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NACA Research Memorandums
115
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NACA Research Memorandums
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Experimental data for four full-scale conical cooling-air ejectors
Performance of Five Low-Temperature-Ratio Ram-Jet Combustors Over Range of Simulated Altitudes
Slowing-Down Distribution to Indium Resonance of Neutrons From a Ra-Alpha-Be Source in Water-Iron Mixtures
A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane, Ted No. NACA DE 390
Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads
Starting and performance characteristics of a large asymmetric supersonic free-jet facility
A transonic wind-tunnel investigation of the effects of twist and camber with and without incidence, twist and body indentation on the aerodynamic characteristics of a 45 degree sweptback wing-body configuration
The Use of Area Suction to Increase the Effectiveness of a Trailing-Edge Flap on a Triangular Wing of Aspect Ratio 2
Downwash Behind a Triangular Wing of Aspect Ratio 3 - Transonic Bump Method
Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 2: preliminary analysis of over-all performance
Performance of Separation Nose Inlets at Mach Number 5.5
A study of the effects of body shape on the vortex wakes of inclined bodies at a Mach number of 2
Considerations in the adaptation of low-cost fuels to gas-turbine-powered commercial aircraft
Some Experimental Effects of Afterbody Shape on the Zero-Lift Drag of Bodies for Mach Numbers Between 0.8 and 1.3
Summary of Rocket-Model Tests at Zero Lift of the Northrop MX-775B Missile Configuration from Mach Numbers of 0.9 to 1.8
Thermal shock resistance and high-temperature strength of a molybdenum disilicide - aluminum oxide ceramic
A Brief Hydrodynamic Investigation of a Navy Seaplane Design Equipped With a Hydro-Ski
Horizontal-Tail Load Measurements at Transonic Speeds of the Bell X-1 Research Airplane
Static lateral stability characteristics of an airplane model having a 47.7 degree sweptback wing of aspect ratio 6 and the contribution of various model components at a Reynolds number of 4.45 x 10(exp 6)
Transonic Aerodynamic Characteristics of an NACA 64A006 Airfoil Section With a 15-Percent-Chord Leading-Edge Flap
The Vertical-Tail Loads Measured During a Flight Investigation on a Jet-Powered Bomber Airplane
Combustion in the Wake as a Means of Body-Drag Reduction as Determined from Free-Flight Tests of 40-Millimeter Shells
First Landing of Bell X-2 Research Airplane
An Investigation at Transonic Speeds of the Aerodynamic Characteristics of an Air Inlet Installed in the Root of a 45 Degree Sweptback Wing
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