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Serial/Series Title:
NACA Research Memorandums
Collection:
Technical Report Archive and Image Library
Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with bypasses discharging in an axial direction
Date: January 30, 1953
Creator: Allen, J L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59488/
Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane II : inlets utilizing half of a conical spike
Date: September 4, 1952
Creator: Allen, J L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59397/
Performance comparison at supersonic speeds of inlets spilling excess flow by means of bow shock, conical shock, or bypass
Date: October 23, 1953
Creator: Allen, J L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59688/
Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
Date: August 3, 1956
Creator: Allen, J. L.
Description: Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc53090/
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
Date: December 28, 1956
Creator: Allen, J. L.
Description: Blunt-lip side inlet with ramp bleed, bypass, and duct ahead of engine.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc52908/
Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0
Date: January 30, 1958
Creator: Allen, J. L.
Description: Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc52901/
Pumping Characteristics for Several Simulated Variablegeometry Ejectors With Hot and Cold Primary Flow
Date: September 8, 1954
Creator: Allen, J. L.
Description: Pumping characteristics of variable geometry ejectors with hot and cold primary nozzle flow.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc52854/
Survey of supersonic inlets for high Mach number applications
Date: April 1, 1958
Creator: Allen, J. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc53198/
Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
Date: August 3, 1956
Creator: Allen, John L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62404/
Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1
Date: December 28, 1956
Creator: Allen, John L
Description: Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successful for small distortions as obtained with throat bleed. By removing boundary-layer air the bypass nearly recovered the total-pressure loss due to the long duct.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc62861/