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Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000
Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date:
May 23, 1947
Creator:
Neely, Robert H. & Conner, D. William
System:
The UNT Digital Library
Operating Temperatures of I-40-5 Turbojet Engine Burner Liners and the Effect of Temperature Variation on Burner-Liner Service Life
Report presenting an investigation of burner liners in a turbojet engine to determine the principal factors limiting the burner-liner service life. The investigation covered a range of engine speeds and testing was conducted to determine whether bare, ceramic-coated, or shielded thermocouples would give the most correct temperature readings.
Date:
August 23, 1948
Creator:
Wilsted, H. D.; Duffy, Robert T. & Grey, Ralph E.
System:
The UNT Digital Library
Free-flight investigation of the rolling effectiveness at high subsonic, transonic, and supersonic speeds of leading-edge and trailing-edge ailerons in conjunction with tapered and untapered plan forms
Report presenting several rectangular and tapered wing configurations with leading-edge and trailing-edge ailerons tested as part of a general investigation of an aerodynamic control at supersonic speeds. Results indicated that the use of the leading-edge aileron alone was ineffective or caused negative control until a high Mach number was attained. Results for the untapered configurations, tapered configurations, and drag measurements are provided.
Date:
July 23, 1948
Creator:
Strass, H. Kurt
System:
The UNT Digital Library
Residual Stress Analysis of Overspeeded Disk With Central Hole by X-Ray Diffraction
An X-ray - diffraction analysis of residual surface stresses after plastic strain was introduced in a parallel-sided 3S-O aluminum disk with a central hole by two types of centrifugal overspeed is reported. Both tangential and radial stresses were generally tensile with large local variations near the hole where surface stresses may have been partly superficial. These stresses were both tensile and compressive dependent on the distance from the disk center when mass compression was effected near the hole.
Date:
July 23, 1948
Creator:
Good, James N.
System:
The UNT Digital Library
Low-speed wind-tunnel investigation of the longitudinal stability characteristics of a model equipped with a variable-sweep wing
Report presenting an investigation to determine the longitudinal stability characteristics of a complete model equipped with a variable-sweep wing at four different angles of sweepback. The primary objective was to study various wing modifications and an external-flap arrangement designed to minimize the shift in neutral point accompanying the change in sweep angle.
Date:
May 23, 1949
Creator:
Donlan, Charles J. & Sleeman, William C., Jr.
System:
The UNT Digital Library
Wind-Tunnel investigation of NACA 65,3-418 airfoil section with boundary-layer control through a single suction slot applied to a plain flap
Report presenting an investigation in the two-dimensional low-turbulence tunnel of the NACA 65,3-418 airfoil section with a 25-percent-airfoil-chord plain flap and a suction slot on the flap. The primary purpose of the investigation is to determine the effect of the type of boundary-layer control on the section lift-drag ratio.
Date:
February 23, 1949
Creator:
Horton, Elmer A. & von Doenhoff, Albert E.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
Investigation of flap-type ailerons on an untapered wing having an aspect ratio of 3.7, 45 degree sweepback, and an NACA 65A009 airfoil section: Transonic-bump method
Report presenting an investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream.
Date:
August 23, 1950
Creator:
MacLeod, Richard G.
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: A Pressure-Distribution Study of the Aerodynamic Characteristics of the Wing at Mach Number 1.59
Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.
Date:
May 23, 1950
Creator:
Cooper, Morton & Spearman, M. Leroy
System:
The UNT Digital Library
An Investigation of Several Supersonic Missile Configurations Directed Toward Minimizing Center-of-Pressure Travel
Memorandum presenting an investigation in the 9-inch supersonic tunnel of several missiles with low-aspect-ratio, cruciform, tandem lifting surfaces with a view toward developing a missile with small variations of center-of-pressure location at various angles of attack and roll. The investigation centered about a basic configuration with equal-span wings and tails.
Date:
September 23, 1952
Creator:
Rainey, Robert W.
System:
The UNT Digital Library
Experimental Investigation of the Stability, Control, and Induced Rolling Moments of a Canard Missile Airframe at a Mach Number of 1.7
Memorandum presenting the results of an investigation of the stability, control, and induced rolling moments of a canard missile with cruciform wings of rectangular plan form at Mach number 1.7. All of the data obtained, including the measured hinge moments of the canard control surfaces, axial forces on the complete missile, and forces and moments on the various combinations of missile components are presented in tabular form.
Date:
September 23, 1952
Creator:
Chubb, Robert S.
System:
The UNT Digital Library
Effects of double-slotted flaps and leading-edge modifications on the low-speed characteristics of a large-scale 45 degrees swept-back wing with and without camber and twist
Report presenting an investigation of two large-scale, semispan, wing-fuselage models with the 0.25-chord line swept back 45 degrees to determine and compare the effects of partial-span, double-slotted flaps on the characteristics of a 45 degree sweptback wing with and without camber and twist. A secondary investigation was also conducted to determine the effects of various full-span, leading-edge modifications on the characteristics of the models with and without the flaps.
Date:
July 23, 1951
Creator:
James, Harry A. & Dew, Joseph K.
System:
The UNT Digital Library
Large-scale flight measurements of zero-lift drag at Mach numbers from 0.8 to 1.6 of a wing-body combination having an unswept 4.5 percent thick wing with modified hexagonal sections
Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination from high-subsonic to supersonic speeds in a range of Reynolds numbers. The wing was unswept about the 74.5-percent-chord line, an aspect ratio of 3.04, a taper ratio of 0.394, and 4.5-percent-thick modified hexagonal airfoil sections. Results regarding total drag, wing-plus-interference drag, and base pressure are provided.
Date:
March 23, 1951
Creator:
Schult, Eugene D.
System:
The UNT Digital Library
Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91
Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date:
September 23, 1952
Creator:
Cahill, Jones F. & Nuber, Robert J.
System:
The UNT Digital Library
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail: longitudinal characteristics
Report presenting an investigation to determine the effect of an all-movable horizontal tail on the low-speed longitudinal characteristics of a triangular-wing airplane. The model consisted of a triangular wing of aspect ratio 2, a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail, and a thin, unswept, all-movable horizontal tail.
Date:
April 23, 1951
Creator:
Graham, David & Koenig, David G.
System:
The UNT Digital Library
The properties of three cast polyester resins of Sierracin 212, 212A, and 250A
From Summary: "Physical properties of samples of three cast polyester resins known as Sierracin resins were investigated. Tests were made to determine specific gravity, index of refraction, Rockwell hardness, Tukon indentation hardness, effect of exposure to accelerated and outdoor weathering, Munsell color, resistance to accelerated service tests, crazing resistance under stress, flexural strength, Izod impact strength, and Taber abrasion resistance. Tables of the values obtained for these physical properties are included in the report."
Date:
April 23, 1951
Creator:
Kline, G. M.
System:
The UNT Digital Library
Summary of Normal Accelerations, Gust Velocities, and Operating Practices, From April to August 1949 of a Twin-Engine Airplane in Commercial Transport Operations
Report presenting the first sample of time-history data of airspeed, altitude, and normal accelerations obtained by the NACA VGH recorder in transport operations. This data defines the distribution of normal accelerations and airspeeds in greater detail than what was obtainable with the V-G recorder. Results regarding effective gust velocities, proportion of time spent in rough air, values of airspeed in descent, and variations in load experience are provided.
Date:
August 23, 1950
Creator:
Steiner, Roy & McDougal, Robert L.
System:
The UNT Digital Library
Tests of a small-scale NACA submerged inlet at transonic Mach numbers
Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.
Date:
February 23, 1950
Creator:
Rolls, L. Stewart & Rathert, George A., Jr.
System:
The UNT Digital Library
Low-speed investigation of the effects of nacelles on the longitudinal aerodynamic characteristics of a 60 degree sweptback delta-wing - fuselage combination with NACA 65A003 airfoil sections
Report presenting an investigation in the full-scale tunnel to determine the effects of symmetrically located wing nacelles on the low-speed aerodynamic characteristics of a 60 degree sweptback delta-wing-fuselage combination. The testing occurred with three spanwise nacelle locations with three chordwise positions at each spanwise station.
Date:
July 23, 1952
Creator:
Scallion, William I.
System:
The UNT Digital Library
Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21
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.
System:
The UNT Digital Library
Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip
Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip with freedom in roll. The results indicated that the longitudinal position of the fighters with respect to the bomber had an important effect on the flight behavior of the coupled configuration.
Date:
September 23, 1952
Creator:
Bennett, Charles V. & Boisseau, Peter C.
System:
The UNT Digital Library
Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails
Report presenting a low-speed investigation in the stability tunnel to determine the effects of tail height, length, and aspect ratio on the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with twin triangular all-movable tails located near the wing tips.
Date:
May 23, 1952
Creator:
Jaquet, Byron M.
System:
The UNT Digital Library
Flight Measurements of the Lateral Stability and Control Characteristics of a High-Speed Fighter Airplane
Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.
Date:
September 23, 1952
Creator:
Crane, H. L.; Beckhardt, A. R. & Matheny, C. E.
System:
The UNT Digital Library
Low speed stability characteristics of a complete model with a wing of W plan form
Report presenting an investigation of the low-speed static stability characteristics of a complete model equipped with a W wing. The lift-curve slope of the wing-fuselage combination was found to be in good agreement with that predicted by available wing-alone theory. Results regarding the longitudinal characteristics, wing-juncture modifications, and lateral and directional stability characteristics are provided.
Date:
April 23, 1952
Creator:
Polhamus, Edward C. & Becht, Robert E.
System:
The UNT Digital Library