in t...
Concepts are investigated for obtaining both low cowl drag and good inlet performance at high angles...
Pressure distributions on three inlets having different cowl lengths were obtained in the Langley 16...
Experimental results are presented on aerodynamic effects of geometric variations in upper surface b...