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NACA Research Memorandums
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Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine
Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers
Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures
Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane
The effect of accelerating a hypothetical aircraft through the transonic range with controls fixed
Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor
The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds
Effect of Various Modifications on Drag and Longitudinal Stability and Control Characteristics at Transonic Speeds of a Model of the XF7U-1 Tailless Airplane: NACA Wing-FLow Method, TED No. NACA DE 307
Effect of wing-tank location on the drag and trim of a swept-wing model as measured in flight at transonic speeds
An Experimental Investigation of a Jet-Engine Nacelle in Several Positions on a 37.25 Degree Swept-Back Wing
Experimental investigation of thrust augmentation of 4000-pound-thrust axial-flow-type turbojet engine by interstage injection of water-alcohol mixtures in compressor
Flight Investigation of the Pressure Distributions and Loads on a Front and Rear Sliding Canopy
Full-Scale Investigation of Boundary-Layer Control by Suction Through Leading-Edge Slots on a Wing-Fuselage Configuration Having 47.5 Degree Leading-Edge Sweep With and Without Flaps
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.40
Maximum-Lift Investigation of a 1/40-Scale X-1 Airplane Wing at Mach Numbers From 0.60 to 1.15
Model Ditching Investigations of Three Airplanes Equipped With Hydro-Skis
Model ditching investigations of three airplanes equipped with hydro-skis
Pressure Coefficients at Mach Numbers from 0.60 to 0.85 for a Semispan Wing with NACA 0012-64 Section, 20-Percent-Chord Plain Aileron, and 0 Degree and 45 Degree Sweepback
Pressure Distributions on the Blade Sections of the NACA 10-(5)(066)-03 Propeller Under Operating Conditions
Rough-Water Tests of Models of the Vosper and Plum Planing Boats
Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Similar to One Proposed by Douglas Aircraft Company, Inc.
Tests of a Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Stability and Control
Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the Douglas X-3 Research Airplane, Study 41-B
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: stability and control characteristics
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