Resource Type
Serial/Series Title
NACA Research Memorandums
141
Atomic Energy Commission Reports
35
Hanford Works Reports
17
HW (Series)
14
Oak Ridge National Laboratory Reports
14
University of California Radiation Laboratory Reports
11
NACA Technical Reports
8
ORNL (Series)
7
AEC research and development report
5
AECU (Series)
5
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230 Matching Results
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Free-Spinning Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane
Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel on a 1/20-scale model of the McDonnell F2H-3 airplane. The effects of control settings and movement on the erect spin and recovery characteristics of the model were determined for the take-off condition and for the condition with full wing-tip fuel tanks installed.
Date:
July 24, 1951
Creator:
Wilson, Jack H.
Object Type:
Report
System:
The UNT Digital Library
The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained From a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds
A 60 degree delta wing canard missile configuration was flight-tested at the Langley pilotless aircraft research station at Wallops Island, Va. The results include the longitudinal stability derivatives, control effectiveness, drag characteristics, and control-surface hinge-moment characteristics for a Mach number range of 0.7 to 1.45.
Date:
November 24, 1950
Creator:
Niewald, Roy J. & Moul, Martin T.
Object Type:
Report
System:
The UNT Digital Library
The effects of camber and twist on the aerodynamic loading and stalling characteristics of a large-scale 45 degree swept-back wing
Report presenting pressure-distribution measurements on two large-scale semispan wing-fuselage models with 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and 10-percent-thick sections normal to the quarter-chord line. Adding camber and twist to a wing significantly improved the upper surface loading of the wing at a lift coefficient of 0.4 through a reduction in the peak negative pressure coefficient. Results regarding loading characteristics and stalling characteristics are provided.
Date:
January 24, 1951
Creator:
Hunton, Lynn W. & Dew, Joseph K.
Object Type:
Report
System:
The UNT Digital Library
Secondary Flows in Annular Cascades and Effects on Flow in Inlet Guide Vanes
Qualitative discussion is presented of the general nature of secondary flows in stationary annular cascades with thin wall boundary layers and radial design variation of circulation. Deviations from ideal mean outlet flows (based on blade-element performance) exist in potential-flow region of vanes because of conditions imposed by end-wall boundaries, displacement of wall boundary layers toward blade suction surfaces, and irrotationality requirement. As a consequence of existence of nonuniform radial flow across blade spacing, it may not generally be possible to obtain an arbitrarily specified design variation of the turning angle along the radial height of a blade row.
Date:
August 24, 1951
Creator:
Lieblein, Seymour & Ackley, Richard H.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Solidity on Turning Through Constant-Thickness Circular-Arc Guide Vanes in Axial Annular Flow
Memorandum presenting an investigation conducted on sheet metal, circular-arc compressor inlet guide vanes in an annular cascade with untapered walls to determine the effect of solidity on turning through a blade row. Guide vanes of 30 and 40 degrees camber were investigated over a range of solidity from 0.5 to 4.0. Results regarding the effect of solidity on turning angle, comparison with two-dimensional methods, application of results, and total-pressure losses are provided.
Date:
August 24, 1951
Creator:
Mankuta, Harry & Guentert, Donald C.
Object Type:
Report
System:
The UNT Digital Library
An experimental investigation of boundary interference on force and moment characteristics of lifting models in the Langley 16- and 8-foot transonic tunnels
Report presenting testing of a wing-fuselage force model configuration and the fuselage alone at angles of attack up to 32 degrees in the 16-foot transonic tunnel. Results regarding the force and moment characteristics, base pressures, and shadowgraph pictures are provided.
Date:
February 24, 1953
Creator:
Whitcomb, Charles F. & Osborne, Robert S.
Object Type:
Report
System:
The UNT Digital Library
Buffeting of a vertical tail on an inclined body at supersonic Mach numbers
Report presenting time histories of rolling and yawing moments on inclined bodies of revolution with vertical-tail surfaces at several Mach numbers and Reynolds numbers. Three ogival-nose bodies with three overall fineness ratios and a conical-nosed body with a fineness ratio of 12.0 were tested. Results regarding the visual-flow studies, rolling- and yawing-moment measurements, and pressure measurements are provided.
Date:
March 24, 1953
Creator:
Gowen, Forrest E.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of the Flow Field Behind an Aspect-Ratio-10 Hydrofoil Near the Water Surface
Report presenting an investigation of the flow field behind a hydrofoil with an 8-inch chord and an aspect ratio of 10; the foil was operating at about 0.75 chord below the free-water surface. The downwash and water surface profiles were measured behind the hydrofoil for a variety of positions of interest. Results regarding surface contours, a comparison of surface profiles with theoretical two-dimensional waves, and downwash are presented.
Date:
February 24, 1953
Creator:
Carter, Arthur W. & Butler, Roger V.
Object Type:
Report
System:
The UNT Digital Library
Performance Characteristics of a Double-Cylindrical-Shroud Ejector Nozzle
Memorandum presenting an investigation of the performance characteristics of a double-shroud ejector for the purpose of evaluating its effectiveness as an exit nozzle. Calculations based on ejector performance data, taken with the ejector discharging into quiescent air, indicate that thrust performance on the order of ideal nozzle thrust may be obtained over a Mach number range of 0.8 to 2.3 from a double-shroud ejector. The results of a simplified theoretical analysis are in fair agreement with those experimentally obtained.
Date:
November 24, 1953
Creator:
Reshotko, Eli
Object Type:
Report
System:
The UNT Digital Library
Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-Inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93
Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.
Date:
June 24, 1954
Creator:
Grigsby, Carl E.
Object Type:
Report
System:
The UNT Digital Library
The Use of the Rolled-Up Vortex Concept for Predicting Wing-Tail Interference and Comparison With Experiment at Mach Number of 1.62 for a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces
Report presenting a method for predicting wing-tail interference as applied to the calculation of tail efficiency parameters, lift characteristics, and center-of-pressure locations for a series of generalized missile configurations. The calculations are also compared to experimental data. The rolled-up vortex concept appears to give good results in the prediction of tail efficiency with angle of attack for inline configurations.
Date:
September 24, 1952
Creator:
Grigsby, Carl E.
Object Type:
Report
System:
The UNT Digital Library
Axial-Slot Air Admission for Controlling Performance of a One-Quarter-Annual Turbojet Combustor and Comparison With Complete Engine
"An investigation of a single-annulus turbojet combustor with slot-type air admission was conducted to demonstrate the application of certain design principles to the control of outlet-gas temperature distributions. Comparisons of performance of a one-quarter-annulus combustor (duct-type installation) and a full-annulus combustor (obtained in a full-scale turbojet engine) are presented to indicate the applicability of results obtained from combustion studies conducted in duct-type installations. A reasonable correlation existed between the performance of the one-quarter-annulus and full-annulus combustors except for temperature distribution" (p. 1).
Date:
March 24, 1952
Creator:
Mark, Herman & Zettle, Eugene V.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Aerodynamic and Icing Characteristics of a Flush Alternate-Inlet Induction-System Air Scoop
Memorandum presenting an investigation in the icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. Results regarding the ram-inlet tests, alternate-inlet tests, and preheat-air tests are provided.
Date:
July 24, 1953
Creator:
Lewis, James P.
Object Type:
Report
System:
The UNT Digital Library
Free-flight measurements of some effects of aileron span, chord, and deflection and of wing flexibility on the rolling effectiveness of ailerons on sweptback wings at Mach numbers between 0.8 and 1.6
Report presenting a free-flight investigation to determine some effects of aileron span and deflection on the rolling effectiveness of plain, sealed, 15-percent- and 30-percent-chord flap-type ailerons through a range of Mach numbers. Wings of different degrees of torsional flexibility were tested and the results were extended to estimate rigid-wing rolling-effectiveness of all aileron configurations tested.
Date:
January 24, 1952
Creator:
Schult, Eugene D.; Strass, H. Kurt & Fields, E. M.
Object Type:
Report
System:
The UNT Digital Library
Performance of an annular turbojet combustor having reduced pressure losses and using propane fuel
Report presenting an investigation to develop a high-combustion-efficiency turbojet combustor with pressure losses typical of those encountered in current turbojet engines. A total of 13 air-entry hole modifications was investigated to obtain a combustor design with high combustion efficiencies and a satisfactory outlet radial temperature profile. Results regarding combustor development and the performance of Model 28I are provided.
Date:
September 24, 1953
Creator:
Norgren, Carl T. & Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of a Modified 1/20-Scale Model of the Convair MX-1554 Airplane at Mach Numbers of 1.41 and 2.01
Report presenting an investigation of a model of the Convair MX-1554 airplane in the 4- by 4-foot supersonic pressure tunnel to evaluate the effects of extending the length of the fuselage afterbody and to provide longitudinal and lateral stability and control data. Results indicated that extension of the fuselage afterbody length caused little change in the minimum longitudinal force coefficient and drag due to lift.
Date:
August 24, 1953
Creator:
Hilton, John H., Jr. & Palazzo, Edward B.
Object Type:
Report
System:
The UNT Digital Library
Investigation of an NACA 4-(5)(05)-041 Four-Blade Propeller With Several Spinners at Mach Numbers Up to 0.90
Report presenting an investigation to determine the aerodynamic characteristics of an NACA 4-(5)(05)-041 four-blade propeller in combination with NACA 1-series and extended cylindrical spinners for a range of blade angles. Results regarding variation of propeller thrust coefficient, power coefficient, efficiency, tip Mach number, characteristics of the propeller in combination with different spinners, and maximum efficiency are provided.
Date:
December 24, 1952
Creator:
Reynolds, Robert M.; Buell, Donald A. & Walker, John H.
Object Type:
Report
System:
The UNT Digital Library
Correlation of Flight and Wind-Tunnel Measurements of Roll-Off in Low-Speed Stalls on a 35 Degree Swept-Wing Aircraft
Memorandum presenting flight and wind-tunnel measurements made of the low-speed stalling characteristics on a swept-wing jet aircraft. Included in the study are the effects on the stalling characteristics of a number of wing modifications. Results regarding the roll-off characteristics and maximum lift and stalling characteristics are provided.
Date:
September 24, 1953
Creator:
Anderson, Seth B.
Object Type:
Report
System:
The UNT Digital Library
Gust-Tunnel Investigation of the Effect of Leading Edge Separation on the Normal Accelerations Experienced by a 45 Degree Sweptback-Wing Model in Gusts
Report presenting an investigation of a 45 degree sweptback-wing model with interchangeable round and sharp leading edges to determine the effect of leading-edge separation on the loads experienced by the models in gusts. Leading-edge separation was found to increase the gust load, which appeared to vary based on the gust-gradient distance and velocity.
Date:
November 24, 1953
Creator:
Cahen, George L.
Object Type:
Report
System:
The UNT Digital Library
Free-flight-tunnel investigation of the low-speed stability and control characteristics of a model having a fuselage of relatively flat cross section
Report presenting an experimental investigation in the free-flight tunnel to determine the low-speed stability and control characteristics of a model with a fuselage of relatively flat cross section. The model was found to exhibit an erratic behavior in pitch and yaw, which appeared to be due to random trim changes associated with the flow from the forward portion of the flat fuselage. Results regarding the longitudinal stability and control characteristics and lateral stability and control characteristics are provided.
Date:
February 24, 1953
Creator:
Paulson, John W. & Johnson, Joseph L., Jr.
Object Type:
Report
System:
The UNT Digital Library
Transonic Aerodynamic and Loads Characteristics of a 4-Percent-Thick Unswept-Wing--Fuselage Combination
Report presenting an investigation in the transonic tunnel to determine the basic aerodynamic and loading characteristics of an unswept-wing-fuselage combination with a wing of aspect ratio 4, taper ratio 0.5, and NACA 65A004 airfoil sections. Force, moment, and pressure measurements were obtained for a range of Mach numbers and angles of attack.
Date:
May 24, 1954
Creator:
Hieser, Gerald; Henderson, James H. & Swihart, John M.
Object Type:
Report
System:
The UNT Digital Library
Correlation of Buffet Boundaries Predicted From Wind-Tunnel Tests With Those Measured During Flight Tests on the F8F-1 and X-1 Airplanes -Transonic-Bump Method
Memorandum presenting testing of semispan wing-fuselage models of the F8F-1 and X-1 airplanes in the 16-foot high-speed wind tunnel utilizing the transonic-bump method. The variations of lift coefficient with angle of attack and Mach number and pitching-moment coefficient with lift coefficient at various Mach numbers are presented for the models. The buffet boundaries were found to be in reasonable agreement with those determined from flight tests of full-scale airplanes.
Date:
December 24, 1952
Creator:
Martin, Andrew & Reed, James F.
Object Type:
Report
System:
The UNT Digital Library
Hinge-Moment, Lift, and Pitching-Moment Characteristics of a Flap-Type Control Surface Having Various Hinge-Line Locations on a 4-Percent-Thick 60 Degree Delta Wing: Transonic Bump Method
Report presenting an investigation in the high-speed tunnel to determine the hinge-moment, lift, and pitching-moment characteristics of a 4-percent-thick 60 degree delta wing with a trailing-edge flap-type control. The purpose of this investigation is to determine the ideal aerodynamic balance of a large part of the control force in order to make aircraft easier to control in the event of power failure.
Date:
March 24, 1954
Creator:
Thompson, Robert F.
Object Type:
Report
System:
The UNT Digital Library
Flight Tests of a Man Standing on a Platform Supported by a Teetering Rotor
Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.
Date:
March 24, 1954
Creator:
Hill, Paul R. & Kennedy, T. L.
Object Type:
Report
System:
The UNT Digital Library