National Advisory Committee for Aeronautics (NACA) - 14 Matching Results

Search Results

Results: 1 - 14
open access

Altitude-chamber investigation of J73-GE-1A turbojet engine component performance

Description: Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.
Date: December 9, 1954
Creator: Campbell, Carl E. & Sobolewski, Adam E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine

Description: From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static… more
Date: December 9, 1954
Creator: Campbell, Carl E. & Conrad, E. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of scale and test technique on the validity of small-scale measurements of the aerodynamic characteristics of a wing with the leading edge swept back 63 degrees

Description: Report presenting the lift and pitching-moment characteristics of two wings of the same plan form measured over a range of Mach and Reynolds numbers using the wing-flow method. One wing had a symmetrical airfoil section and no twist, while the other was cambered and twisted to support a uniform load distribution at a lift coefficient of 0.25 at Mach number 1.5. A comparison with previous testing is also provided.
Date: December 9, 1949
Creator: Rolls, L. Stewart
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of twist and camber, fences, and horizontal-tail height on the low-speed longitudinal stability characteristics of a wing-fuselage combination with a 45 degree sweptback wing of aspect ratio 8 at a Reynolds number of 4.0 x 10(exp 6)

Description: Report presenting an investigation of the separate and combined effects of twist and camber, fences, and horizontal-tail height on the static longitudinal stability of a 45 degree sweptback wing-fuselage combination of aspect ratio 8 at Mach number 0.19. Two different wings were investigated, one untwisted and one with twist and cambered. Results regarding wing-fuselage configuration and wing-fuselage configurations with horizontal tail are provided.
Date: December 9, 1952
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of Gust and Draft Velocities from Flights of P-61c Airplanes within Thunderstorms August 7, 1946 to August 13, 1946 at Orlando, Florida

Description: This report presents the results obtained from gust and draft velocity measurements within thunderstorms for the period August 7, 1946 to August, 13, 1946 at Orlando Florida. In several of the surveys, indications of ambient air temperature were obtained from photo-observer records. These data are summarized in the report.
Date: December 9, 1946
Creator: Tolefson, Harold B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Altitude Performance of an Experimental Turbular Prevaporizing Combustor

Description: Memorandum presenting an investigation of an experimental tubular combustor that provides for prevaporizing and premixing of the fuel with a part of the air before its introduction into the combustion zone. Combustion efficiency and total-pressure loss data are presented for three configurations selected from a total of 43 different modifications investigated. Results regarding the combustor development, comparison of liquid and gaseous fuel, combustor total-pressure losses, combustor-outlet te… more
Date: December 9, 1954
Creator: Butze, Helmut F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of compressible flow mixing losses obtained downstream of a blade row

Description: Report presenting an investigation conducted to determine the importance of the mixing loss downstream of a blade row with respect to blade profile loss for compressible flow conditions. Theoretical and experimental results and the application of mixing loss results to the example transonic turbine are provided.
Date: December 9, 1954
Creator: Stewart, Warner L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method of designing corrugated surfaces having maximum cooling effectiveness within pressure-drop limitations for application to cooled turbine blades

Description: Report presenting a method using charts for the systematic determination of a corrugation geometry configuration which, for a specific application to an air-cooled turbine blade, gives the required amount of blade temperature reduction using the minimum amount of coolant flow within pressure-drop limitations. A numerical example is included to illustrate the use of the method.
Date: December 9, 1954
Creator: Slone, Henry O.; Hubbartt, James E. & Arne, Vernon L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack

Description: Report presenting a method to estimate the incompressible-flow surface pressures of compressor airfoils in cascade at design angle of attack by modifying the known pressure distribution as an isolated airfoil. The interference between airfoils was found to vary in a systematic manner. Testing performed on NACA 65-series compressor blade sections appears to agree with estimated values.
Date: December 9, 1953
Creator: Erwin, John R. & Yacobi, Laura A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack

Description: "A method was devised for estimating the incompressible-flow pressure distribution over compressor blade sections at design angle of attack. The theoretical incremental velocities due to camber and thickness of the section as an isolated airfoil are assumed proportional to the average passage velocity and are modified by empirically determined interference factors. Comparisons were made between estimated and test pressure distributions of NACA 65-series sections for typical conditions. Good agr… more
Date: December 9, 1953
Creator: Erwin, John R. & Yacobi, Laura A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices

Description: The results of a preliminary investigation to develop a nose shape suitable for housing an infrared seeker are presented. The zero-lift drag characteristics of a missile-like body with various unconventional nose shapes were obtained through a range of Mach numbers from 0.8 to 1.8 and Reynolds numbers, based on body length, from 20 x10 to the 6th power to 70 x 10 to the 6th power, respectively, by using rocket-propelled free-flight models. Results of the test indicate that at supersonic speeds … more
Date: December 9, 1952
Creator: Piland, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Total-Pressure-Recovery Characteristics of a Symmetric and Asymmetric Nose Inlet Over a Wide Range of Angle of Attack at Supersonic Mach Numbers

Description: Report presenting an investigation of the total-pressure-recovery characteristics over a wide range of angles of attack of an axially symmetric nose inlet at a Mach number of 1.42 and an asymmetric nose inlet at Mach numbers of 1.42 and 1.84.
Date: December 9, 1953
Creator: Carter, Howard S. & Merlet, Charles F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of the Landing on Water of a Model of a High-Speed Airplane - Langley Tank Model 229

Description: Memorandum presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a scale model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The test is part of an investigation of the feasibility of the operation from water of high-speed airplanes. The results of the test form a basis for evaluating the improvement in hydrodynamic characteristics.
Date: December 9, 1947
Creator: King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of the landing on water of a model of a high-speed airplane - Langley tank model 229

Description: Report presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a dynamic model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The model skipped out of the water and experienced maximum normal accelerations up to 7.4g and maximum longitudinal accelerations up to 4.5g. Results of landing the basic model and landing the modified model that has a slightly different fuselage are provided.
Date: December 9, 1947
Creator: King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen