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A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowa… more
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department
open access

Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination

Description: Report presenting the effects of an angle of incidence of 4 degrees and body indentation on wing loads of a sweptback wing-body combination at a range of Mach numbers. The wing had an aspect ratio of 4, taper ratio of 0.3, 45 degrees of sweepback of the quarter-chord line, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of incidence and effect of body indentation are provided.
Date: January 11, 1956
Creator: Platt, Robert J., Jr.
Partner: UNT Libraries Government Documents Department
open access

Distribution of losses behind a compressor rotor as measured by a rotating rake

Description: Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of … more
Date: January 17, 1956
Creator: Godwin, William R.
Partner: UNT Libraries Government Documents Department
open access

Effect of inlet-air-flow-distortions on steady-state performance of J65-B-3 turbojet engine

Description: The effects of inlet-air-flow distortions on the performance of the J65-B-3 turbojet engine were determined over a range of altitudes from 15,000 to 50,000 feet at a flight Mach number of 0.8. Radial inlet-air-flow distortions apparently do not affect the radial distribution of pressure after the first few compressor stages, while the circumferential inlet-air-flow distortion carried completely through the engine. For the distortions investigated, at rated exhaust-gas temperature and fixed-area… more
Date: January 25, 1956
Creator: Smith, Ivan D.; Braithwaite, W. M. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
open access

Some Effects of Sweep and Aspect Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Taper Ratio of 0.6

Description: Report presenting an investigation of the flutter characteristics of a series of thin cantilever wings with taper ratios of 0.6 for a range of Mach numbers. Results regarding flutter frequencies, time histories, effects of sweep on the flutter-speed ratio, effects of aspect ratio on the flutter-speed ratio, effects of additional models on the reference flutter speed, application of the flutter-speed ratio, and modified experimental flutter-speed coefficient are provided.
Date: January 24, 1956
Creator: Unangst, John R. & Jones, George W., Jr.
Partner: UNT Libraries Government Documents Department
open access

An experimental study of a method for designing fuselage side air inlets for high performance at transonic and low supersonic speeds

Description: Report presenting a brief experimental investigation of a method for designing fuselage side air inlets with high internal total-pressure recovery and zero spillage drag at a specified design inlet mass-flow ratio. With a scoop designed according to the concept, near-zero spillage drag can be attained at the design inlet mass-flow ratio through a range of Mach numbers. Results regarding pressure recovery and drag due to the scoop are provided.
Date: January 17, 1955
Creator: Howell, Robert R. & Trescot, Charles D., Jr.
Partner: UNT Libraries Government Documents Department
open access

Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds

Description: Report presenting the longitudinal and lateral stability characteristics of a 40 degree swept-wing fighter model with and without horizontal tails of 0 degrees and 22.5 degrees negative dihedral for a range of Mach numbers, angles of attack, and sideslip.
Date: January 17, 1956
Creator: Arabian, Donald D.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines

Description: For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date: January 17, 1956
Creator: Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
open access

Analysis of a flight investigation at supersonic speeds of a simple homing system

Description: From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."
Date: January 10, 1956
Creator: Gardiner, Robert A.; Gillis, Clarence L. & Graves, G. B., Jr.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of effect of cooling air on turbine performance of two turbojet engines modified for air-cooling

Description: Report presenting an investigation at sea-level static conditions to determine the effects of radial discharge of cooling air from turbine rotor blades on turbine performance in two turbojet engines, one with a centrifugal compressor and the other with an axial-flow compressor. Results regarding the performance characteristics, efficiency comparisons, and some interpretation are provided.
Date: January 25, 1956
Creator: Smith, Gordon T.; Freche, John C. & Cochran, Reeves P.
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the damping in roll of the Bell X-1A research airplane and its components at supersonic speeds

Description: Report presenting the experimental values of damping in roll of the Bell X-1A airplane and its components at 5 Mach numbers at zero angle of attack. The wing was found to be the predominant contributor to the damping in roll throughout the range of Mach numbers, but the contributions of other airplane components were significant in the range of 2.22 to 2.41.
Date: January 10, 1956
Creator: McDearmon, Russell W. & Clark, Frank L.
Partner: UNT Libraries Government Documents Department
open access

Effects of a J34 Turbojet Engine on Supersonic Diffuser Performance

Description: Report presenting testing of a translating cone inlet with a variable bypass at Mach numbers 1.6, 1.8, and 2.0 with both a choked exit plug and a J34 turbojet engine. The main difference between the two options was increased inlet subcritical stability with the engine. Results regarding basic diffuser performance, inlet stability, buzz amplitude and frequency, and diffuser-exit profiles are provided.
Date: January 4, 1956
Creator: Beheim, Milton A. & Englert, Gerald W.
Partner: UNT Libraries Government Documents Department
open access

Effect of an Adjustable Supersonic Inlet on the Performance Up to Mach Number 2.0 of a J34 Turbojet Engine

Description: "A J34 turbojet engine was investigated at free-stream Mach numbers of 0.12 and 1.6 to 2.0 to determine the effect of supersonic inlet operation on engine performance. With the exception of ideal jet thrust, the use of generalized engine parameters correlated the engine data satisfactorily when the exit nozzle was choked. Large total-pressure distortions did not affect compressor efficiency" (p. 1).
Date: January 4, 1956
Creator: Beke, Andrew; Englert, Gerald & Beheim, Milton
Partner: UNT Libraries Government Documents Department
open access

Effects of compressor interstage bleed and adjustable inlet guide vanes on compressor stall characteristics of a high-pressure-ratio turbojet engine at altitude

Description: Report presenting the stall characteristics of the J71-A2(X-29) turbojet engine as determined in an altitude test chamber. When the normal high-speed configuration of bleeds closed, inlet guide vanes open was operated in the low-speed range, the stall-limit line intersected the operating line at 4067 and 4630 rpm. Results regarding compressor performance at steady state and stall and fuel flow at steady state and stall are provided.
Date: January 17, 1956
Creator: Mallett, William E. & Groesbeck, Donald E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of local heat-transfer and pressure drag characteristics of a yawed circular cylinder at supersonic speeds

Description: Local heat-transfer coefficients, temperature recovery factors, and pressure distributions were measured on the front side of a circular cylinder at a nominal Mach number of 3.9 over a range of free-stream Reynolds numbers from 2.1 x 10 to the 3rd power to 6.7 x 10 to the 3rd power and yaw angles from zero degrees to 44 degrees. Yawing the cylinder reduced the heat-transfer coefficients and the pressure drag coefficients. The amount of reduction may be predicted by a theory presented herein.
Date: January 24, 1956
Creator: Goodwin, Glen; Creager, Marcus O. & Winkler, Ernest L.
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation at Mach number 1.9 of simulated wing-root inlets

Description: Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.
Date: January 19, 1955
Creator: Piercy, Thomas G. & Weinstein, Maynard I.
Partner: UNT Libraries Government Documents Department
open access

An investigation of string support interference on base pressure and forebody chord force at Mach numbers from 0.60 to 1.30

Description: Report presenting testing to determine the interference effects of various sting-support configurations on the base pressure and foredrag characteristics of a wing-fuselage combination with a turbulent boundary layer. The primary variable investigated was the length of the constant-diameter portion of a sting support. Results regarding the base-pressure interference and foredrag interference are provided.
Date: January 28, 1955
Creator: Tunnell, Phillips J.
Partner: UNT Libraries Government Documents Department
open access

A flight investigation at transonic speeds and small angles of attack of the aerodynamic characteristics of a model having a 45 degree sweptback wing of aspect ratio 3 with an Naca 64A006 airfoil section

Description: Report presenting an investigation of the longitudinal aerodynamic characteristics of a model with a 45 degree sweptback wing of aspect ratio 3 and a 45 degree sweptback cruciform tail at transonic speeds and small angles of attack by a free-fall recoverable-model technique. Results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, and loading distribution over the fuselage are provided.
Date: January 25, 1954
Creator: Holdaway, George H.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 2: Stage and Blade-Element Performance

Description: Memorandum presenting an investigation to determine the feasibility of increasing the specific weight flow of a transonic axial-flow compressor inlet stage by decreasing the hub-tip ratio. The current phase of the investigation was conducted to determine the blade-element and the overall performance of the complete stage. Results regarding the overall performance, blade-element performance, and stator-blade-element performance are provided.
Date: January 10, 1955
Creator: Montgomery, John C. & Glaser, Frederick W.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Two Short Annular Diffuser Configurations Utilizing Section and Injection as a Means of Boundary-Layer Control

Description: Memorandum presenting an investigation of the performances of two annular diffuser designs applicable to turbojet afterburner installations to determine the effectiveness of injection and suction boundary-layer controls. Results regarding inlet measurements, flow observations, static-pressure distributions, downstream velocity distributions, and mean performance coefficients are provided.
Date: January 25, 1955
Creator: Wilbur, Langley W. & Higginbotham, James T.
Partner: UNT Libraries Government Documents Department
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The effect of blunt-trailing-edge elevons on the longitudinal and lateral handling qualities of the semitailless airplane

Description: Report presenting a flight program using the Northrop X-4 semitailless airplane to investigate the effect on the longitudinal and lateral stability and control of thickened elevons with trailing-edge thickness one-half the control-hinge-station thickness. The investigation consisted of speed runs, wind-up turns, abrupt rudder-fixed rolls, and longitudinal pulses between a range of Mach numbers.
Date: January 13, 1955
Creator: Saltzman, Edwin J.
Partner: UNT Libraries Government Documents Department
open access

Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design

Description: Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.
Date: January 19, 1955
Creator: Schum, Eugene F.
Partner: UNT Libraries Government Documents Department
open access

Performance of YJ73-GE-3 turbojet engine in altitude test chamber

Description: Report presenting the steady-state performance of the YJ73-GE-3 turbojet engine in an altitude test chamber for a range of exhaust-nozzle areas, simulated altitudes, and Mach numbers. A method of performance calculation based on engine pumping characteristics is provided. Results regarding performance maps, pumping characteristics and performance prediction, thrust correlation, effect of inlet temperature on performance, calculated performance from pumping characteristics, and altitude-ignition… more
Date: January 19, 1955
Creator: Kaufman, Harold R. & Dobson, Wilbur F.
Partner: UNT Libraries Government Documents Department
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