Technical Report Archive & Image Library (TRAIL) - 15 Matching Results

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Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 1: maximum thickness at 20 percent of the chord

Description: From Summary: "This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form."
Date: November 19, 1948
Creator: Berggren, Robert E. & Summers, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cyclic Engine Test of Cast Vitallium Turbine Buckets - 1

Description: Report presenting an investigation to correlate the engine service performance of cast Vitallium turbine buckets with standard laboratory metallurgical data. Data was obtained on four turbine wheels of Timken alloy with cast Vitallium buckets. Results regarding the engine test and metallurgical examination are provided.
Date: February 19, 1948
Creator: Farmer, J. Elmo; Darmara, F. N. & Poulson, Francis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ditching Tests of a 1/8-Scale Model of the Chance Vought XF6U-1 Airplane, TED No. NACA DE319

Description: Tests were made with a 1/8-scale dynamically similar model of the Chance Vought XF6U-1 airplane to study its behavior when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, by recording time histories of the accelerations, and by taking motion pictures of the ditchings. From the results of the tests it was concluded that th… more
Date: January 19, 1948
Creator: Fisher, Lloyd J., Jr. & McBride, Ellis E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Downwash and Dynamic Pressure at the Horizontal Tail of a Six-Engine Pusher-Propelled Airplane

Description: Report discussing an investigation of the vertical plane of the elevator hinge line of a powered model of a bomber to determine the values of downwash and the dynamic-pressure ratio. The equations for calculating these values and the testing procedures are described.
Date: July 19, 1948
Creator: Furlong, G. Chester
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements in Flight on the 10-Percent-Thick and 8-Percent-Thick Wing X-1 Airplanes

Description: Report presenting drag measurements made on a 10-percent-thick wing and 8-percent-thick tail and a 8-percent-thick wing, 6-percent-thick tail version of the X-1 airplane at a variety of Mach numbers. The drag of the thicker wing was found to be much higher than that of the thinner wing. The fuselage was found to cause interference with the wing of both models, making the separation of wing and fuselage drag difficult to determine.
Date: November 19, 1948
Creator: Gardner, John J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake

Description: "An investigation of an NACA submerged air intake was conducted on a full-scale model of a fighter-type airplane. This study was made to determine the large-scale aerodynamic characteristics of a submerged air intake proposed as the result of small-scale tests and to compare the pressure-recovery characteristics of the large- and small-scale installations. Additional tests were made to determine the effect on pressure recovery of a systematic variation of ramp divergence" (p. 1).
Date: October 19, 1948
Creator: Martin, Norman J. & Holzhauser, Curt A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

General handling-qualities results obtained during acceptance flight tests of the Bell XS-1 airplane

Description: Report presenting measurements of the handling qualities of the Bell XS-1 transonic airplane using NACA instruments. Information regarding the stability and control characteristics and aerodynamic loads was obtained using two different airplanes in gliding and powered flight. Results regarding the longitudinal and lateral stability and control and stalling characteristics are provided.
Date: April 19, 1948
Creator: Williams, Walter C.; Forsyth, Charles M. & Brown, Beverly P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 3: The Effectiveness of a Constant-Chord Aileron

Description: Report presenting a wind-tunnel investigation at a range of Mach numbers with a constant Reynolds number of a semispan model of a thin, unswept wing of aspect ratio 4 and taper ratio 0.5 with a constant-chord aileron and a modified diamond profile. Results regarding lift and rolling-moment characteristics and aileron effectiveness are provided.
Date: November 19, 1948
Creator: Johnson, Ben H., Jr. & Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Low-Speed Static Stability Characteristics of Complete Models Having Sweptback and Sweptforward Wings

Description: "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the static stability characteristics at low speeds of complete models with various swept wings so that comparisons might be made with available theoretical and empirical methods of predicting the stability characteristics. Longitudinal and lateral stability characteristics, flaps up and down, were obtained for models having 0 degree, 15 degrees, 30 degrees, and 45 degrees sweptforward and sweptback win… more
Date: November 19, 1948
Creator: Spearman, M. Leroy & Comisarow, Paul
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of two pitot-static tubes at supersonic speeds

Description: The results of tests at a Mach number of 1.94 of an ogives-nose cylindrical pitot-static tube and similar tests at Mach numbers of 1.93 and 1.62 of a service pitot-static tube to determine body static pressures and indicated Mach numbers are presented and discussed. The radial pressure distribution on the cylindrical bodies is compared with that calculated by an approximate theory.
Date: November 19, 1948
Creator: Hasel, Lowell E. & Coletti, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal Stability and Control Characteristics of a Semispan Airplane Model at Transonic Speeds as Obtained by the Transonic-Bump Method

Description: Memorandum presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the longitudinal stability and control characteristics of a semispan airplane model at transonic speeds. The results indicated an increase in the maneuvering stability through the transonic range, but regions of instability were indicated by the slope of the curve stabilizer incidence for trim against Mach number at all positions tested.
Date: July 19, 1948
Creator: Weil, Joseph & Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of several air ejectors with conical mixing sections and small secondary flow rates

Description: An investigation of several ejector configurations to determine the ability to handle the air required for engine cooling. The results are limited to investigations of conical-type mixing-section ejectors at ratios of mixing-section minimum diameter to primary-jet-nozzle diameter using unheated air. Results regarding experimental data, generalization of experimental data, spacing for maximum weight-flow ratio, ejector thrust, ejector configurations for constant weight-flow ratio, and selection … more
Date: July 19, 1948
Creator: Huddleston, S. C.; Wilsted, H. D. & Ellis, C. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92

Description: Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87.
Date: April 19, 1948
Creator: Drake, Hubert M.; McLaughlin, Milton D. & Goodman, Harold R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Simulated Altitude Performance of Combustors for the Westinghouse 24C Jet Engine I-24C-2 Combustor

Description: "A Westinghouse 24C-2 combustor was investigated at conditions simulating operation of the 24C Jet engine at zero ram over ranges of altitude and engine speed. The investigation was conducted to determine the altitude operational limits, that is, the maximum altitude for various engine speeds at which an average combustor-outlet gas temperature sufficient for operation of the jet engine could be obtained. Information was also obtained regarding the character of the flames, the combustion effici… more
Date: November 19, 1948
Creator: Manganiello, Eugene J.; Bernardo, Everett & Schroeter, Thomas T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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