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NACA Research Memorandums
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Altitude-wind-tunnel investigations of thrust augmentation of a turbojet engine 1: Performance with tail-pipe burning
Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8 and 19XB-1 Jet- Propulsion Engines: 4 - Analysis of Compressor Performance
Effects of Compressibility on the Characteristics of Five Airfoils
Flight Observations of Aileron Flutter at High Mach Numbers as Affected by Several Modifications
Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Fairchild Lark Pilotless-Aircraft Configuration: Standard Configuration with Wing Flaps Deflected 60 Degrees and Model having Tail in Line with Wings, TED No. NACA 2387
Performance of a 20-inch steady-flow ram jet at high altitudes and ram-pressure ratios
Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70
The use of perforated inlets for efficient supersonic diffusion
Wind-Tunnel Investigation of Bomb-Bay Configurations Intended to Minimize the Tumbling of Light-Weight Bombs
Determination of Stress-Rupture Parameters for Four Heat-Resisting Alloys
Investigation of Thrust Augmentation of a 1600-Pound Thrust Centrifugal-Flow-Type Turbojet Engine by Injection of Refrigerants at Compressor Inlets
Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336
An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane
Preliminary evaluation of the performance of a uniflow two-stroke-cycle spark-ignition engine combined with a blowdown turbine and a steady-flow turbine
Preliminary Investigation at a Mach Number of 1.9 and a Reynolds Number of 2,200,000 of Three Ailerons Applicable to the Bell XS-2 Airplane Design
Wind-Tunnel Investigation of the Low-Speed Stability and Control Characteristics of a Model With a Sweptback Vee Tail and a Sweptback Wing
Preliminary Free-Flight Investigation of the Effect of Airfoil Section on Aileron Rolling Effectiveness at Transonic and Supersonic Speeds
Performance of J33-A-23 Turbojet-Engine Compressor, II, Over-All Performance Characteristics of Compressor with 34-Blade Impeller at Equivalent Impeller Speeds from 6000 to 11,750 RPM
Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a 42.7 Degree Sweptback Wing Having Partial-Span Ailerons
NACA Transonic Wing-Tunnel Test Sections
Spin and Recovery Characteristics of the Northrop XF-89 Airplane
Flight Investigation of 6.25-Inch-Diameter Deacon Rocket and 10-Inch-Scale Model Rocket
An Investigation of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- By 80-Foot Wind Tunnel: Pressure Data
Performance of supersonic axial-flow compressors based on one-dimensional analysis
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