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NACA Research Memorandums
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Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor
Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane
The effect of blunt-trailing-edge elevons on the longitudinal and lateral handling qualities of the semitailless airplane
Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids
Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System
Effects of Free-Stream Reynolds Number, Engine Installation, and Model Scale on Stability Characteristics of a Translating-Spike Inlet at Mach 2.0
Effect of Design Changes of Operating Conditions on Combustion and Operational Performance of a 28-Inch Diameter Ram-Jet Engine
A Wind-Tunnel Investigation of the Stability of the Antisubmarine Rocket Mk 1 Mod 0
Experimental Investigation of Extreme Internal Flow Turning at the Cowl Lip of an Axisymetric Inlet at a Mach Number of 2.95
The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5 - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number, 2.01
Free-Flight Aerodynamic-Heating Data at Mach Numbers Up to 10.9 on a Flat-Faced Cylinder
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-Effect of Method of Positioning the Radar Antenna on the Speed of Response
Thermal Stability of a Commercial Propyl Pentaborane (HEF-2) in the Range 147 Degree to 190 Degree C
Investigation of an Underslung Scoop Inlet at Mach Numbers to 1.99
Drag at Model Trim Lift of a 1/15-Scale Convair B-58 Supersonic Bomber
Investigation of shock diffusers at Mach number 1.85 3: multiple-shock and curved-contour projecting cones
An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings
Free-Flight Investigation of Fullspan, 0.2 Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Taper, Aspect Ratio, and Section-Thickness Ratio
Theoretical analysis of the performance of a supersonic ducted rocket
Effects of Obstructions in Compressor Inlet on Blade Vibration in 10-Stage Axial-Flow Compressor
Preliminary investigation of porous walls as a means of reducing tunnel boundary effects at low-supersonic Mach numbers
Drag of a Wing-Body Configuration Consisting of a Swept-Forward Tapered Wing Mounted on a Body of Fineness Ratio 12 Measured During Free Fall at Transonic Speeds
Flight Characteristics at Low Speed of Delta-Wing Models
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