PERFORMANCE OF A BLUNT-LIP SIDE INLET WITH RAMP BLEED, BYPASS, AND A LONG CONSTANT-AREA DUCT AHEAD OF THE ENGINE- MACH NUMBERS 0.66 AND 1.5 TO 2.1
Blunt-lip side inlet with ramp bleed, bypass, and duct ahead of engine
BOUNDARY LAYER CONTROL↗
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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.
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TESTS OF A TWIN-DUCT INDUCTION SYSTEM FOR A MACH NUMBER RANGE OF 0.78 TO 2.07
Flight tests of twin-duct induction system
DUCT↗
AERODYNAMICS OF TILTING DUCTED-FAN CONFIGURATIONS
Tests of wing-tip-mounted ducted fans for v/stol aircraft
WING PROFILE↗
Wind-tunnel test of a full-scale, 1.1 pressure ratio, ducted lift-cruise fan
Fixed blade angle, ducted, tip-turbine-driven, cruise fan as aircraft propulsive device at high subsonic speed
SUBSONIC SPEED↗
State-of-the-art literature survey on fabrication techniques of advanced ducting components
Manufacturing techniques and alloy materials for cryogenic duct systems
DUCT↗
Investigation and analysis of the electropolishing process for saturn ducting final report, 15 mar. - 31 dec. 1962
Immersion and impingement electropolishing methods for increasing corrosion resistance of stainless steels and nickel alloys used in propellant ducts
NICKEL ALLOY↗
Performance of Twin-duct Variable-geometry Side Inlets at Mach Numbers of 1.5 to 2.0
Supersonic wind tunnel test of twin-duct variable geometry side inlets
VARIABLE GEOMETRY STRUCTURE↗
Performance characteristics of a 4-foot- diameter ducted fan at zero angle of attack for several fan blade angles
Static and propulsive performance characteristics of ducted fan at zero angle of attack for several fan blade angles
DUCTED FAN↗
Concentration profile establishment of binary gas mixture in swirl and duct flows
Inviscid hydrodynamical model for determining density profile of binary single phase gas mixture in swirl and duct flows
MATHEMATICAL MODEL↗
Longitudinal and lateral-directional aerodynamic characteristics of a large-scale, V/STOL model with four tilting ducted fans arranged in a dual tandem configuration
Longitudinal and lateral-directional aerodynamic characteristics of large scale, V/STOL model with four tilting ducted fans arranged in dual tandem configuration
SCALE MODEL↗
Predicted and measured performance of two full-scale ducted propellers
Predicted and measured performance of two full- scale ducted propellers at angle of attack - analytical model development
SHROUDED PROPELLER↗
Liquid hydrogen flexible ducting technology Final report, Jun. 1964 - Jan. 1966
Liquid hydrogen flexible ducting technology for space flight vehicle applications
DUCT↗
Propellant feed ducting and engine gimbal lines for the Saturn vehicle
Liquid propellant feed ducting and engine gimbal lines for Saturn vehicles
LIQUID PROPELLANT↗
A wind-tunnel investigation of a 7-foot- diameter ducted propeller
Aerodynamic characteristics of seven foot diameter ducted propeller in wind tunnel
PROPELLER↗
Review of high-frequency radiowave ducting in the magnetosphere of the earth
High frequency radio wave ducting review for earth magnetosphere
MAGNETOSPHERE↗
Aerodynamic forces of an oscillating cylindrical duct with an internal flow.
Aerodynamic forces of harmonically oscillating cylindrical duct with supersonic internal flow within framework of potential flow theory
FLOW THEORY↗
Transmittance properties of a curved specularly reflecting duct irradiated by a collimated beam.
Energy transmitting characteristics and wall local energy absorption distribution of curved specular reflecting duct irradiated by collimated beam
ENERGY TRANSFER↗
Model ducted propulsor noise characteristics at takeoff conditions
A model Advanced Ducted Propulsor (ADP) was tested in the NASA Lewis Low-Speed Anechoic Wind Tunnel at a simulated takeoff velocity of Mach 0.2. The model was designed and manufactured by Pratt & Whitney. The 16-blade rotor ADP was tested with 22- and 40-vane stators to achieve cut-on and cut-off criterion with respect to propagation of the fundamental rotor-stator interaction tone. Additional test parameters included three inlet lengths, three nozzle sizes, two spinner configurations, and two rotor rub strip configurations. The model was tested over a range of rotor blade setting angles and inlet angles of attack. Acoustic data were taken with a sideline translating microphone probe and with a unique inlet microphone probe that identified inlet rotating acoustic modes. The beneficial acoustic effects of cut-off were clearly demonstrated. A 10-dB fundamental tone reduction was associated with the long inlet and 40-vane stator. The fundamental tone level was essentially unaffected by inlet angle of attack at rotor speeds of above 96% design.
TRT-EXPERIMENTAL↗