Search Results

open access

Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 4: Effect of Inlet-Air Temperature, Combustion-Chamber-Inlet Mach Number, and Fuel Volatility on Combustion Performance

Description: Report presenting testing of the effects of the following variables on combustion performance are determined: inlet-air temperature, combustion-chamber-inlet Mach number and pressure, and fuel density and volatility.
Date: July 27, 1951
Creator: Kahn, Robert W.; Nakanishi, Shigeo & Harp, James L., Jr.
Partner: UNT Libraries Government Documents Department
open access

Combustion Instability in an Acid-Heptane Rocket with a Pressurized-Gas Propellant Pumping System

Description: Results of experimental measurements of low-frequency combustion instability of a 300-pound thrust acid-heptane rocket engine were compared to the trends predicted by an analysis of combustion instability in a rocket engine with a pressurized-gas propellant pumping system. The simplified analysis, which assumes a monopropellant model, was based on the concept of a combustion the delay occurring from the moment of propellant injection to the moment of propellant combustion. This combustion time … more
Date: September 27, 1951
Creator: Tischler, Adelbert O. & Bellman, Donald R.
Partner: UNT Libraries Government Documents Department
open access

Ignition-energy requirements in a single tubular combustor

Description: Report presenting an investigation conducted to determine the minimum spark energy required for ignition in a single tubular combustor. Inlet-air pressure and flow rates limiting ignition are compared with those limiting steady-state burning in the combustor. Results regarding ignition at sea-level conditions, altitude steady-state burning limits, altitude ignition, and reproducibility are provided.
Date: March 27, 1951
Creator: Foster, Hampton H.
Partner: UNT Libraries Government Documents Department
open access

Instrumentation for Recording Transient Performance of Gas-Turbine Engines and Control Systems

Description: Report presenting design features for the instrumentation used in a study of the transient performance of gas-turbine engines and control systems. The dynamic characteristics of the instrumentation are discussed and examples of typical acceleration data for a controlled and an uncontrolled engine are provided.
Date: June 27, 1951
Creator: Delio, Gene J. & Schwent, Glennon V.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method

Description: "An investigation of two semispan wings swept back 50 degrees 38 minutes was conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.68 to 1.15 by use of the transonic-bump technique. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one was an untwisted uncambered wing and the other was the same wing but incorporated twist and camber designed to give uniform load at a lift coefficient of 0.25 at … more
Date: August 27, 1951
Creator: Spreemann, Kenneth P. & Alford, William J., Jr.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Longitudinal Characteristics of the X-3 Configuration With Wing and Horizontal Tail Surfaces of Aspect Ratio 3.0 by Means of Rocket-Propelled Models: Results at High Lift Coefficients

Description: "A rocket-propelled model of the X-3 configuration equipped with an all-movable tail of aspect ratio 3.0 has been flown to determine the longitudinal characteristics of this configuration at high lift coefficients. An analysis of the response of the model to rapid deflections of the horizontal tail gave information on lift, drag, longitudinal stability, and longitudinal trim change. The primary result of the tests was that the configuration was indicated to have very unstable tendencies at lift… more
Date: August 27, 1951
Creator: Peck, Robert F. & Mitchell, Jesse L.
Partner: UNT Libraries Government Documents Department
open access

Load distribution over a fuselage in combination with a swept wing at small angles of attack and transonic speeds

Description: Report presenting free-fall tests of a wing-body configuration with a 45 degree sweptback cambered and twisted wing of aspect ratio 6 on a fuselage of fineness ratio 12.4. Results regarding the load and pitching moments and load-coefficient distribution are provided.
Date: November 27, 1951
Creator: White, Maurice D. & Look, Bonne C.
Partner: UNT Libraries Government Documents Department
open access

Low-speed wind-tunnel investigation of lateral control characteristics of a 60 degrees triangular-wing model having half-delta tip controls

Description: Report presenting a low-speed investigation in the stability tunnel to determine the lateral control characteristics of a 60 degree triangular wing model equipped with half-delta tip controls with areas of 5, 10, and 15 percent of the wing area. Results regarding lateral control effectiveness, rolling effectiveness, and a comparison of control and effectiveness with theory are provided.
Date: November 27, 1951
Creator: Jaquet, Byron M. & Queijo, M. J.
Partner: UNT Libraries Government Documents Department
open access

Resolution of Annealing Experiments for the Study of Nonequilibrium States

Description: The two techniques for conducting annealing experiments for the purpose of determining the distribution of atoms of a solid among non equilibrium states are considered. Related definitions for resolving power for annealing with steadily rising temperature and for annealing at a series of fixed temperatures are given. The necessary separation of activation energies for the resolution of two different non equilibrium states is found to be greater in the case of a steadily rising temperature, but … more
Date: September 27, 1951
Creator: Schwed, Philip
Partner: UNT Libraries Government Documents Department
open access

The Use of Two-Dimensional Section Data to Estimate the Low-Speed Wing Lift Coefficient at Which Section Stall First Appears on a Swept Wing

Description: Report discusses a procedure for estimating the wing lift coefficient for and spanwise location of the first occurrence of section stall on a swept wing. It has been modified from a method used to calculate the same information for unswept wings. The effects of split flaps, leading-edge modifications, and fences are described.
Date: July 27, 1951
Creator: Maki, Ralph L.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen