Bell 47D1 Helicopter, manufactured by Bell Helicopter Inc., USA

Bell 47D1 Helicopter, manufactured by Bell Helicopter Inc., USA

Access: Use of this item is restricted to the UNT Community.
Date: 1945
Creator: Young, Arthur
Description: The 47D1 Bell helicopter hangs in the exhibition space in the Museum of Modern Art. The acrylic plastic bubble resembles an insect's head.
Contributing Partner: UNT College of Visual Arts + Design
Transportability Studies : ML-1 Nuclear Power Plant

Transportability Studies : ML-1 Nuclear Power Plant

Date: April 1960
Creator: Blakley, J. W.; Alcorn, J. S.; Del Valle, L. G.; Healy, P. W.; Moran, D. H. & Scott, W. S.
Description: Report that discusses programs to determine the transportability of the ML-1 nuclear power plant via railroad, tractor-trailer, and aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Corrosion Protection of Aerospace Grade Magnesium Alloy Elektron 43™ for Use in Aircraft Cabin Interiors

Corrosion Protection of Aerospace Grade Magnesium Alloy Elektron 43™ for Use in Aircraft Cabin Interiors

Date: August 2013
Creator: Baillio, Sarah S.
Description: Magnesium alloys exhibit desirable properties for use in transportation technology. In particular, the low density and high specific strength of these alloys is of interest to the aerospace community. However, the concerns of flammability and susceptibility to corrosion have limited the use of magnesium alloys within the aircraft cabin. This work studies a magnesium alloy containing rare earth elements designed to increase resistance to ignition while lowering rate of corrosion. The microstructure of the alloy was documented using scanning electron microscopy. Specimens underwent salt spray testing and the corrosion products were examined using energy dispersive spectroscopy.
Contributing Partner: UNT Libraries
A British short "Sunderland" flying boat patrolling the sea lanes.

A British short "Sunderland" flying boat patrolling the sea lanes.

Date: unknown
Creator: Davies, Roland.
Description: A "flying boat" aircraft is shown flying over the sea. A ship can be seen in the water below.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Date: January 30, 1958
Creator: Allen, J. L.
Description: Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Date: August 6, 1958
Creator: Obery, L. J. & Stitt, L. E.
Description: Internal compression inlet with throat bleed-off at hypersonic flow.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Isentropic Nose Inlets at Mach Number of 5.6

Performance of Isentropic Nose Inlets at Mach Number of 5.6

Date: May 6, 1954
Creator: Bernstein, H. & Haefeli, R. C.
Description: Isentropic nose inlet performance at mach 5.6.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Variable Two-dimensional Inlet Designed for Engine-inlet Matching. I - Performance at Design Mach Number of 3.07

Performance of Variable Two-dimensional Inlet Designed for Engine-inlet Matching. I - Performance at Design Mach Number of 3.07

Date: November 20, 1956
Creator: Beheim, M. A. & Gertsma, L. W.
Description: Supersonic performance of variable two-dimensional inlets designed for engine-inlet matching.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study. Iii - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-flow Effects and Conclusions From Entire Stator Investigation

Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study. Iii - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-flow Effects and Conclusions From Entire Stator Investigation

Date: September 17, 1957
Creator: Moffitt, T. P.; Rohlik, H. E. & Wintucky, W. T.
Description: Hub-tip radius ratio transonic turbine for secondary flow - stator configurations designed to eliminate blade wakes and secondary-flow effects.
Contributing Partner: UNT Libraries Government Documents Department
Lateral-control Characteristics and Dihedral Effect of a Wingbody Combination With a Variable-incidence Triangular Wing and Wing-tip Ailerons at a Mach Number of 1.52

Lateral-control Characteristics and Dihedral Effect of a Wingbody Combination With a Variable-incidence Triangular Wing and Wing-tip Ailerons at a Mach Number of 1.52

Date: January 10, 1951
Creator: Dennis, D. H. & Scherrer, R.
Description: Aileron effectiveness & dihedral effect of wing- body combination with variable-incidence wing & half-delta controls at wing tips.
Contributing Partner: UNT Libraries Government Documents Department
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