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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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NACA Research Memorandums
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Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine
A Study of Injection Processes for 15-percent Fluorine-85- Percent Oxygen and Heptane in a 200-pound-thrust Rocket Engine
Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01
Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50
Preliminary Free-Jet Performance of XRJ43-MA-3 Ram-Jet Engine at a Mach Number of 2.70
Altitude Performance of a 20-Inch-Diameter Ram-Jet Engine Investigated in a Free-Jet Facility at Mach Number 3.0
Experimental Investigation of Laminar-Boundary-Layer Control on an Airfoil Section Equipped With Suction Slots Located at Discontinuities in the Surface Pressure Distribution
Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection
Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine
Altitude Free-Jet Investigation of Dynamics of a 28-Inch-Diameter Ram-Jet Engine
Relation of Turbojet Propulsion System Development to the Strategic Bomber Mission
Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane
Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the Douglas D-558-I Airplane for a 1 g Stall, a Speed Run to a Mach Number of 0.90, and a Wind-Up Turn at a Mach Number of 0.86
Some Transonic Aerodynamic Characteristics of a Model Similar to the McDonnell F3H-2N Airplane
Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 4. - Delta-Wing Heavy-Bomber Configuration With Large Store. Mach Number, 1.61
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 3 - Swept-Wing Fighter-Bomber Configuration With Large and Small Stores. Mach Number, 1.61
Liquid Hydrogen as a Jet Fuel for High-Altitude Aircraft
Influence of Boric Oxide Deposition on Turbojet-Engine Operation
Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50
An Analytic Study of Turbojet Engine Thrust Augmentation With Liquid Hydrogen, Pentaborane, Magnesium Slurry, and JP-4 Afterburner Fuels and a 220-Second Impulse Rocket
Investigation of Ejection Release Characteristics of Four Dynamically Scaled Internal-Store Shapes From a 1/17-Scale Simulated Bomb Bay of the Republic F-105 Airplane at Mach Numbers of 1.39 and 1.98
Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Mach Numbers 1.41 and 2.01
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