Resource Type
Collection
Serial/Series Title
NACA Research Memorandums
49
Atomic Energy Commission Reports
14
NACA Technical Notes
11
United States Geological Survey Reports
7
University of California Radiation Laboratory Reports
7
Trace elements investigations report
6
Report (U.S. Atomic Energy Commission)
3
AEC research and development report
2
AECU (Series)
2
E.I. du Pont de Nemours & Company Reports
2
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States
179 Matching Results
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Health Protection in Beryllium Facilities Summary of Ten Years of Experience
From Introduction: "The purpose of this report is to summarize the information gathered during the design and operation of these facilities so that it may be used in providing for the safe handling of beryllium materials."
Date:
May 1, 1958
Creator:
Breslin, A. J. & Harris, W. B.
Object Type:
Report
System:
The UNT Digital Library
Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model
Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.
Date:
May 26, 1958
Creator:
Matthews, Clarence W.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date:
May 2, 1958
Creator:
Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel
Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
Date:
May 28, 1958
Creator:
Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.
Date:
May 20, 1958
Creator:
Gertsma, L. W. & Beheim, M. A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models cooled with lithium hydride are provided.
Date:
May 28, 1958
Creator:
Modisette, Jerry L.
Object Type:
Report
System:
The UNT Digital Library
Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives
Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date:
May 2, 1958
Creator:
Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
Object Type:
Report
System:
The UNT Digital Library
A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
"A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).
Date:
May 28, 1958
Creator:
Hall, James R. & Garland, Benjamine J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.
Date:
May 16, 1958
Creator:
Lord, Douglas R. & Czarnecki, K. R.
Object Type:
Report
System:
The UNT Digital Library
Droplet Impingement and Ingestion by Supersonic Nose Inlet in Subsonic Tunnel Conditions
"The amount of water in cloud droplet form ingested by a full-scale supersonic nose inlet with conical centerbody was measured in the NACA Lewis icing tunnel. Local and total water impingement rates on the cowl and centerbody surfaces were also obtained. All measurements were made with a dye-tracer technique" (p. 1).
Date:
May 1958
Creator:
Gelder, Thomas F.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of Extreme Internal Flow Turning at the Cowl Lip of an Axisymetric Inlet at a Mach Number of 2.95
Memorandum presenting an experimental investigation of the pressure-recovery performance of a fixed-geometry, two-cone, two-drag inlet at Mach number 2.95. Low drag was achieved by use of an internally cylindrical cowl with rapid flow turning that was within 4 degrees of the wedge angle for shock detachment. Results regarding the inlet performance and evaluation of inlet performance are provided.
Date:
May 13, 1958
Creator:
Weston, Kenneth C. & Kowalski, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter
Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.
Date:
May 8, 1958
Creator:
Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Object Type:
Report
System:
The UNT Digital Library
High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser
Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application.
Date:
May 12, 1958
Creator:
Connors, James F. & Flaherty, Richard J.
Object Type:
Report
System:
The UNT Digital Library
Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet
Memorandum presenting an investigation conducted in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results of the investigation showed that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.
Date:
May 19, 1958
Creator:
Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
Object Type:
Report
System:
The UNT Digital Library
An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control
Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date:
May 12, 1958
Creator:
Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Object Type:
Report
System:
The UNT Digital Library
A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations
Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approach speed, comparison of flight and predicted approach speeds, and comparison of test pilots' and service pilots' approach speed are provided.
Date:
May 8, 1958
Creator:
White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Object Type:
Report
System:
The UNT Digital Library
Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes
Memorandum presenting an investigation conducted to measure and compare the total-pressure recovery and distortion characteristics at the compressor face of two single-place fighter-type airplanes with similar two-spool turbojet engines, but with dissimilar inlets. The total-pressure recovery was relatively independent of angle of attack and mass-flow ratio for both airplanes except for a significant decrease in pressure recovery with angle of attack for airplane B at the highest Mach numbers tested.
Date:
May 26, 1958
Creator:
Larson, Terry J.; Thomas, George M. & Bellman, Donald R.
Object Type:
Report
System:
The UNT Digital Library
Area-Suction Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane
"A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying area-suction boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effect of boundary-layer control in the handling qualities and operation of the airplane, particularly during landing. The wind-tunnel and flight tests indicated that area suction applied to the trailing-edge flaps produced significant increases in flap lift increment" (p. 1).
Date:
May 6, 1958
Creator:
Cook, Woodrow L.; Anderson, Seth B. & Cooper, George E.
Object Type:
Report
System:
The UNT Digital Library
An approximate analytical method for studying entry into planetary atmospheres
Report presenting a single, ordinary, nonlinear differential equation of second order that can be used for determining entry into an exponential planetary atmosphere. The reduced equation includes various terms, some of which represent the gravity force, the centrifugal acceleration, and the lift force. A number of solutions for lifting and nonlifting vehicles entering at various initial angles are obtained from the complete nonlinear equation.
Date:
May 1958
Creator:
Chapman, Dean R.
Object Type:
Report
System:
The UNT Digital Library
Summary of experimental heat-transfer measurements in turbulent flow for a Mach number range from 0.87 to 5.05
Report presenting heat-transfer measurements made in turbulent flow at a variety of Mach and Reynolds numbers through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. The results are presented as Stanton number and recovery factor as a function of Reynolds number. Stanton number was found to decrease with an increase in Reynolds number and usually decreases with an increase in Mach number.
Date:
May 1958
Creator:
Brevoort, Maurice J. & Arabian, Barbara D.
Object Type:
Report
System:
The UNT Digital Library
An experimental investigation of wake effects on hydro-skis
Report presenting an experimental investigation to determine the effects of planing in a wake on the forces of a planing surface and to locate desirable positions in the wake with regard to the lift and lift-drag ratio of the planing surface. Two combinations of hydro-skis were tested: one with two in tandem and one with three arranged with one hydro-ski in the front and two in the back. Results indicated that the rear hydro-ski in tandem arrangement could have large increases in lift coefficient and small improvements in lift-drag ratio compared with the regular configuration.
Date:
May 1958
Creator:
McBride, Ellis E. & Fisher, Lloyd J.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of Effects of Retreating-Blade Stall on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade
Note presenting flight tests conducted with a medium-size single-rotor helicopter, one blade of which was equipped with strain gages, to determine the effects of retreating-blade stall on the rotor blade bending and torsional moments during high-speed flight and pull-up maneuvers. The results indicate that retreating-blade stall has a substantial effect on the periodic rotor blade moments. Results regarding the effect of stall in steady forward flight and effect of stall in pull-up maneuvers are provided.
Date:
May 1958
Creator:
Ludi, LeRoy H.
Object Type:
Report
System:
The UNT Digital Library
Study of ground-reaction forces measured during landing impacts of a large airplane
Report presenting the results of tests conducted on a large bomber-type airplane to determine the ground-reaction forces imposed on the main landing gear under actual landing conditions. The vertical force on the landing gear truck at which the oleopneumatic shock strut began to compress varied over a wide range. Results regarding vertical forces, drag forces, and side forces are provided.
Date:
May 1958
Creator:
Hall, Albert W.; Sawyer, Richard H. & McKay, James M.
Object Type:
Report
System:
The UNT Digital Library
Measurement of the Effect of an Axial Magnetic Field on the Reynolds Number of Transition in Mercury Flowing Through a Glass Tube
Note presenting experiments conducted to determine the effect of a strong axial magnetic field on the flow of mercury through a circular channel. The magnetic induction was 15,000 gauss, and the channel was a pyrex tube 17-1/4 inches long and 0.027 inch inside diameter. The results indicated that the stabilizing effect occurred only at Reynolds number above 5,000, so that the region of practical applicability seems to be at fairly high Reynolds numbers and when there are only slight disturbances in the flow.
Date:
May 1958
Creator:
Bader, Michel & Carlson, William C. A.
Object Type:
Report
System:
The UNT Digital Library