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The Bernard 82 Military Airplane (French): A Long-Range Monoplane

Description: Circular presenting a description of the Bernard 82, which is a scaled-up version of the 80 G.R.; they have similar designs but the 82 has greater span and wing area, deeper chord, higher fuselage, and a thicker wing for the bombs. A description of some flight tests and characteristics is also provided.
Date: June 1934
Partner: UNT Libraries Government Documents Department

As Investigation at Mach Numbers of 1.41 and 2.01 of the Aerodynamic Characteristics of an 0.025-scale Model of the MX-1712

Description: "An investigation of the aerodynamic characteristics of an 0.025-scale model of the MX-1712 configuration has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel. The tests were performed at Mach numbers of 1.41 and 2.01 at a Reynolds number of approximately 2.6 x 10(exp 6) based on the wing mean aerodynamic chord. The MX-1712 is a proposed swept-wing, jet-powered supersonic bomber aircraft. The wing is of aspect ratio 3.5, taper ratio 0.2, and thickness ratio 5.5 percent (streamwise) and has 47deg sweep of the quarter-chord line" (p. 1).
Date: October 17, 1952
Creator: Smith, Norman F. & Hasel, Lowell E.
Partner: UNT Libraries Government Documents Department

An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration

Description: Report presenting an investigation of a swept-wing supersonic bomber configuration in the 4- by 4-foot supersonic pressure tunnel. Testing occurred at Mach numbers of 1.41 and 2.01 and a designated Reynolds number based on the wing mean aerodynamic chord. The model had a tapered wing with an aspect ratio of 3.5, a taper ratio of 0.2, a thickness ratio of 5.5 percent and 47 degrees sweep of the quarter-chord line. The investigation included the longitudinal and lateral force characteristics and various combinations of its components, including several jet nacelle installations.
Date: February 1, 1956
Creator: Smith, Norman F. & Hasel, Lowell E.
Partner: UNT Libraries Government Documents Department

Analysis of the turbojet for propulsion of supersonic bombers

Description: From Introduction: "The investigation is discussed in the present report is an analysis of the turbojet engine as the power plant for bombers capable of supersonic flight speeds. A similar analysis, in which the turbojet engine is considered for the propulsion of supersonic fighter aircraft, is presented in reference 1. Two plans are considered in this report."
Date: April 5, 1954
Creator: Krebs, Richard P. & Wilcox, E. Clinton
Partner: UNT Libraries Government Documents Department

Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber

Description: From Introduction: "The difficulties experienced in cooling the exhaust-valve seats of the rear-row cylinders have been overcome to a considerable extent by improving the mixture distribution through application of the injection impeller (reference 1) and by augmenting the flow of cooling air to the critical baffles (reference 2). Flight tests of this airplane (reference 3) indicated that the temperatures of exhaust-valve seats on rear-row cylinders were markedly lowered by these modifications and that airplane range, altitude, and gross weight previously limited by these temperatures could be greatly increased."
Date: March 14, 1946
Creator: Marble, Frank E.; Miller, Marlon A. & Bell, E. Barton
Partner: UNT Libraries Government Documents Department

Dynamic Longitudinal Stability and Control of Tandem Coupled Bomber-Fighter Airplane Models With Rigid and Pitch-Free Couplings

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic longitudinal stability and control characteristics of tandem-coupled bomber-fighter airplane models. Results regarding bomber alone tests, freely coupled combination, and rigidly coupled combination are provided.
Date: January 22, 1951
Creator: Grana, David C. & Hewes, Donald E.
Partner: UNT Libraries Government Documents Department

Fortress of the Sky

Description: This film shows the work that everyone from Boeing researchers to factory workers put in to Boeing aircraft.
Date: 1943
Creator: Knox, Gordon; Burnside, Norman & Gudebrod, G. David
Partner: UNT Media Library

Measurements of ground-reaction forces and vertical center-of-gravity accelerations of a bomber airplane taxiing over obstacles

Description: Report presenting an investigation made on an unswept-wing four-engine bomber airplane to determine the vertical and drag ground-reaction forces imposed on the landing gear when taxiing over obstacles of various sizes. Results are presented of the effects of ground speed and the widths and heights of the obstacles on the vertical and drag forces, vertical acceleration at the center of gravity of the airplane, on shock-strut displacement, and on response of the upper mass of the airplane structure.
Date: September 1958
Creator: McKay, James M.; Sawyer, Richard H. & Hall, Albert W.
Partner: UNT Libraries Government Documents Department

Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Description: From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."
Date: December 5, 1956
Creator: Bielat, Ralph P.; Coffee, Claude W., Jr. & Petynia, William W.
Partner: UNT Libraries Government Documents Department

A Theoretical Study of the Effect of Control-Deflection and Control-Rate Limitations on the Normal Acceleration and Roll Response of a Supersonic Interceptor

Description: Memorandum presenting a theoretical study of the effect of limiting the deflection and rate of deflection of the control surface on the normal acceleration and roll response to step commands for a representative, automatically controlled, supersonic, tailless interceptor. Results regarding pitch, roll, and some general comments are provided.
Date: April 29, 1953
Creator: Matthews, Howard F. & Schmidt, Stanley F.
Partner: UNT Libraries Government Documents Department

An investigation of the aerodynamic characteristics at transonic Mach numbers of a swept-wing supersonic bomber configuration

Description: Report presenting an investigation of the aerodynamic characteristics of a swept-wing supersonic bomber configuration conducted in the 8-foot transonic tunnel. The wing had an aspect ratio of 3.5, taper ratio of 0.2, 47 degrees of sweepback of the 0.25-chord line, and airfoil sections which were 5.5 percent thick parallel to the plane of symmetry. Results regarding the longitudinal force characteristics, effects of wing incidence, a modified wing, various auxiliary wing devices, and horizontal-tail height are provided.
Date: February 1, 1956
Creator: Bielat, Ralph P. & Cooper, J. Lawrence
Partner: UNT Libraries Government Documents Department

Analysis of the Horizontal-Tail Loads Measured in Flight on a Multiengine Jet Bomber

Description: "The primary objectives of the present paper are to report the horizontal-tail-loads measurements for configuration B which have not previously been reported and to summarize the horizontal-tail-loads results obtained with both configurations. The manner in which the aerodynamic-loads data were analyzed to include structural temperature effects and fuselage flexibility effects constitutes an important part of the present paper" (p. 1).
Date: September 1955
Creator: Aiken, William S., Jr. & Wiener, Bernard
Partner: UNT Libraries Government Documents Department

The effect of altitude on bomber performance

Description: Report presenting a study devoted to the analysis of the effect of design and operating altitude on the performance of bombers. The primary emphasis is on range performance and charts are presented with range as a function of wing loading, power loading, and design altitude. Results regarding the range at maximum L/D, range at constant power, and performance charts are provided.
Date: October 1943
Creator: Hill, Paul R. & Crigler, John L.
Partner: UNT Libraries Government Documents Department

Comparison of Wind-Tunnel and Flight Measurements of Stability and Control Characteristics of a Douglas A-26 Airplane

Description: Tests in Langley pressure tunnel of model XA-26 bomber were compared with those of A-26B (twin-engine attack bomber) and showed that static longitudinal stability, indicated by elevator-fixed neutral points, and variation of elevator deflection in straight and turning flight were good. Airplane possessed improved stability at low speeds which was attributed to pronounced stalling at root of production wing. At rudder-force reversal at speeds higher than those in flight tests, agreement in rudder-fixed and rudder-free static directional stability was good. Hinge moment obtained at zero sideslip was satisfactory for determining aileron forces in sideslip.
Date: March 1946
Creator: Kayten, Gerald G. & Koven, William
Partner: UNT Libraries Government Documents Department

An evaluation of the effects of flexibility on wing strains in rough air for a large swept-wing airplane by means of experimentally determined frequency-response functions with an assessment of random-process techniques employed

Description: Report presenting power spectral methods of analysis as applied to flight test measurements of the strain responses of a large swept-wing bomber airplane in rough air in order to determine the effects of airplane in rough air in order to determine the effects of airplane structural dynamics on the strain responses.
Date: July 1958
Creator: Coleman, Thomas L.; Press, Harry & Meadows, May T.
Partner: UNT Libraries Government Documents Department

The Development of Jet-Engine Nacelles for a High-Speed Bomber Design

Description: "The results of an experimental investigation made for the purpose of developing suitable jet-engine nacelle designs for a high-speed medium bomber are presented. Two types of nacelles were investigated, the first enclosing two 4000-pounds-thrust jet engines and a 65-inch-diameter landing wheel and the second enclosing a single 4000-pounds-thrust jet engine. Both types of nacelles were tested in positions underslung beneath the wing and centrally located on the wing" (p. 1).
Date: August 29, 1947
Creator: Dannenberg, Robert E.
Partner: UNT Libraries Government Documents Department

Free-Flight Investigation of the Drag of a Model of a 60 Degree Delta-Wing Bomber With Strut-Mounted Siamese Nacelles and Indented Fuselage at Mach Numbers From 0.80 to 1.35

Description: Memorandum presenting a model of a 60 degree delta-wing bomber with strut-mounted Siamese nacelles, which was designed, with the use of a symmetrical fuselage indentation, to have a smooth average area distribution at a Mach number of 1.20. The results show that the configuration drag rise was significantly higher than that from the equivalent-body tests and area-rule theory throughout the Mach number range. Results regarding total drag and pressure drag are provided.
Date: September 25, 1957
Creator: Hoffman, Sherwood
Partner: UNT Libraries Government Documents Department

Cultural Impact on the WASPs and Night Witches

Description: Poster presentation for the 2012 University Scholars Day at the University of North Texas discussing research on cultural myths surrounding U.S. female military pilots the the effect of the Soviet Union on their development.
Date: April 19, 2012
Creator: Crossley, Kristyn & Hamner, Jesse
Partner: UNT Honors College

Flight tests of two airplanes having moderately high effective dihedral and different directional stability and control characteristics

Description: Report presenting flight tests of a twin-engine midwing attack bomber and a single-engine low-wing fighter, which indicate that both have moderately high effective dihedral but different directional stability and control characteristics. The pilots had a harder time controlling the fighter airplane, while the attack bomber was found to have a higher degree of directional stability and low directional trim forces, which the pilots preferred.
Date: October 1945
Creator: Sjoberg, S. A.
Partner: UNT Libraries Government Documents Department