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Skin-Temperature Telemeter for Determining Boundary-Layer Heat-Transfer Coefficients

Description: Memorandum presenting a description of a method of telemetering skin temperature using a small resistance wire pickup with a time constant of less than 0.003 second to determine boundary-layer heat-transfer coefficients. An evaluation of the accuracy of the method of measuring the heat-transfer coefficient is given for a particular application.
Date: March 15, 1951
Creator: Fricke, Clifford L. & Smith, Francis B.
Partner: UNT Libraries Government Documents Department

Relation of Turbojet Propulsion System Development to the Strategic Bomber Mission

Description: Memorandum presenting a generalized analysis of the effects of turbojet propulsion system development and fuel selection on ability of a strategic bomber to perform desired and minimum missions. The variation of bomber performance using a hydrocarbon, boron, or nuclear fuel is discussed.
Date: August 15, 1956
Creator: Rothrock, Addison M.; Cesaro, Richard S. & Walker, Curtis L.
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine

Description: Report presenting the initial development of a technique for the qualitative study of the stability and control characteristics of a free, self-propelled, dynamic submarine model. Two types of control systems were evaluated. Results regarding the qualitative analysis of the control system, dive paths, equations of motion, and comparison with experimental paths are provided.
Date: April 15, 1954
Creator: McKann, Robert E. & Petynia, William W.
Partner: UNT Libraries Government Documents Department

Preliminary Transonic Flutter Investigation of Models of T-Tail of Blackburn NA-39 Airplane

Description: Memorandum presenting a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation is to be considered preliminary in that only estimated airplane properties were available for the scaling. Results regarding interpretation of results, presentation of data, and a discussions are provided.
Date: April 15, 1958
Creator: Jones, George W., Jr. & Boswinkle, Robert W., Jr.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of Laminar-Boundary-Layer Control on an Airfoil Section Equipped With Suction Slots Located at Discontinuities in the Surface Pressure Distribution

Description: Memorandum presenting an experimental investigation of a two-dimensional, 6.6-percent-thick, 6-foot-chord airfoil section equipped with suction slots for laminar-boundary-layer control. The section was designed to have favorable pressure gradients between the suction slots. The laminar boundary layer on the airfoil had the same extreme sensitivity to minute details of the model surface condition as has been found in other investigations.
Date: December 15, 1953
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Partner: UNT Libraries Government Documents Department

Summary of the Availability and Performance Problems of High Octane Number Fuels

Description: Memorandum presenting a study to determine the possible blending agents or additives that may be used to supplement current high performance number, rich rating components in future aviation fuels. The study indicated that such high rich rating blending agents as toluene and xylene cannot be made available in sufficient quantities to maintain the rich rating performance of the fuels when reducing the lead content from 4.6 to 3.0 ml per gallon.
Date: April 15, 1949
Creator: NACA Committee on Aircraft Fuels
Partner: UNT Libraries Government Documents Department

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured in Flight on the Wing of the Douglas D-558-I Airplane for a 1 g Stall, a Speed Run to a Mach Number of 0.90, and a Wind-Up Turn at a Mach Number of 0.86

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented unanalyzed for six spanwise stations on the right wing of the Douglas D-558-I research airplane (BuAero No. 37972). The data were obtained in a 1 g stall at subcritical Mach numbers, in a speed run to a Mach number of 0.90 and in a wind-up turn at a Mach number of 0.86" (p. 1).
Date: December 15, 1950
Creator: Keener, Earl R. & Pierce, Mary
Partner: UNT Libraries Government Documents Department

The Low-Speed Lift and Drag Characteristics of a Series of Airplane Models Having Triangular or Modified Triangular Wings

Description: Memorandum summarizing the lift and drag characteristics of a series of five low-aspect-ratio triangular-wing or modified triangular-wing airplane models. The series consists of three triangular wings of aspect ratios 2, 3, and 4 and two modified triangular wings of aspect ratio 2 with taper ratios of 0.20 and 0.33. The experimental lift and drag characteristics of the five models are compared with existing theory.
Date: June 15, 1953
Creator: Graham, David
Partner: UNT Libraries Government Documents Department

Experimental Investigation of Water Injection in Subsonic Diffuser of a Conical Inlet Operation at Free-Stream Mach Number of 2.5

Description: A spike-type nose inlet with sharp-lip cowl was investigated at a free-stream Mach number of 2.5 with water injection in its 16-inch diameter, 11-foot-long subsonic diffuser section. Inlet total temperature of exit with liquid-air ratios of about 0.04 with no apparent change in the critical pressure recovery. The observed temperature drops were less than the theoretically predicted values, and the amount of water evaporated was 35 to 50 percent less than that theoretically possible.
Date: January 15, 1957
Creator: Beke, Andrew
Partner: UNT Libraries Government Documents Department

An Investigation at Subsonic Speeds of the Rolling Effectiveness of a Small Perforated Spoiler on a Wing Having 45 Degrees of Sweepback

Description: Memorandum presenting an investigation of the rolling effectiveness of a partial-span, perforated spoiler on a wing with 45 degrees of sweepback at Mach numbers from 0.25 to 0.96. The effects of the spoiler on the lift, drag, and pitching moment were also determined. Results regarding Reynolds number, Mach number, and predicted rate of roll are provided.
Date: September 15, 1952
Creator: Bandettini, Angelo
Partner: UNT Libraries Government Documents Department

Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel

Description: Memorandum presenting tests of a scale model of a B-36J/RF-84F tip-coupled airplane in the 19-foot pressure tunnel in order to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain an indication of the dynamic stability characteristics of the configuration. The variables studied in the investigation included skew angle of the fighter-bomber coupling, fighter longitudinal position, fighter and bomber loading, angle of sideslip, degrees of body freedom, and the number of fighters.
Date: March 15, 1956
Creator: Neely, Robert H.
Partner: UNT Libraries Government Documents Department

Investigation of Perforated Convergent-Divergent Diffusers With Initial Boundary Layer

Description: An experimental investigation was made at Mach number 1.90 of the performance of a series of perforated convergent-divergent supersonic diffusers operating with initial boundary layer, which was induced and controlled by lengths of cylindrical inlets affixed to the diffusers. Supercritical mass-flow and peak total-pressure recoveries were decreased slightly by use of the longest inlets (4 inlet diameters in length). Combinations of cylindrical inlets, perforated diffusers, and subsonic diffuser were evaluated as simulated wind tunnels having second throats. Comparisons with noncontracted configurations of similar scale indicated conservatively computed power reductions of 25 percent.
Date: August 15, 1950
Creator: Weinstein, Maynard I.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine

Description: From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date: December 15, 1950
Creator: Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

A Summary Report on the Effects of Mach Number on the Span Load Distribution on Wings of Several Models

Description: Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.
Date: July 15, 1947
Creator: Jessen, Henry, Jr.
Partner: UNT Libraries Government Documents Department

Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches

Description: Memorandum presenting a calculation of the amount of possible correction for coordinated turns with limited bank angle and level sideslips for a large transport airplane, the C-54D. The results indicate that for all instances from the end of the runway, coordinated turns are the more effective maneuver.
Date: December 15, 1949
Creator: Faber, Stanley
Partner: UNT Libraries Government Documents Department

An Experimental Investigation of Four Triangular-Wing-Body Combinations in Sideslip at Mach Numbers 0.6, 0.9, 1.4, and 1.7

Description: "The lateral-directional-stability derivatives of a body in combination with several triangular wings were determined at subsonic and supersonic speeds. The wings used in the investigation were of aspect ratios 2 and 4 and thickness ratios of 3 and 5 percent. One of the wings of aspect ratio 2 was cambered and twisted. The results indicate that at supersonic speeds the effects of plan form on the lateral-directional-stability derivatives for the plane wings were predicted satisfactorily by linearized theory and that the effects of thickness were small" (p. 1).
Date: March 15, 1954
Creator: Christensen, Frederik B.
Partner: UNT Libraries Government Documents Department

Experimental Determination of Boundary-Layer Transition on a Body of Revolution at M = 3.5

Description: Memorandum presenting transition tests made in free-flight on a slender body of revolution at Mach number 3.5, wall to free-stream temperature ratio of unity, and with a noiseless and zero-turbulence air stream. The parameter which was varied was surface roughness. Results regarding tests at a Reynolds number of 12 million and 24 million, bursts of turbulence, surface roughness, effect of angle of attack, and time dependence of the transition point are provided.
Date: March 15, 1954
Creator: Jedlicka, James R.; Wilkins, Max E. & Seiff, Alvin
Partner: UNT Libraries Government Documents Department

An assessment of the airplane drag problem at transonic and supersonic speeds

Description: Report presenting the airplane drag problem at transonic and supersonic speeds. The area rule is shown to be a powerful tool that provides guidance for designers in selecting aerodynamic features compatible with low wave drag. Analytical methods have been developed that permit quantitative evaluation of the wave-drag level likely to be experienced with a given design.
Date: July 15, 1954
Creator: Donlan, Charles J.
Partner: UNT Libraries Government Documents Department

An investigation of some factors affecting the drag of relatively large nonlifting bodies of revolution in a slotted transonic wind tunnel

Description: Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.
Date: January 15, 1953
Creator: Pendley, Robert E. & Bryan, Carroll R.
Partner: UNT Libraries Government Documents Department

Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions

Description: Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain operating conditions the flame extended beyond the turbine position.
Date: August 15, 1947
Creator: Dittrich, Ralph T.
Partner: UNT Libraries Government Documents Department

A theory for stability and buzz pulsation amplitude in ram jets and an experimental investigation including scale effects

Description: From Summary: "From a theory developed on a quasi-one-dimensional-flow basis, it was found that the stability of the ram jet is dependent upon the instantaneous values of mass flow and total pressure recovery of the supersonic diffuser and immediate neighboring subsonic diffuser. Conditions for stable and unstable flow were presented. The theory developed in the report was in agreement with the experimental data of the reports both of Sterbentz and Evvard and of Ferri and Nucci."
Date: October 15, 1953
Creator: Trimpi, Robert L.
Partner: UNT Libraries Government Documents Department

Effect of screens in reducing distortion and diffusion length for a 'dump' diffuser at a Mach number of 3.85

Description: Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.
Date: July 15, 1958
Creator: Wasserbauer, Joseph F.
Partner: UNT Libraries Government Documents Department

Theory of wing-body drag at supersonic speeds

Description: "At subsonic speeds the pressure drag arising from the thickness of the body or wings is negligible so long as the shapes are sufficiently well streamlined to avoid flow separation. In that range there exists no possibility of either favorable or adverse interference on the pressure distributions themselves. If one body is so placed as to receive a drag from the pressure field of another then the second body is sure to receive a corresponding increment of thrust from the first" (p. 1).
Date: September 15, 1953
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department

Lateral-control investigation at transonic speeds of differentially deflected horizontal-tail surfaces for a configuration having a 6-percent-thick 45 degree sweptback wing

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the lateral-control effectiveness of differentially deflected horizontal-tail surfaces mounted behind a 45 degree sweptback wing-fuselage combination. The effectiveness of the differentially deflected horizontal tail as a lateral-control device was found to be essentially independent of angle of attack and Mach number even in the transonic region. Results regarding the effects of differential deflection of horizontal-tail surfaces and effects of the vertical tail are provided.
Date: November 15, 1955
Creator: Critzos, Chris C.
Partner: UNT Libraries Government Documents Department