89 Matching Results

Search Results

Newsmap. Monday, October 5, 1942 : week of September 25 to October 2

Description: Front: Text describes action on various war fronts: Russia, New Guinea, Solomons, Aleutians, China, Madagascar, Shipping, Mediterranean. Large world map is keyed to text and illustrates time zones around the world. Inset maps show South Russia, New Guinea, Target in Europe with inset of Industrial areas bombed in the Ruhr Valley. Includes photographs: WAFS report for duty, Armored "super jeep", South of Bengazi, Tank landing, "Guiding plane back home to roost". Back: Training (Action! -- Solomons -- Landing operations -- Europe). 21 photographs accompanied by descriptive and explanatory text.
Date: October 5, 1942
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, April 5, 1943 : week of March 26 to April 2, 186th week of the war, 68th week of U.S. participation

Description: Front: Text describes action on various war fronts: Tunisia, Russia, Southwest Pacific, Air offensive, Aleutians. Large world map is keyed to text and illustrates time zones around the world. Inset map shows Tunisia. Includes photographs: troops receiving daily news summaries, bombers in flight, M-10 tank destroyers, and a German Mark VI. Back: British Aircraft. 19 aircraft are identified by sketch or photograph. Text provides description of each.
Date: April 5, 1943
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Newsmap. Monday, July 5, 1943 : week of June 24 to July 1, 199th week of the war, 81st week of U.S. participation

Description: Front: Text describes action on various war fronts: Army Air Forces. HQ. Air Adjutant General. Publication Division. Maps: [Military action throughout Europe, northern Tunisia and Libya]; Area[s] controlled by Japanese [New Guinea and the Solomon Islands]. Drawing: Low-level strafing attack by a flight of twin-engined DB-3A medium bombers. Photographs: Airfield on Adak, Aleutian Islands; Navy Ventura bomber warms up on landing strip; Parachute bombs at Salamaua. Back: Drawings and text describe survival tactics for those who must abandon ship.
Date: July 5, 1943
Creator: [United States.] Army Orientation Course.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 282nd week of the war, 164th week of U.S. participation

Description: Front: Text describes action on various war fronts: Americans drive toward Manila; Allied aircraft active in Pacific; Red Army on road to Berlin; Allies erase German bulge. Maps: Objective Manila; Pacific action; West to Berlin; East to Berlin. Inset map of Berlin. Back: Text and 6 photographs highlight the activities of the Army Postal Service that delivers an average of 40 million piece of mail a week.
Date: February 5, 1945
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 286th week of the war, 168th week of U.S. participation

Description: Front: Text describes action on various war fronts: U.S. Troops Cross Roer in New Drives; Tokyo Smashed Again - Manila Falls. Maps: Drives into Germany -- Volcano Islands -- Iwo. Back: Text highlights what the Army is doing to help the folks back home and suggests ways service people and families can work with the Office of Dependency Benefits to ensure prompt payments.
Date: March 5, 1945
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department

Newsmap. For the Armed Forces. 247th week of the war, 129th week of U.S. participation

Description: Front: Text describes action on various war fronts: Italy, Western Europe, USSR, Pacific, Southeast Asia, China. Maps: Approach to Rome; northern New Guinea. Includes photographs: U.S. Navy plane on patrol duty; American jeep passes by a disabled German self-propelled 88mm. gun in the Spigno area; Ensign R. Black, Navy hellcat pilot of Brigham, Utah exits from his shattered plane. Back: Air commandos. Text and 8 photographs tell the story of air commandos in Asia.
Date: June 5, 1944
Creator: [United States.] Army Service Forces. Army Information Branch.
Partner: UNT Libraries Government Documents Department

NACA Conference on Aerodynamic Problems of Transonic Airplane Design

Description: Compilation of the papers presented at a NACA conference on transonic airplane design, including stability and control and configurations with extreme sweep. From Introduction: "The purpose of this conference was to convey to those involved in the study of the aerodynamic problems of transonic aircraft these recent research results and to provide those attending an opportunity for discussion of the results."
Date: 1947-11-05/1947-11-06
Partner: UNT Libraries Government Documents Department

An experimental investigation of NACA submerged air inlets on a 1/5-scale model of a fighter airplane

Description: From Summary: "The results of an experimental investigation of an NACA submerged-air-inlet system on a 1/5-scale model of a fighter airplane are presented. Preliminary development tests were conducted to select the optimum entrance configuration. Duct-system total-pressure losses and pressure distributions over the lip and ramp of this air intake were obtained."
Date: December 5, 1947
Creator: Gault, Donald E.
Partner: UNT Libraries Government Documents Department

Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body

Description: Report presenting an approximate method for calculating the interference pressure distribution at zero lift of a symmetrical sweptback wing mounted on a circular cylindrical body with the chord plane of the wing passing through the axis of the body. An example is provided using a circular cylindrical body and an untapered wing with 60 degrees of sweepback.
Date: August 5, 1949
Creator: Nielsen, Jack N. & Matteson, Frederick H.
Partner: UNT Libraries Government Documents Department

Flight investigation of the heat requirements for ice prevention on aircraft windshields

Description: Report presenting a flight investigation conducted to establish the heat requirements for ice prevention on aircraft windshields mounted on the forebody of an airplane at several angles. Electrically heated windshields were used in order to provide accurate measuring of heat input to the windshield. Results regarding the quantity of heat provided, amount of water collection, ideal windshield angle, ranges in airplane velocity, and icing conditions are provided.
Date: September 5, 1947
Creator: Kleinknecht, Kenneth S.
Partner: UNT Libraries Government Documents Department

Precautions for Flight Testing Near the Speed of Sound

Description: From experience gained by NACA test pilots in flying at high subsonic Mach numbers and from interpretation of the data obtained, some general precautionary rules for test flying near sonic Mach numbers have been formulated. The reasons for these rules are discussed and observations are made with respect to the hazards arising from undesirable stability and control characteristics which have been noted in test flights of various airplanes. This paper, although written primarily for the attention of test pilots, contains general information of interest to those who are concerned with various phases of flight testing near sonic Mach numbers.
Date: November 5, 1947
Creator: Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Control Effectiveness and Hinge-Moment Characteristics of a Tip Control Surface on a Low-Aspect-Ratio Pointed Wing at a Mach Number of 1.9

Description: Report presenting a wind-tunnel investigation of a semispan pointed wing of aspect ratio 1.7 with 60 degree leading-edge sweepback and 30 degree trailing-edge sweepforward with a control surface. The purpose of the investigation was to determine the effectiveness of flap-type controls at transonic and supersonic speeds. Results regarding the wing characteristics and control-surface characteristics are provided.
Date: October 5, 1949
Creator: Conner, D. William & May, Ellery B., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Effects at Subsonic Speeds of a Constant-Chord Elevon on a Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25

Description: Report presenting testing of a cambered and twisted wing with constant-chord elevons with a slender fuselage to determine the longitudinal and lateral control from the elevons for a range of Mach numbers. Results regarding lift, drag, pitching-moment, and rolling-moment characteristics for various elevon deflections are provided.
Date: December 5, 1949
Creator: Jones, J. Lloyd & Demele, Fred A.
Partner: UNT Libraries Government Documents Department

Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method

Description: Report presenting measurements using the NACA wing-flow method of the lift, pitching-moment, and hinge-moment characteristics of a 35 degree sweptback NACA 65-009 airfoil of aspect ratio 3.04 with a full-span 1/4-chord unsealed plain flap. The tests were carried out at a range of Mach numbers, Reynolds numbers, angles of attack, and flap deflections. Variations of lift and pitching moment with angle of attack or flap deflection were approximately rectilinear at all Mach numbers for moderate angles of attack and flap deflections.
Date: August 5, 1947
Creator: Johnson, Harold I.
Partner: UNT Libraries Government Documents Department

High Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 1/16-Scale Model of the D-558-2 Research Airplane at High Subsonic Mach Number and at a Mach Number of 1.2

Description: Report presenting the results of lift, drag, and pitching-moment measurements on a model of the Douglas D-558-2 airplane at a range of angles of attack and Mach numbers. The model was also tested with two different sets of chordwise fences in order to investigate their effects on force and moment characteristics at high speeds.
Date: April 5, 1949
Creator: Osborne, Robert S.
Partner: UNT Libraries Government Documents Department

Initial Test in the Transonic Range of Four Flutter Airfoils Attached to a Freely Falling Body

Description: Report presenting the results of testing in the transonic range of four flutter airfoils attached to a freely falling body. Failures of the airfoils were metered and recorded in order to determine the Mach numbers and altitudes of failure.
Date: May 5, 1947
Creator: Barmby, J. G. & Clevenson, S. A.
Partner: UNT Libraries Government Documents Department

Pressure distribution over a sharp-nose body of revolution at transonic speeds by the NACA wing-flow method

Description: Report presenting an investigation to obtain the pressure distribution over a sharp-nose body of revolution with a circular-arc profile and fineness ratio 6 at transonic speeds using the NACA wing-flow method. Results regarding the variation of pressure coefficient with Mach number, pressure distributions along the body axis, pressure drag, and effects of interference and horizontal gradient are provided.
Date: March 5, 1948
Creator: Danforth, Edward C. B. & Johnston, J. Ford
Partner: UNT Libraries Government Documents Department

An Approximate Method of Calculation of Relative Humidity Required to Prevent Frosting on Inside of Aircraft Pressure Cabin Windows, Special Report

Description: This report has been prepare in response to a request for information from an aircraft company. A typical example was selected for the presentation of an approximate method of calculation of the relative humidity required to prevent frosting on the inside of a plastic window in a pressure type cabin on a high speed airplane. The results of the study are reviewed.
Date: December 5, 1940
Creator: Jones, Alun R.
Partner: UNT Libraries Government Documents Department

Relation between spark-ignition engine knock, detonation waves, and autoignition as shown by high-speed photography

Description: "A critical review of literature bearing on the autoignition and detonation-wave theories of spark-ignition engine knock and on the nature of gas vibrations associated with combustion and knock results in the conclusion that neither the autoignition theory nor the detonation-wave theory is an adequate explanation of spark-ignition engine knock. A knock theory is proposed, combining the autoignition and detonation-wave theories, which introduces the idea that the detonation wave develops in autoignited or after-burning gases, and ascribes comparatively low-pitched heavy knocks to autoignition but high-pitched pinging knocks to detonation waves with the possibility of combinations of the two types of knocks" (p. 317).
Date: December 5, 1945
Creator: Miller, Cearcy D.
Partner: UNT Libraries Government Documents Department

Two-dimensional unsteady lift problems in supersonic flight

Description: The variation of pressure distribution is calculated for a two-dimensional supersonic airfoil either experiencing a sudden angle-of-attack change or entering a sharp-edge gust. From these pressure distributions the indicial lift functions applicable to unsteady lift problems are determined for two cases. Results are presented which permit the determination of maximum increment in lift coefficient attained by an unrestrained airfoil during its flight through a gust. As an application of these results, the minimum altitude for safe flight through a specific gust is calculated for a particular supersonic wing of given strength and wing loading.
Date: December 5, 1947
Creator: Heaslet, Max A. & Lomax, Harvard
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Performance Characteristics with the High-Flow Compressor

Description: A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-flow turbojet engine with a high flow compressor. Pressure altitudes included 5000 to 40000 feet with ram pressure ratios from 1.00 to 1.82. Altitudes included 20000 to 40000 feet and ram pressure ratios from 1.09 to 1.75. A comparison is made between engine performance with high flow and low flow compressors.
Date: August 5, 1948
Creator: Fleming, William A. & Golladay, Richard L.
Partner: UNT Libraries Government Documents Department

Laminar mixing of a compressible fluid

Description: From Summary: "A theoretical investigation of the velocity profiles for laminar mixing of a high-velocity stream with a region of fluid at rest has been made assuming that the Prandtl number is unity. A method which involves only quadratures is presented for calculating the velocity profile in the mixing layer for an arbitrary value of the free-stream Mach number. Detailed velocity profiles have been calculated for free-stream Mach numbers of 0, 1, 2, 3, and 5."
Date: January 5, 1949
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department