An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback
Explore the source record for details and available documents.
Spearman, M Leroy↗
SEARCH · Search NASA
Results for “SUPERSONIC AIRCRAFT”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
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 1.59
Explore the source record for details and available documents.
Spearman, M Leroy↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Static Lateral Stability Characteristics at Mach Numbers of 1.40 and 1.59
Explore the source record for details and available documents.
Spearman, M Leroy↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : a Pressure-distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.59
Explore the source record for details and available documents.
Cooper, Morton↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Static Lateral Control Characteristics at Mach Numbers of 1.40 and 1.59
Explore the source record for details and available documents.
Robinson, Ross B↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59
Explore the source record for details and available documents.
Smith, Norman F↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Section and 40 Degree Sweepback : a Pressure-distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.40
Explore the source record for details and available documents.
Smith, Norman F↗
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback
Explore the source record for details and available documents.
Gapcynski, John P↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degrees Sweepback : Estimated Downwash Angles Derived from Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59
Explore the source record for details and available documents.
Grant, Frederick C↗
The Sodium Hydroxide Reactor : Effect of Reactor Variables on Criticality and Fuel-element Temperature Requirements for Subsonic and Supersonic Aircraft Nuclear Propulsion
Explore the source record for details and available documents.
Bogart, Donald↗
The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations
Explore the source record for details and available documents.
Mitchell, Jesse L↗
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : stability and control characteristics at a Mach number of 1.61 of the complete configuration equipped with spoilers
Explore the source record for details and available documents.
Driver, Cornelius↗
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Aerodynamic Characteristics of the Configuration Equipped with a Canard Control Surface at a Mach Number of 1.89
Explore the source record for details and available documents.
Spearman, M Leroy↗
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : static longitudinal and lateral stability and control characteristics at a Mach number of 1.89
Explore the source record for details and available documents.
Spearman, M Leroy↗
Preliminary discussion of fuel temperatures attained in supersonic aircraft
Explore the source record for details and available documents.
Gibbons, Louis C↗
Study of Ram-air Heat Exchangers for Reducing Turbine Cooling-air Temperature of a Supersonic Aircraft Turbojet Engine
The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude The sizes and weights of the cores of heat exchangers were determined analytically for possible application for reducing turbine cooling-air temperatures of an engine designed for a Mach number of 2.5 and an altitude of 70,000 feet. A compressor-bleed-air weight flow of 2.7 pounds per second was assumed for the coolant; ram air was considered as the other fluid. Pressure drops and inlet states of both fluids were prescribed, and ranges of compressor-bleed-air temperature reductions and of the ratio of compressor-bleed to ram-air weight flows were considered.
Diaguila, Anthony J↗
Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations
Explore the source record for details and available documents.
Spearman, M Leroy↗
Wind-tunnel Investigation at a Mach Number of 2.01 of Forebody Strakes for Improving Directional Stability of Supersonic Aircraft
Explore the source record for details and available documents.
Driver, Cornelius↗