Preliminary study of a subsonic nuclear cruise airplane having a helium-cooled thermal reactor
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Allen, J. L.↗
Engineering topics
Allen, J. L.
Publications and source records attributed to Allen, J. L..
Development of the Manned Orbital Research Laboratory /MORL/ system utilization potential. Task area IV - MORL system improvement study, book 1
Manned Orbital Research Laboratory system improvement study
SYSTEMS DESIGN↗
Analysis of booster systems with a recoverable hypersonic airplane first stage
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Allen, J. L.↗
BACTERIA UNDER SIMULATED MARTIAN CONDITIONS
Behavior of bacteria under simulated martian conditions, and possible effects of these organisms on extraterrestrial life
MARS /PLANET/↗
Bacteria under simulated martian conditions
Bacteria under simulated martian environment
MARS ENVIRONMENT↗
Effect of diurnal freeze-thawing on survival and growth of selected bacteria
Diurnal freeze-thawing and survival of selected bacteria
BACTERIA↗
PERFORMANCE SUMMARY AND ANALYSIS OF A MACH 3.0 DESIGN AXISYMMETRIC ALL-EXTERNAL-COMPRESSION DOUBLE-CONE INLET FROM MACH NUMBER 3.0 TO 0.8
Axisymmetric external compression double cone inlet - mach 3 to 0.8 - pressure recovery, mass flow ratio, cowl pressure and additive drag
AIR INLET↗
PERFORMANCE OF A MACH NUMBER OF 3.0 DESIGN AXISYMMETRIC DOUBLECONE EXTERNAL-COMPRESSION INLET IN MACH NUMBER RANGE 2.07 TO 1.48
Axisymmetric double cone compression inlet
AERODYNAMICS↗
Survey of supersonic inlets for high Mach number applications
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Allen, J. L.↗
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
Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser
TURBOJET ENGINE↗
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↗
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↗
PUMPING CHARACTERISTICS FOR SEVERAL SIMULATED VARIABLEGEOMETRY EJECTORS WITH HOT AND COLD PRIMARY FLOW
Pumping characteristics of variable geometry ejectors with hot and cold primary nozzle flow
AFTERBURNER↗