UNT Libraries Government Documents Department - 19 Matching Results

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Determination of vortex paths by series expansion technique with application to cruciform wings

Description: A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 degrees comparison is made with the results of a closed expression given in NACA-TN-2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory ag… more
Date: February 8, 1956
Creator: Alksne, Alberta Y.
Item Type: Refine your search to only Report
open access

Sites of Azaserine Inhibition During Photosynthesis byScenedesmus

Description: The success attending the use of azaserine as a specific inhibitor of one atage in the metabolic pathway leading to the synthesis of inosinic acid in pigeon liver prompted us to use this antibiotic in a similar attack on purine synthesis in Scenedesmus. However, investigation of the products produced during photosynthesis by suspensions of these algae in the presence of azaserine showed that a more widespread interference with metabolism had occurred. The purpose of this communication is to des… more
Date: May 8, 1956
Creator: Barker, S. Alan; Bassham, James A.; Calvin, M. & Quarck, Ursula C.
Item Type: Refine your search to only Report
open access

Application and Operation of the 325 Building Well Counter

Description: Well-type scintillation counters have found use in many radiochemical laboratories. A gamma scintillation well counter has been used to measure the gamma activity of liquid samples in the 325 Building counting room for about a year. This well counter has been built and calibrated so that gamma activity measurements made with it can be easily compared with measurements made with the gamma scintillation counter (GSC). The well counter is electronically identical to the present GSC and differs onl… more
Date: March 8, 1956
Creator: Brauer, F. P.
Item Type: Refine your search to only Report
open access

A free-flight investigation of the effects of a sonic jet on the total-drag and base-pressure coefficients of a boattail body of revolution from Mach number 0.83 to 1.70

Description: Report presenting flight testing of two 7.5 degree boattail bodies of revolution with constant base annuli and varying jet static-pressure ratios and simulated turbojet exhaust rocket motors in order to determine the jet interference effects on total-drag and base-pressure coefficients over a range of Mach numbers. Results regarding the total drag and base-pressure and base-drag coefficients are provided.
Date: March 8, 1956
Creator: Falanga, Ralph A.
Item Type: Refine your search to only Report
open access

Performance of Inconel 739 Buckets in J33-9 Turbojet Engine

Description: Investigation of the performance of Inconel 739 (a nickel-base alloy of low critical-element content) buckets in a J33-9 engine showed that Inconel 739 had an engine life at least equivalent if not superior to S-816 buckets operated at 1500 degrees F. Inconel 739 buckets had a small scatter in life and exhibited lower total elongation than S-816. Bucket life was less than that predicted on; the basis of stress-rupture considerations alone. The failure mechanism was probably influenced by fatigu… more
Date: October 8, 1956
Creator: Gyorgak, C. A. & Johnston, J. R.
Item Type: Refine your search to only Report
open access

Wind Tunnel Investigation at High Subsonic Speeds of Drag at 0 Degrees Angle of Attack of Swept-Wing Fuselage Models With Pylon Mounted and Semisubmerged Missiles

Description: Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date: October 8, 1956
Creator: King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

An Investigation of the Release Characteristics of a 1/30 Dynamically Scaled AVCO Booster Vehicle from the Simulated Bomb Bay of the B-52 Airplane : COORD. No. AF-AM-59

Description: Memorandum presenting an investigation conducted in the 27- by 27-inch preflight jet of the release characteristics of a dynamically scaled AVCO booster vehicle, internally carried store model from a scale simulated bomb bay of the B-52 airplane at Mach numbers of 0.64 and 0.93. Simulated altitudes were -11,800 feet and 50,000 feet. Successful releases were obtained at all Mach numbers and simulated altitudes of the test.
Date: October 8, 1956
Creator: Lee, John B.
Item Type: Refine your search to only Report
open access

A simulation study of a wingless missile

Description: Report presenting a preliminary study to determine the possibility of utilizing a wingless configuration as a guided missile. The results indicated that the maximum trimmed lift coefficient developed by the wingless missile was somewhat smaller than that of the winged missile at a Mach number of 2.4.
Date: February 8, 1956
Creator: Lessing, Henry C. & Reese, David E., Jr.
Item Type: Refine your search to only Report
open access

Longitudinal Stability Investigation for a Mach Number Range of 0.8 to 1.7 of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail

Description: Report presenting an investigation of an airplane configuration model with a 45 degree swept wing of aspect ratio 4.0 and a taper ratio 0.3 with a low swept horizontal tail to determine its longitudinal stability. Longitudinal aerodynamic coefficients and stability derivatives are presented as functions of Mach number over the test range. The results are compared to wind tunnel and rocket model data and generally show good agreement.
Date: February 8, 1956
Creator: McFall, John C., Jr.
Item Type: Refine your search to only Report
open access

Analysis of turbojet-engine controls for afterburning starting

Description: From Introduction: "The object of this report is to investigate the effects of after-burner lighting on the engine behavior and control-system requirements of a controlled turbojet engine. In this report, a simulation procedure for the afterburner is developed (based on ref. 3), this afterburner simulation is coordinated with previously developed nonafterburning-engine simulation procedures (ref. 4), and the compensated interacting control systems of references 1 and 2 are used. The results of … more
Date: October 8, 1956
Creator: Phillips, W. E., Jr.
Item Type: Refine your search to only Report
open access

Technical Information for Application of Differential Pressure Transmitters in Pulse Column Bottom Interface Control Systems

Description: The information in this report is based on experience with a similar unit installed on experimental pule columns in the 321 Building. These installations were made to demonstrate the feasibility of the system. In one case, the installation on the 2A Prototype Column, the differential pressure cell (D/P cell) bottom interface control system was monitored by a capacitance-type instrument. The other installations were made on glass columns and were monitored visually.
Date: October 8, 1956
Creator: Smith, A. E.
Item Type: Refine your search to only Report
open access

The origin and distribution of supersonic interference from measurement of individual forces on several wing-fuselage-store configurations 6: swept-wing heavy-bomber configuration with stores of different sizes and shapes

Description: Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. The separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. Results regarding drag, lift, pitching moment, side force, and yawing moment are provided.
Date: March 8, 1956
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
open access

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference performed in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a heavy-bomber airplane with stores of several shapes and sizes.
Date: March 8, 1956
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Transonic Speeds of a Jet Control on a 35 Degree Swept Wing: Transonic-Bump Method

Description: Report presenting an investigation in the high-speed tunnel using the transonic-bump method to determine the characteristics of a jet control consisting of numerous holes located at the 65-percent chord line of a 35 degree swept semispan wing with an NACA 65A006 airfoil section. Testing occurred over a range of Mach numbers, angles of attack, and ejection-pressure ratios. Results regarding rolling-moment coefficients and aerodynamic characteristics in pitch are provided.
Date: February 8, 1956
Creator: Vogler, Raymond D. & Turner, Thomas R.
Item Type: Refine your search to only Report
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