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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
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
Simulated Flight Investigation of Scaled-speed Elastic Sweptwing Bomber and Fighter Models Coupled Wing Tip to Wing Tip

Simulated Flight Investigation of Scaled-speed Elastic Sweptwing Bomber and Fighter Models Coupled Wing Tip to Wing Tip

Date: February 14, 1956
Creator: Thompson, R. F.
Description: Simulated flight tests of elastic swept-wing bomber and fighter model coupled wing tip to wing tip.
Contributing Partner: UNT Libraries Government Documents Department
Some considerations regarding the application of the supersonic area rule to the design of airplane fuselages

Some considerations regarding the application of the supersonic area rule to the design of airplane fuselages

Date: July 3, 1956
Creator: Whitcomb, R. T.
Description: Supersonic aircraft fuselage design for minimum wave drag.
Contributing Partner: UNT Libraries Government Documents Department
Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Date: December 28, 1956
Creator: Allen, J. L.
Description: Blunt-lip side inlet with ramp bleed, bypass, and duct ahead of engine.
Contributing Partner: UNT Libraries Government Documents Department
Performance of a Supersonic Ramp-type Side Inlet With Ram-scoop Throat Bleed and Varying Fuselage Boundary-layer Removal Mach Number Range 1.5 to 2.0

Performance of a Supersonic Ramp-type Side Inlet With Ram-scoop Throat Bleed and Varying Fuselage Boundary-layer Removal Mach Number Range 1.5 to 2.0

Date: January 17, 1957
Creator: Campbell, R. C. & Mitchell, G. A.
Description: Performance of supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary layer removal at low supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-engine Matching Up to Mach 3

Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-engine Matching Up to Mach 3

Date: May 20, 1958
Creator: Beheim, M. A. & Gertsma, L. W.
Description: Performance at mach 3.07, 1.89 and 0 of inlets designed for inlet-engine matching up to mach 3.
Contributing Partner: UNT Libraries Government Documents Department
Performance Characteristics of Several Divergent-shroud Aircraft Ejectors

Performance Characteristics of Several Divergent-shroud Aircraft Ejectors

Date: September 8, 1955
Creator: Beale, W. T. & Greathouse, W. K.
Description: Performance characteristics of several divergent- shroud aircraft ejectors.
Contributing Partner: UNT Libraries Government Documents Department
A comparison of flight-measured carrier- approach speeds with values predicted by several different criteria for 41 fighter-type airplane configurations

A comparison of flight-measured carrier- approach speeds with values predicted by several different criteria for 41 fighter-type airplane configurations

Date: May 8, 1958
Creator: Drinkwater, F. J., III; Schlaff, B. A. & White, M. D.
Description: Comparison of flight measured carrier-approach speeds with values predicted by several different criteria for 41 fighter aircraft configurations.
Contributing Partner: UNT Libraries Government Documents Department
A summary of results obtained during flight simulation of several aircraft prototypes with variable-stability airplanes

A summary of results obtained during flight simulation of several aircraft prototypes with variable-stability airplanes

Date: May 25, 1956
Creator: Creer, B. Y. & Mc Neill, W. E.
Description: Dynamic lateral stability and handling data from flight simulation with F6F-3 and F-86A VARIABLE-STABILITY aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests of a series of practice bombs

Wind tunnel tests of a series of practice bombs

Date: October 1, 1957
Creator: Ward, D. H.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Vi - Swept-wing Heavy-bomber Configuration With Stores of Different Sizes and Shapes

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Vi - Swept-wing Heavy-bomber Configuration With Stores of Different Sizes and Shapes

Date: March 8, 1956
Creator: Smith, N. F.
Description: Effect of stores on a swept-wing heavy bomber.
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. V - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Mach Number 2.01

The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. V - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Mach Number 2.01

Date: February 13, 1956
Creator: Carlson, H. W. & Geier, D. J.
Description: Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure.
Contributing Partner: UNT Libraries Government Documents Department
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wingfuselage-store Configurations. Iv.-delta-wing Heavy-bomber Configuration With Large Store. Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wingfuselage-store Configurations. Iv.-delta-wing Heavy-bomber Configuration With Large Store. Mach Number, 1.61

Date: December 15, 1955
Creator: Morris, O. A.
Description: Origin and distribution of supersonic store interference/measurement of individual forces on delta-wing heavy bomber configuration mach 1.61.
Contributing Partner: UNT Libraries Government Documents Department
Force and Pressure Measurements on Several Canopy-fuselage Configurations at Mach Numbers 1.41 and 2.01

Force and Pressure Measurements on Several Canopy-fuselage Configurations at Mach Numbers 1.41 and 2.01

Date: December 15, 1955
Creator: Robins, A. W.
Description: Force and pressure measurements on several canopy- fuselage configurations at low supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Full-scale wind-tunnel tests of a 35 deg swept-wing fighter airplane with a spoiler- slot-deflector lateral control system

Full-scale wind-tunnel tests of a 35 deg swept-wing fighter airplane with a spoiler- slot-deflector lateral control system

Date: October 26, 1956
Creator: Scallion, W. I.
Description: Wind tunnel tests of swept-wing fighter aircraft with spoiler-slot-deflector lateral control system.
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer in Regions of Separated and Reattached Flows

Heat Transfer in Regions of Separated and Reattached Flows

Date: June 10, 1957
Creator: Crawford, D. H. & Rumsey, C. B.
Description: Heat transfer in regions of separated and reattached flows.
Contributing Partner: UNT Libraries Government Documents Department
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