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Comparison of Free-Flight Measurements of the Zero-Lift Drag Rise of Six Airplane Configurations and Their Equivalent Bodies of Revolution at Transonic Speeds
"Free-flight drag measurements are presented which show the practicability of duplicating the zero-lift drag rise of many airplane configurations by simple bodies of revolution. The results confirm the transonic area rule for straight wings, and for delta and modified-delta wings with and without nacelles. The results showed that the area rule did not apply to one swept-wing configuration and an explanation is advanced to explain why it does not apply" (p. 1).
Date:
January 5, 1954
Creator:
Hall, James Rudyard
System:
The UNT Digital Library
Flight determined buffet boundaries of ten airplanes and comparisons with five buffeting criteria
Report presenting the flight-determined buffet boundaries of ten airplanes. Comparisons are made with five possible buffeting criteria related to airfoil-section characteristics. The primary factors that determine buffeting criteria are critical Mach number, Mach number of sonic flow at the crest, lift-divergence Mach number, lift-peak Mach number, and empirical buffeting criterion are provided.
Date:
January 5, 1951
Creator:
Gadeberg, Burnett L. & Ziff, Howard L.
System:
The UNT Digital Library
Load-Range Performance of Turbine-Propeller Engine in Transonic Speed Range and Comparison With Load-Range Performance of Turbojet Engine
Memorandum presenting an investigation of the effect on load-range performance of various combinations of compressor pressure ratio and turbine-inlet temperature for the turbine-propeller engine and to provide a means for comparing the load range of turbine-propeller and turbojet engines for a range of flight speeds.
Date:
January 5, 1951
Creator:
Lubarsky, Bernard
System:
The UNT Digital Library
The effects of boundary-layer control on the longitudinal characteristics of a swept-back wing using suction through streamwise slots in the outboard portion of the wing
Report presenting an investigation to determine the effects of a simplified form of boundary-layer control on the low-speed longitudinal characteristics of a sweptback wing. The primary objective was to improve the longitudinal characteristics of the sweptback wing at lift coefficients below the maximum. Results regarding the characteristics of the wing without boundary-layer control and effects of boundary-layer control are provided.
Date:
January 5, 1951
Creator:
McCormack, Gerald M. & Tolhurst, William H., Jr.
System:
The UNT Digital Library
Low-Speed Investigation of the Effects of Location of a Delta and a Straight Tail on the Longitudinal Stability and Control of a Thin Delta Wing With Extended Double Slotted Flaps
Report presenting an investigation to determine the effects of horizontal-tail location and plan form on the longitudinal stability and control characteristics of a fuselage and thin delta wing with extended double slotted flaps. Several configurations of the aircraft, including flaps with the tail off, extended double slotted flaps, and canard with extended double slotted flap and delta tail are explored.
Date:
January 5, 1954
Creator:
Riebe, John M. & Graven, Jean C., Jr.
System:
The UNT Digital Library
Effect on Transonic and Supersonic Drag of a Fuselage Protuberance of an Essential Unswept Wing-Fuselage Combination
"An investigation of the effect on transonic and supersonic drag of a fuselage protuberance designed to improve the overall longitudinal distribution of cross-sectional area of an essentially unswept wing-fuselage combination has been made with free-flight rocket models. The wing-fuselage configuration was tested with and without a fuselage protuberance designed to relieve the steep area gradient over the rear portion of the wing" (p. 1).
Date:
January 5, 1954
Creator:
Sandahl, Carl A.
System:
The UNT Digital Library
Tests of the Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Wing Modifications
"Wind-tunnel tests were conducted to determine the longitudinal stability characteristics of a full-scale Northrop XSSM-A-3 missile. Various wing modifications were investigated in an effort to provide a configuration that would maintain longitudinal stability to lift coefficients necessary for landing the missile during flight tests. The results of the tests led to the choice of a wing with an increased leading-edge radius" (p. 1).
Date:
January 5, 1950
Creator:
Graham, David
System:
The UNT Digital Library
A cascade-general-momentum theory of operation of a supersonic propeller annulus
Report presenting a cascade-general-momentum theory method for calculating the operating conditions of a supersonic propeller annulus throughout the flight Mach number range. General flow patterns about the cascade and adjustments to free-stream conditions are discussed.
Date:
January 5, 1953
Creator:
Klawans, Bernard B. & Vogeley, Arthur W.
System:
The UNT Digital Library
Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 2 - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 Degrees
The stator-blade angles in the twelfth through fifteenth stages of a 16-stage axial-flow compressor were increased 3O. The over-all performance of this modified compressor is compared to the performance of the compressor with original blade angles. The matching characteristics of the modified compressor and a two-stage turbine were obtained and compared to those of the compressor with original blade angles and the same turbine.
Date:
January 5, 1952
Creator:
Hatch, James E. & Medeiros, Arthur A.
System:
The UNT Digital Library