Resource Type
Serial/Series Title
Atomic Energy Commission Reports
311
NACA Research Memorandums
115
AEC research and development report
89
Hanford Works Reports
71
HW (Series)
58
NACA Technical Reports
46
North American Aviation Reports
45
Health and Safety Laboratory Reports
42
General Electric Company Atomic Power Reports
41
TID
41
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731 Matching Results
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A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane, Ted No. NACA DE 390
Report presenting an investigation of the aerodynamic characteristics of a model of the Grumman F9F-9 airplane in the transonic tunnel. Results regarding the transonic drag-rise increment, drag analysis, and effective downwash angle are provided.
Date:
October 1, 1954
Creator:
Bielat, Ralph P.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Measurement of Static Forces on Internally Carried Bombs of Two Different Bluff Shapes in the Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.6
Report discussing the influence of forces and moments on a fighter-bomber airplane with an open bomb bay and on two bluff bomb shapes in various positions below the fuselage and plane of symmetry. The wing was found to have a noticeable effect on bomb forces and that bluff bombs affect the longitudinal characteristics of the wing-fuselage combination.
Date:
April 1, 1957
Creator:
Geier, Douglas J. & Robins, A. Warner
Object Type:
Report
System:
The UNT Digital Library
A Comparison of the Maneuvering Performance of a Monowing Versus a Cruciform Missile
Memorandum presenting an assessment of the importance of the addition lag of the monowing versus a cruciform shape on a missile.
Date:
June 1, 1955
Creator:
Matthews, Howard F. & Schmidt, Stanley F.
Object Type:
Report
System:
The UNT Digital Library
First Landing of Bell X-2 Research Airplane
Report presenting testing regarding the Bell X-2 supersonic research airplane, which is equipped with a skid main landing gear and nose wheel, to determine the low-speed handling qualities and landing characteristics. Results regarding the landing approach pattern, time histories, and final resting position of the airplane at landing are provided.
Date:
October 1, 1952
Creator:
Day, Richard E. & Stillwell, Wendell H.
Object Type:
Report
System:
The UNT Digital Library
NACA Conference on Aerodynamics of High Speed Aircraft
"This document contains reproductions of technical papers presented by staff members of the NACA Laboratories at the NACA Conference on Aerodynamics of High-Speed Aircraft held at the Langley Aeronautical Laboratory November 1, 2, and 3, 1955. The primary purpose of the conference was to convey to contractors of the military services and others concerned with the design of aircraft the results of recent research and to provide those attending with an opportunity to discuss these results. The papers in this document are in the same form in which they were orally presented at the conference to facilitate their prompt distribution" (p. vii).
Date:
1955-11-01/1955-11-03
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Fuel investigation in a tubular-type combustor of a turbojet engine
A series of 11 fuels ranging in volatility and including various types of hydrocarbons were tested in a single tubular combustion chamber of a turbojet engine under inlet-air conditions simulating engine operation at two speeds at an altitude of 40,000 feet. Temperature-rise data at various fuel-air ratios were obtained for each set of air-flow conditions. Results regarding the effect of combustor inlet-air conditions on temperature rise, four different series of tests, and a review of some general considerations are provided.
Date:
August 1, 1947
Creator:
Tischler, Adelbert O. & Dittrich, Ralph T.
Object Type:
Report
System:
The UNT Digital Library
An empirically derived method for calculating pressure distribution at supercritical Mach numbers and moderate angles of attack
Report presenting a procedure for calculating pressure distributions over airfoils at supercritical Mach numbers. Only the forward portion of the airfoil, where interaction between local boundary-layer thickness and local-pressure distribution is negligible, is considered in detail. The method cannot be considered definitive because it requires that certain characteristics regarding pressure distributions and geometric properties be known.
Date:
April 1, 1947
Creator:
Nitzberg, Gerald E. & Sluder, Loma E.
Object Type:
Report
System:
The UNT Digital Library
Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge
Report presenting a preliminary theoretical and experimental investigation of the supersonic characteristics of blunt-trailing-edge airfoils. Results regarding the drag measurements at zero lift, measurements at angle of attack, and a general discussion of the theoretical and experimental results is provided.
Date:
November 1, 1949
Creator:
Chapman, Dean R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Report discussing a wing-alone and wing-fuselage configuration with particular characteristics as part of a series of tests of wings using the transonic-bump test technique. Lift, drag, pitching moment, and root bending moment were obtained for the configurations. The effective downwash angles and dynamic-pressure characteristics in the tail region are also described.
Date:
November 1, 1949
Creator:
Goodson, Kenneth W. & Few, Albert G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
Report presenting an investigation of the effect of two wing sections and a tip tank on the aerodynamic characteristics of a rigid unswept wing in the high-speed tunnel over a Mach number range of 0.60 to 0.90. Results regarding the effect of original airfoil sections, effect of modifications to Section B, effect of tip tank, and characteristics of the tip tank in the presence of the wing are provided.
Date:
December 1, 1949
Creator:
Silvers, H. Norman & Spreeman, Kenneth P.
Object Type:
Report
System:
The UNT Digital Library
Investigation of downwash and wake characteristics at a Mach number of 1.53 1: rectangular wing
The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made.
Date:
March 1, 1949
Creator:
Perkins, Edward W. & Canning, Thomas N.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Internal Regenerative Fuel-Heating System for 20-Inch Ram Jet
Memorandum presenting an investigation conducted to evaluate the effectiveness of a simple internal regenerative fuel preheater for a 20-inch-diameter ram jet. Data obtained at subsonic sea-level conditions indicated that fuel could be successfully preheated in this manner.
Date:
September 1, 1949
Creator:
Baker, Sol & Perchonok, Eugene
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of rim cracking in disks subjected to high temperature gradients
Report presenting the results of an experimental investigation of rim cracking in a welded-blade composite gas-turbine wheel, in two carbon-steel disks, and five tool-steel disks. Various characteristics were investigated, including the effectiveness of holes in preventing crack propagation and the influence of hardness and various types of notch on rim cracking.
Date:
September 1, 1949
Creator:
Wilterdink, P. I.
Object Type:
Report
System:
The UNT Digital Library
An Experimental Investigation at Large Scale of Single and Twin Naca Submerged Side Intakes at Several Angles of Sideslip
Report presenting the results of an experimental investigation to determine the pressure-recovery and mass-flow characteristics of single and twin NACA submerged intakes on the sides of a fuselage at various angles of sideslip. Tests were conducted with single and twin submerged intakes on a model of a fighter-type airplane.
Date:
August 1, 1949
Creator:
Martin, Norman J. & Holzhauser, Curt A.
Object Type:
Report
System:
The UNT Digital Library
Elevator-stabilizer effectiveness and trim of the X-1 airplane to a Mach number of 1.06
Report presenting measurements of elevator-stabilizer effectiveness and trim of the X-1 airplane at 40,000 feet altitude at a range of Mach numbers and normal-force coefficients.
Date:
November 1, 1950
Creator:
Drake, Hubert M. & Carden, John R.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Longitudinal Characteristics of the X-3 Configuration Using Rocket-Propelled Models: Preliminary Results at Mach Numbers From 0.65 to 1.25
Report presenting a rocket-powered model of the X-3 configuration flown through a range of Mach numbers to determine the response of the model to rapid deflections of the horizontal tail and its effects on lift, drag, longitudinal stability and control, and longitudinal-trim change. The model was found to remain statically and dynamically stable through the lift-coefficient and Mach number range of the test.
Date:
December 1, 1950
Creator:
Mitchell, Jesse L. & Peck, Robert F.
Object Type:
Report
System:
The UNT Digital Library
Performance of J35-A-23 Compressor 1: Over-All Performance Characteristics at Equivalent Speeds From 20 to 100 Percent of Design
Report presenting an investigation of the overall performance of the J35-A-23 compressor, which is a 16-stage compressor designed to produce a total-pressure ratio of 8.75 at an equivalent flow of 155 pounds per second and an equivalent speed of 6100 rpm. Tests were run at a range of flows and speeds. Notes on installation and characteristics of the compressor are also provided.
Date:
October 1, 1951
Creator:
Medeiros, Arthur A.; Guentert, Donald C. & Hatch, James E.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation of the delay of turbulent flow separation by means of wedge-shaped bodies
Report presenting an experimental investigation of pyramidal, wedge-like bodies as devices for delaying separation of a turbulent boundary layer. Within certain limits, effective boundary-layer control was obtainable with wedges of different geometry, but the drag of the wedges was high, making it desirable to keep their size to a minimum. Greater maximum lift was obtainable by placing the wedges well forward along the chord and by allowing open spaces between adjacent wedges.
Date:
March 1, 1951
Creator:
McCullough, George B.; Nitzberg, Gerald E. & Kelly, John A.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0008-63 section
Report presenting an investigation of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0008-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 1, 1951
Creator:
Smith, Donald W. & Heitmeyer, John C.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0005-63 section
Report presenting a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0005-63 sections in streamwise planes has been investigated at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 1, 1951
Creator:
Smith, Donald W. & Heitmeyer, John C.
Object Type:
Report
System:
The UNT Digital Library
Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a partial-span aileron on an inversely tapered sweptback wing
Report presenting an investigation of the rolling effectiveness at transonic and supersonic speeds of an inversely tapered sweptback wing with a 10-percent-thick cambered airfoil section and outboard partial-span controls made by means of rocket-propelled test vehicles.
Date:
May 1, 1950
Creator:
Strass, H. Kurt; Fields, E. M. & Schult, E. D.
Object Type:
Report
System:
The UNT Digital Library
Large-scale flight measurements of zero-lift drag at Mach numbers form 0.86 to 1.5 of a wing-body combination having a 60 degree triangular wing with NACA 65A003 sections
Report presenting flight testing at high-subsonic and supersonic speeds at high Reynolds numbers to determine the zero-lift drag of a fin-stabilized body and a wing-body combination. The body was parabolic in profile, had a fineness ratio of 10, and a ratio of body frontal area to wing area to 0.306.
Date:
June 1, 1950
Creator:
Nelson, Robert L.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Operating Pressure Ratio of a Supersonic Wind Tunnel Utilizing Distributed Boundary-Layer Suction in Test Section
Effect of distributed boundary-layer suction on operating pressure ratio of a supersonic wind tunnel was investigated. Investigation was made in 3.84- by 10-inch supersonic tunnel operating at Mach number 2.0 and suction was applied in neighborhood of the normal shock to two walls of a constant-area extension of test section. A reduction of 4 percent of operating pressure ratio was attributed to improved flow conditions at subsonic-diffuser inlet. The theoretical normal shock was, in practice, replaced by a multiple-branch shock configuration across which the flow parameters changed in approximate accordance with the Rankine-Hugoniot values.
Date:
November 1, 1950
Creator:
Cohen, C. B. & Valerino, A. S.
Object Type:
Report
System:
The UNT Digital Library
Experimental damping in pitch of 45 degree triangular wings
Report presenting the results of an experimental wind-tunnel investigation of the damping in pitch of two triangular wings having leading edges swept back 45 degrees are presented. The wings differed only in airfoil section. Results regarding the damping coefficients, aeroelastic effects at supersonic speeds, Reynolds number effects, and application of the results to the prediction of the dynamic behavior of full-scale aircraft are provided.
Date:
December 1, 1950
Creator:
Tobak, Murray; Reese, David E., Jr. & Beam, Benjamin H.
Object Type:
Report
System:
The UNT Digital Library