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Performance of J-33-A-21 and J-33-A-23 Compressors With and Without Water Injection

Description: "In an investigation of the J-33-A-21 and the J-33-A-23 compressors with and without water injection, it was discovered that the compressors reacted differently to water injection although they were physically similar. An analysis of the effect of water injection on compressor performance and the consequent effect on matching of the compressor and turbine components in the turbojet engine was made. The analysis of component matching is based on a turbine flow function defined as the product of the equivalent weight flow and the reciprocal of the compressor pressure ratio" (p. 1).
Date: January 28, 1948
Creator: Beede, William L.
Partner: UNT Libraries Government Documents Department

Tentative Procedures for Analysis of HCP Process Materials

Description: Abstract: The procedures recommended for analysis in Department 190 Laboratories, in the Limits Control Laboratory, and in the Analytical Development Laboratories, of all process materials from the HCP cycle are presented in a stepwise manner. A description of the characteristics of each sample type along with a brief description of factors involved in the Analytical Quality Control program is included.
Date: May 28, 1947
Creator: Belknap, Herbert J.; Nessle, G. J. & Grimes, W. R.
Partner: UNT Libraries Government Documents Department

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Vee Tail

Description: "An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-ft free-spinning tunnel. Results of tests with a conventional tail have been previously reported; the results presented herein are for the model with a vee tail installed. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model. In the normal loading were determined" (p. 1).
Date: November 28, 1947
Creator: Berman, Theodore
Partner: UNT Libraries Government Documents Department

Effects of wing-tip turrets on the aerodynamic characteristics of a typical bomber-wing model

Description: Report presenting wind-tunnel tests up to a Mach number of 0.85 to determine the effects of wing-tip gun turrets on the aerodynamic characteristics of a typical bomber-wing model. Lift, drag, and pitching-moment data are presented for the wing alone; for the wing with the turrets in the clean condition; and for the wing and the turrets with guns and sighting equipment. The turrets had negligible effect on the lift and pitching-moment characteristics of the wing.
Date: March 28, 1949
Creator: Boddy, Lee E. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department

Theoretical investigation of thrust augmentation of turbojet engines by tail-pipe burning

Description: Report presenting a theoretical analysis of thrust augment of turbojet engines by tail-pipe burning and charts from which the thrust augmentation produced may be evaluated from the normal engine data and performance of the tail-pipe burner. Results regarding general curves and illustrative curves are provided.
Date: January 28, 1947
Creator: Bohanon, H. R. & Wilcox, E. C.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of Two NACA 7-Series Type Airfoils Equipped With a Slot-Lip Aileron, Trailing-Edge Frise Aileron, and a Double Slotted Flap

Description: Report presenting a wind-tunnel investigation of two NACA 7-series type airfoils, one with 17.7-percent chord thickness and one with 15.4-percent chord thickness, each quipped with a 30-percent-airfoil-chord double slotted flap, a slot-lip aileron, and a trailing-edge Frise aileron with two amounts of overhang balance. Measurements of airfoil lift and drag, Frise aileron hinge moment, and slot-lip aileron hinge moment were obtained through a large range of deflection of flap, Frise aileron, and slot-lip aileron and section angle of attack. Satisfactory lateral control can be obtained by using this combination of airfoils, flaps, and ailerons.
Date: March 28, 1949
Creator: Braslow, Albert L. & Visconti, Fioravante
Partner: UNT Libraries Government Documents Department

A Torsional Stiffness Criterion for Preventing Flutter of Wings of Supersonic Missiles

Description: "A formula, based on a semirational analysis, is presented for estimating the torsional stiffness necessary to prevent flutter of a sweptback or unswept uniform wing that attains supersonic speeds. Results of missile flights at speeds up to Mach number 1.4 demonstrate the usefulness of the formula" (p. 1).
Date: August 28, 1947
Creator: Budiansky, Bernard; Kotanchik, Joseph N. & Chiarito, Patrick T.
Partner: UNT Libraries Government Documents Department

Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnels to develop optimum double-slotted-flap configurations for seven thin NACA airfoil sections. Each was equipped with the same flaps and measured at the same Reynolds numbers. Results regarding the lift characteristics and pitching moment are provided.
Date: April 28, 1947
Creator: Cahill, Jones F. & Racisz, Stanley F.
Partner: UNT Libraries Government Documents Department

Effects of Variations in Forebody and Afterbody Dead Rise on the Resistance and Spray Characteristics of the 22ADR Class VPB Airplane: Langley Tank Model 207, TED No. NACA 2361

Description: From Summary: "An investigation was made to determine the effects of changes in the amount and distribution of forebody and afterbody dead rise on the hydrodynamic resistance and spray characteristics of a 1/11-size model of the Bureau of Aeronautics design No. 22ADR class VPB airplane. The variations in dead rise within the range investigated had no significant effects on resistance or trim, free to trim, or on resistance or trimming moment, fixed in trim. The coordinates of the peaks of the bow-spray blisters, with reference to the model, were measured at low speeds, and it was found that the model with the low dead rise at the bow had the lowest blisters."
Date: August 28, 1947
Creator: Clement, Eugene P. & Daniels, Charles J.
Partner: UNT Libraries Government Documents Department

Aerodynamic Characteristics of Two All-Movable Wings Tested in the Presence of a Fuselage at a Mach Number of 1.9

Description: Report presenting testing of half-span models of two wings of different plan form as both all-movable and fixed surfaces in the presence of a half fuselage. All-movable surfaces are being considered for supersonic aircraft as possible angle-of-attack indicators, control surfaces, and all-movable wings. Results regarding the lift characteristics, center of pressure, and drag of the wings are provided.
Date: October 28, 1948
Creator: Conner, D. William
Partner: UNT Libraries Government Documents Department

Analytical Services - Pile Area Laboratories

Description: This is a report on Analytical Services of the Pile Area Laboratories at Hanford. Pertinent facts are listed regarding the analytical services currently provided by the Analytical Section in the pile areas. The work of the Analytical Section in the pile areas may be classified into five categories as follows: Analysis of pile process water, analysis of power plant (boiler) waters, analysis of drinking water, analysis of columbia (non-process) and Yakima River water, and preparation of reagents and standard solutions.
Date: January 28, 1949
Creator: Curtis, R. E.
Partner: UNT Libraries Government Documents Department

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7-by 10-Foot Tunnel: TED No. DE308, Part 6, Estimated High-Speed Flying Qualities

Description: "An analysis of the estimated high-speed flying qualities of the Chance Vought XF7U-1 airplane in the Mach number range from 0.40 to 0.91 has been made, based on tests of an 0.08-scale model of this airplane in the Langley high-speed 7- by 10-foot wind tunnel. The analysis indicates longitudinal control-position instability at transonic speeds, but the accompanying trim changes are not large. Control-position maneuvering stability, however, is present for all speeds. Longitudinal lateral control appear adequate, but the damping of the short-period longitudinal and lateral oscillations at high altitudes is poor and may require artificial damping" (p. 1).
Date: October 28, 1948
Creator: Donlan, Charles J. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department