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Theory and preliminary flight tests of an all-movable vertical tail surface
Report presenting flight testing of an improved type of all-movable tail surface. The particular arrangement tested provides control-free stability and a stable variation of the control forces during maneuvers. Results regarding rudder effectiveness, directional stability, rudder-free lateral motion, and rudder-free turns are provided.
Date:
January 1943
Creator:
Jones, Robert T. & Kleckner, Harold F.
System:
The UNT Digital Library
The High-Speed Characteristics of Several Flaps and Spoilers on the Upper Surface of the Horizontal Stabilizer of a Model of a Radial-Engine Pursuit Airplane
Report discussing an investigation into several types and sizes of flaps and spoilers located forward of the elevators on the upper surface of the horizontal stabilizer of a model of a radial-engine pursuit airplane. Information about the elevator characteristics, elevator-fixed and elevator-free balance lift coefficient, and trim drag coefficient for a range of Mach numbers is provided.
Date:
January 21, 1946
Creator:
Boddy, Lee E.
System:
The UNT Digital Library
Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination
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.
System:
The UNT Digital Library
Characteristics of Naca 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps
"At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord split flaps, deflected 60 degrees, in the center of the wing and having flat span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively" (p. 1).
Date:
January 1941
Creator:
Greenberg, Harry
System:
The UNT Digital Library
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil
From Introduction: "The results of the load tests and some additional aerodynamic characteristics of perforated double split flaps on a rectangular NACA 23012 airfoil are given in the present report."
Date:
January 1943
Creator:
Turner, Thomas R.
System:
The UNT Digital Library
Experimental verification of a simplified vee-tail theory and analysis of available data on complete models with vee tails
Report presenting an analysis of available data on vee-tail surfaces. The analysis indicated that a vee tail designed to provide values of stability and control parameters equal to those provided by a conventional tail would probably provide no reduction in area unless the conventional vertical tail is in a bad canopy wake or unless the vee tail has a higher effective aspect ratio than the conventional vertical and horizontal tails.
Date:
January 1945
Creator:
Purser, Paul E. & Campbell, John P.
System:
The UNT Digital Library
Distribution of losses behind a compressor rotor as measured by a rotating rake
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 low-speed momentum loss coefficient withe angle of attack, and variation of momentum-loss coefficient with Mach number are provided.
Date:
January 17, 1956
Creator:
Godwin, William R.
System:
The UNT Digital Library
Effect of inlet-air-flow-distortions on steady-state performance of J65-B-3 turbojet engine
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 exhaust-nozzle operation, the primary effect of the radial inlet-air-flow distortions was to reduce the engine air flow, and the primary effect of the circumferential distortion was to impose a temperature profile on the turbine, both resulting in reduction of thrust.
Date:
January 25, 1956
Creator:
Smith, Ivan D.; Braithwaite, W. M. & Calvert, Howard F.
System:
The UNT Digital Library
Wind-tunnel tests of hinge-moment characteristics of spring-tab ailerons
Report presenting testing in the stability tunnel of two types of spring tab used as balances on a partial-span plain aileron. The tabs were connected to a spring located in the control system so that tab deflection was dependent on the control force.
Date:
January 1944
Creator:
Imlay, Frederick H. & Bird, J. D.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
Wind-Tunnel Investigation of a Plain Aileron with Various Trailing-Edge Modifications on a Tapered Wing 3: Ailerons with Simple and Spring-Linked Balancing Tabs
Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controlllability at low speeds.
Date:
January 1943
Creator:
Purser, Paul E. & Rogallo, F. M.
System:
The UNT Digital Library
Collection of Balanced-Aileron Test Data
"Test data of balanced ailerons have been collected from NACA and British sources. These data, which are presented in the form of charts, are grouped as A - ailerons with Frise balances, B - ailerons with blunt-nose balances, C - ailerons with internal balances, D - ailerons with contour modifications, and E - ailerons with tabs. Results of flight tests and of wind-tunnel tests in both two- and three-dimensional flow are presented but no correlation nor resume of the data has been included" (p. 1).
Date:
January 1944
Creator:
Rogallo, F. M.
System:
The UNT Digital Library
Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing
Report presenting an investigation in the 7- by 10-foot tunnel of various modifications of the trailing-edge portion of a 0.20-chord plain aileron on a partial-span model of a tapered low-drag wing. The modifications tested included various amounts of symmetrical and unsymmetrical thickening and beveling of the aileron trailing edge. Results regarding coefficients and corrections, characteristics with ailerons neutral, characteristics with ailerons deflected, aileron trim characteristics, and estimated aileron-control characteristics are provided.
Date:
January 1943
Creator:
Purser, Paul E. & McKee, John W.
System:
The UNT Digital Library
An experimental study of a method for designing fuselage side air inlets for high performance at transonic and low supersonic speeds
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.
System:
The UNT Digital Library
Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds
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.
System:
The UNT Digital Library
Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines
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.
System:
The UNT Digital Library
Analysis of a flight investigation at supersonic speeds of a simple homing system
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.
System:
The UNT Digital Library
Experimental investigation of effect of cooling air on turbine performance of two turbojet engines modified for air-cooling
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.
System:
The UNT Digital Library
Wind-tunnel investigation of the damping in roll of the Bell X-1A research airplane and its components at supersonic speeds
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.
System:
The UNT Digital Library
An investigation of aircraft heaters 15: the emissivity of several materials
Report presenting a determination of the mean effective emissivity as a function of temperature for the surfaces of several metals and insulating materials. A description and discussion of the measuring technique is presented. The results are plotted on a variety of graphs.
Date:
January 1944
Creator:
Boelter, L. M. K.; Bromberg, R. & Gier, J. T.
System:
The UNT Digital Library
A description of the Ames 2- by 2-foot transonic wind tunnel and preliminary evaluation of wall interference
Report presenting a description of the Ames 2- by 2-foot transonic wind tunnel, its uses in testing, and a preliminary evaluation of the wall interference in the tunnel.
Date:
January 20, 1956
Creator:
Spiegel, Joseph M. & Lawrence, Leslie F.
System:
The UNT Digital Library
Effects of a J34 Turbojet Engine on Supersonic Diffuser Performance
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.
System:
The UNT Digital Library
The effect of high loading on landing technique and distance, with experimental data for the B-26 airplane
Report presenting an analysis of the effect of wing loading of the landing flare, which indicated that it had an important effect on landing technique and distance. Results regarding the approach and flare path and ground run are provided.
Date:
January 1945
Creator:
O'Sullivan, William J., Jr.
System:
The UNT Digital Library
Effect of an Adjustable Supersonic Inlet on the Performance Up to Mach Number 2.0 of a J34 Turbojet Engine
"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
System:
The UNT Digital Library