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Data From Flow-Field Surveys Behind a Large-Scale Thin Straight Wing of Aspect Ratio 3

Description: Memorandum presenting limited flow-field surveys made behind a large-scale thin straight wing of aspect ratio 3, both alone and in combination with a body and vertical tail. The surveys indicated a region of high downwash angles, low dynamic pressures, and rough flow, that extended higher above the wing chord plane, and farther aft, with increasing angle of attack beyond the tail.
Date: June 23, 1958
Creator: Evans, William T.
Partner: UNT Libraries Government Documents Department
open access

Effect of aerodynamic heating on the flutter of a rectangular wing at a Mach number of 2

Description: Report presenting the flutter of a solid wing as affected by aerodynamic heating, which can cause a large momentary loss in torsional stiffness. Both experimental and analytical studies were conducted and good correlation was demonstrated. The loss of stiffness due to aerodynamic heating was calculated and the operational line intersected with the flutter curve.
Date: June 23, 1958
Creator: Runyan, Harry L. & Jones, Nan H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51

Description: Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date: June 23, 1958
Creator: Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Some Factors Affecting the Stability and Performance Characteristics of Canard Aircraft Configurations

Description: "A survey has been made of some of the factors to be considered in the design of canard aircraft configurations. The factors include Mach number and angle-of-attack effects as well as the effects of various geometric changes. Among the geometric variables included are the effects of wing plan form, wing height, wing twist, canard plan form, canard area, canard moment arm, forebody length, afterbody length, forebody deflection, vertical-tail plan form, vertical-tail size, vertical-tail location,… more
Date: June 23, 1958
Creator: Spearman, M. Leroy & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
open access

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: An Aluminum-Alloy Model of 40-Inch Chord With 0.125-Inch-Thick Skin

Description: Report presenting testing of a 5-percent-thick 2024-T3 aluminum-alloy multiweb wing (MW-1-(2)) at a Mach number of 2 under simulated supersonic flight conditions. The wing experienced dynamic failure as a result of catastrophic flag-waving flutter due to the combined action of aerodynamic heating and loading. Results regarding model temperatures, experimental pressures, strain results, accelerometer, and model failure are provided.
Date: June 23, 1958
Creator: Griffith, George E. & Miltonberger, Georgene H.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 2.02

Description: "An investigation at a free-stream Mach number of 2.02 was made to determine the effects of a propulsive jet on a wing surface located in the vicinity of a choked convergent nozzle. Static-pressure surveys were made on a flat surface that was located in the vicinity of the propulsive jet. The nozzle was operated over a range of exit pressure ratios at different fixed vertical distances from the flat surface. Within the scope of this investigation, it was found that shock waves, formed in the ex… more
Date: June 23, 1954
Creator: Bressette, Walter E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Normal Force Accompanying Thrust-Axis Inclination of the NACA 1.167-(0)(03)-058 and the NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.90

Description: Report presenting an investigation to determine the normal force of two three-blade NACA propellers and the agreement of the measured normal force with a theoretical method. Propeller thrust and normal force were measured for a variety of blade angles, angles of attack, and Mach numbers. Results regarding variation with thrust, effect of inclination, and a comparison with theory are provided.
Date: June 23, 1954
Creator: Demele, Fred A. & Otey, William R.
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of the Pressure Recovery of Several Two-Dimensional Supersonic Inlets at Mach Number of 2.01

Description: Report presenting an investigation of several two-dimensional supersonic inlet configurations at a Mach number of 2.01 and an angle of attack of 0 degrees. Two inlets similar in supersonic diffuser design but one with a subsonic diffusers about half the length of the other one were also investigated. Results regarding the inlet design, pressure recovery, shadowgraphs, and suggestions for inlet improvement are provided.
Date: June 23, 1954
Creator: Comenzo, Raymond J.
Partner: UNT Libraries Government Documents Department
open access

Static Longitudinal and Lateral Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane at a Mach Number of 1.41

Description: "An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a 1/15-scale model of the Grunman F9F-9 airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on the aerodynamic characteristics were also investigated. These tests were made at a Reynolds number of 1.96 x l0 (exp 6) based on the wing mean aerodynamic chord o… more
Date: June 23, 1954
Creator: Palazzo, Edward B. & Spearman, M. Leroy
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of physical and combustion properties of several residual fuel oils and magnesium - fuel-oil slurries in a ram-jet-type combustor

Description: Report presenting an experimental investigation using a 1 7/8-inch diameter burner to determine the suitability of residual fuel oils as carriers in magnesium slurries. Four residual fuel oils with varying viscosities were investigated by themselves and in slurries of 50 percent magnesium. Results regarding the settling characteristics, blow-out velocity, and combustion efficiency are provided.
Date: June 23, 1953
Creator: Cook, Preston N., Jr.; Evans, Vernida E. & Lezberg, Erwin A.
Partner: UNT Libraries Government Documents Department
open access

Internal performance characteristics of variable-throat plug- and vaned-type convergent-divergent nozzles

Description: Investigation of the internal performance characteristics of three types of variable-throat convergent-divergent nozzles over a wide range of pressure ratios. Only small differences in peak thrust coefficient between the three types of variable-throat convergent-divergent nozzles were obtained.
Date: June 23, 1953
Creator: Krull, H. George; Steffen, Fred W. & Ciepluch, Carl C.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Boundary-Layer Suction Through Slots to Obtain Extensive Laminar Boundary Layers on a 15 Percent-Thick Airfoil Section at High Reynolds Numbers

Description: Memorandum presenting a two-dimensional wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and difficulties encountered in obtaining extensive laminar flow are provided.
Date: June 23, 1952
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of boundary-layer suction through slots to obtain extensive laminar boundary layers on a 15-percent-thick airfoil section at high Reynolds numbers

Description: Report presenting a wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and some of the difficulties involved in obtaining extensive laminar flow are provided.
Date: June 23, 1952
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements at Mach Numbers From 1.1 to 1.9 of the Zero-Lift Drag of a Twin-Engine Supersonic Ram-Jet Configuration

Description: Report presenting a flight investigation to determine the zero-lift drag characteristics of a twin-engine supersonic ramjet configuration in order to make performance calculations below the design Mach number. Data was obtained over a range of Mach numbers for two power-off ramjet models with and without nacelles. Information about the variation of Reynolds number, total and external drag coefficients, and model-component drag coefficients is provided.
Date: June 23, 1952
Creator: Leiss, Abraham
Partner: UNT Libraries Government Documents Department
open access

Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21

Description: Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.
Date: June 23, 1952
Creator: Yaker, Charles; Garrett, Floyd B. & Sikora, Paul F.
Partner: UNT Libraries Government Documents Department
open access

Small-Scale Transonic Investigation of the Effects of Partial-Span Leading-Edge Camber on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98

Description: "A small-scale transonic investigation of two semispan wings of the same plan form was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range of 0.70 to 1.10 and a mean-test Reynolds number range of 745,000 to 845,000 to determine the effects of partial-span leading-edge camber on the aerodynamic characteristics of a swept-back wing. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one, was an uncamber… more
Date: June 23, 1952
Creator: Alford, William J., Jr. & Byrnes, Andrew L., Jr.
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer from High-Temperature Surfaces to Fluids. 3 - Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches

Description: "A heat-transfer investigation was conducted with air flowing through an electrically heated silicon carbide tube with a rounded entrance, an inside diameter of 3/4 inch, and an effective heat-transfer length of 12 inches over a range of Reynolds numbers up to 300,000 and a range of average inside-tube-wall temperature up to 2500 R. The highest corresponding local outside-tube-wall temperature was 3010 R. Correlation of the heat-transfer data using the conventional Nueselt relation wherein phys… more
Date: June 23, 1949
Creator: Sams, Eldon W. & Desmon, Leland G.
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer from High-Temperature Surfaces to Fluids 3 - Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches

Description: A heat-transfer investigation was conducted with air flowing through an electrically heated silicon carbide tube with a rounded entrance, an inside diameter of 3/4 inch, and effective heat-transfer length of 12 inches over a range of Reynolds numbers up to 300,000 and a range of average inside-tube-wall temperatures up to 2500 R. The highest corresponding local outside-tube-wall temperature was 3010 R.
Date: June 23, 1949
Creator: Sams, Eldon W. & Desmon, Leland G.
Partner: UNT Libraries Government Documents Department
open access

Force, Static Longitudinal Stability, and Control Characteristics of a 1/16-Scale Model of the Bell XS-1 Transonic Research Airplane at High Mach Numbers

Description: Report presenting results obtained to determine the effects of compressibility at high Mach numbers on a scale model of the Bell XS-1 transonic research airplane. The results are presented for several model configurations through a range of Mach numbers. Results regarding aerodynamic characteristics and static longitudinal stability characteristics are provided.
Date: June 23, 1948
Creator: Mattson, Axel T. & Loving, Donald L.
Partner: UNT Libraries Government Documents Department
open access

Estimation of the Spin and Recovery Characteristics of the North American XSN2J-1 Airplane

Description: "The probable spin and recovery characteristics of the XSN2J-1 air-plane have been estimated on the basis of the results of brief test a performed on a model of an airplane of somewhat similar design. The spin-recovery tail-parachute requirements for the airplane were also determined end, in addition, an analysis was made to determine the best method of emergency pilot escape during a spin. The results of the investigation indicate that the recovery characteristics of the airplane will be satis… more
Date: June 23, 1947
Creator: Snyder, Thomas L.
Partner: UNT Libraries Government Documents Department
open access

Downwash and Wake Behind Plain and Flapped Airfoils

Description: "Extensive experimental measurements have been made of the downwash angles and the wake characteristics behind airfoils with and without flaps and the data have been analyzed and correlated with the theory. A detailed study was made of the errors involved in applying lifting-line theory, such as the effects of a finite wing chord, the rolling-up of the trailing vortex sheet, and the wake. The downwash angles, as computed from the theoretical span load distribution by means of the Biot-Savart eq… more
Date: June 23, 1938
Creator: Silverstein, Abe; Katzoff, S. & Bullivant, W. Kenneth
Partner: UNT Libraries Government Documents Department
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