Performance of a mach 3.0 external-internal- compression axisymmetric inlet at mach numbers from 2.0 to 3.5
External-internal-compression axisymmetric inlet performance at supersonic speeds
INTERNAL COMPRESSION INLET↗
SEARCH · Engineering Papers
Results for “Inlet”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Performance of a double-ramp side inlet with combinations of fuselage, ramp, and throat boundary-layer removal, mach number range, 1.5 to 2.0
Double-ramp side inlet with combinations of fuselage, ramp, and throat boundary layer removal
RAMP↗
Investigation of an underslung normal-wedge inlet at free-stream mach numbers from 1.50 to 1.99
Wedge and scoop air inlet performance and thrust minus drag comparisons at free stream in supersonic wind tunnel test
SUPERSONIC WIND TUNNEL↗
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50
Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7
ISENTROPIC PROCESS↗
Design and overall performance of a two-stage axial-flow pump with a tandem-row inlet stage
Inlet stage group for high suction specific speed multistage axial flow pump
INLET FLOW↗
Investigation of an on-off inlet shock- position control on a 16-inch ram-jet engine
On-off inlet shock positioning equipment on 16 inch ramjet engine
INLET↗
Afterburner Performance with Combustion-chamber Lengths from 10 to 62 Inches at Several Afterburner-inlet Temperatures
Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner
AFTERBURNER↗
Investigation of an Underslung Scoop Inlet at Mach Numbers to 1.99
Supersonic wind tunnel test of underslung scoop inlet on body of revolution
BODY OF REVOLUTION↗
Computer program for calculating flow fields in supersonic inlets
Fortran IV computer program to calculate flow fields in supersonic inlets
COMPUTER PROGRAM↗
Bluntness and boundary layer displacement effects on hypersonic inlet flow fields.
Bluntness and boundary layer displacement effects on air breathing engine hypersonic inlet flow fields
AIR BREATHING ENGINE↗
The effects of boundary-layer removal through throat slots on the internal performance of a side inlet at Mach numbers of 2.0 and 2.3
Wind tunnel study of boundary-layer-control throat bleed slot variations on internal performance of side inlet at Mach numbers 2.0 and 2.3
WIND TUNNEL↗
Investigation of the Air-flow-regulation Characteristics of a Translating-spike Inlet with Two Oblique Shocks from Mach 1.6 to 2.0
Translating spike inlet air flow regulation characteristics from transonic to supersonic speeds at zero angle of attack
AIR INLET↗
An investigation of splitter plates for the aerodynamic separation of twin inlets at Mach 2.5
Splitter plates for aerodynamic separation of supersonic twin inlet propulsion system
TWIN JET↗
An investigation of splitter plates for supersonic twin inlets
Splitter plates for aerodynamic isolation of supersonic twin inlets
SUPERSONIC FLOW INLET↗
Charts of additive drag coefficient and mass-flow ratio for inlets utilizing right circular cones at zero angle of attack
Charts of additive drag coefficient and mass flow ratio for inlets utilizing right circular cones at zero angle of attack
CHART↗
Investigation of high-angle-of-attack performance of a 14 deg ramp-type inlet in various circumferential body locations, Mach number range 1.5 to 2.0
Internal flow performance of fixed 14 deg ramp inlet from zero to 20 deg angle of attack at supersonic free stream
SUPERSONIC FLOW↗
Performance Characteristics of an Underslung Vertical-wedge Inlet with Porous Suction at Mach Numbers of 0.63 and 1.5 to 2.0
Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
SUCTION↗
Analytical study of aerodynamic means of controlling supersonic inlet flow, part I Technical report no. 495B
Means for achieving variable geometry supersonic inlet without using mechanical devices
INLET FLOW↗