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Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation
Aerodynamic heating of aircraft components
High-Speed Wind-Tunnel Tests of a Model of the Lockheed YP-80A Airplane Including Correlation with Flight Tests and Tests of Dive-Recovery Flaps
Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18
Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions
Combustion efficiency performance of a MIL-F-5624 type fuel and monomethylnapthalene in a single vaporizing combustor
Effect of boundary-layer control and inlet lip shape on the performance of a twin-scoop air-induction system at Mach numbers from 0 to 1.9
Pressure Distribution and Aerodynamic Coefficients Associated With Heat Addition to Supersonic Air Stream Adjacent to Two-Dimensional Supersonic Wing
Investigation of a thin straight wing of aspect ratio 4 by the NACA wing-flow method: Lift and pitching-moment characteristics of the wing alone
A flight evaluation of a wing-shroud-blowing boundary-layer control system applied to the flaps of an F9F-4 airplane
Effect of moderate air flow on the distribution of fuel sprays after injection cut-off
Analysis of coolant-flow requirements for an improved, internal-strut-supported, air-cooled turbine-rotor blade
Experimental Investigation of the Effect of Forebody Bluntness on the Pressure Recovery and Drag of a Twin-Scoop Inlet-Body Combination at Mach Numbers of 1.4 and 1.7
Simulated flight investigation of scaled-speed elastic swept-wing bomber and fighter models coupled wing tip to wing tip
Simulated Flight Investigation of Scaled-Speed Elastic Sweptwing Bomber and Fighter Models Coupled Wing Tip to Wing Tip
Summary of lateral-control research
Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip
An Investigation of the Effects of Sweep on the Characteristics of a High-Aspect-Ratio Wing in the Langley 8-Foot High-Speed Tunnel
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