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Technical Report Archive and Image Library
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National Advisory Committee for Aeronautics Collection
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Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine
Off-Design Performance of Divergent Ejectors
Off-Design Performance of Divergent Ejectors
Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8
Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination
Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
A Flight-Test Study of Total-Pressure Distortion in a Thick-Lipped Nose Inlet
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Transonic investigation of yawed wings of aspect ratios 3 and 6 with a Sears-Haack body and with symmetrical and asymmetrical bodies indented for a Mach number of 1.20
Viscous Flows in Inlets
Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Degree Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
Longitudinal Stability Investigation of a Vertical-Take-Off-and-Landing Airplane Configuration With Simulated Jet Intake and Exhaust at Mach Numbers of 1.61 and 2.01
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
Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1
Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1
Flight Investigation of Factors Affecting the Choice of Minimum Approach Speed for Carrier-Type Landings of a Swept-Wing Jet Fighter Airplane
Lateral Stability Investigation at Mach Numbers From 0.8 to 1.7 of Two Rocket-Boosted Models of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail
Theoretical Determination of Low-Drag Supercavitating Hydrofoils and Their Two-Dimensional Characteristics at Zero Cavitation Number
Transonic Investigation of an Axial-Flow Compressor Rotor With a Hub-Tip Ratio of 0.75 and Blades Having NACA A(Sub 2)I(Sub 8b) Mean Lines
Analysis of two-stage-turbine efficiency characteristics in terms of work and speed requirements
Effects of Internal-Area Distribution, Spike Translation, and Throat Boundary-Layer Control on Performance of a Double-Cone Axisymmetric Inlet at Mach Numbers From 3.0 to 2.0
Effects of wing warp on the lift, drag, and static longitudinal stability characteristics of an aircraft configuration having an arrow wing of aspect ratio 1.86 at Mach numbers from 1.1 to 1.7
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