Resource Type
Serial/Series Title
NACA Research Memorandums
155
Atomic Energy Commission Reports
64
NACA Technical Reports
35
Hanford Works Reports
26
HW (Series)
20
Oak Ridge National Laboratory Reports
19
University of California Radiation Laboratory Reports
16
BNL (Series)
12
Brookhaven National Laboratory Reports
12
GJBX
9
50 More
Country
States
Decade
Month
Day
354 Matching Results
Results open in a new window/tab.
Damping in Roll of Rocket-Powered Test Vehicles Having Swept, Tapered Wings of Low Aspect Ratio
"Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the one with a 7-percent-thick circular-arc airfoil section" (p. 1).
Date:
October 8, 1951
Creator:
Sanders, E. Claude, Jr. & Edmondson, James L.
Object Type:
Report
System:
The UNT Digital Library
An analytical method for evaluating factors affecting application of transpiration cooling to gas turbine blades
From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mounted in a static cascade (references 2 and 3) where it is shown that although transpiration cooling results in extremely effective cooling in the midchord region of the blade, there are very large variations in the chordwise temperature distribution because of improper permeability variation."
Date:
September 8, 1952
Creator:
Esgar, Jack B.
Object Type:
Report
System:
The UNT Digital Library
Estimated deceleration of airplane nose section jettisoned at various altitudes and airspeeds
Memorandum presenting calculations made to determine the deceleration at any time after jettisoning of an airplane nose-section design typical of those which have been proposed as escape devices for high-speed airplanes. The decelerations were determined by two methods, one using successive approximations requiring graphical integration and the other giving reasonably close approximations by direct computation.
Date:
January 8, 1951
Creator:
Scher, Stanley H.
Object Type:
Report
System:
The UNT Digital Library
Longitudinal-control effectiveness and downwash characteristics at a Mach number of 1.24 of a 1/30-scale semispan model of the Bell X-5 airplane as determined by the NACA wing-flow method
Report presenting an investigation at a Mach number of 1.24 using the NACA wing-flow method to determine the longitudinal-control effectiveness and downwash characteristics of a scale semispan model of the variable-sweep Bell X-5 airplane with the wind swept back at several different degrees. Lift, drag, and pitching moments were obtained for various angles of attack for several horizontal tail settings and with the tail off for each angle of sweep of the wing.
Date:
January 8, 1951
Creator:
Sawyer, Richard H.; Kennedy, Robert M. & Morris, Garland J.
Object Type:
Report
System:
The UNT Digital Library
Characteristics of perforated diffusers at free-stream Mach number 1.90
"An investigation was conducted at Mach number 1.90 to determine pressure recovery and mass-flow characteristics of series of perforated convergent-divergent supersonic diffusers. Pressure recoveries as high as 96 percent were obtained, but at reduced mass flows through the diffuser. Theoretical considerations of effect of perforation distribution on shock stability in converging section of diffuser are presented and correlated with experimental data. A method of estimating relative importance of pressure recovery and mass flow on internal thrust coefficient basis is given and a comparison of various diffusers investigated is made" (p. 1).
Date:
May 8, 1950
Creator:
Hunczak, Henry R. & Kremzier, Emil J.
Object Type:
Report
System:
The UNT Digital Library
Propeller Section Aerodynamic Characteristics as Determined by Measuring the Section Surface Pressures on an NACA 10-(3)(08)-03 Propeller Under Operating Conditions
Report presenting a wind-tunnel investigation to determine propeller section aerodynamic characteristics by measuring surface pressure distribution on the airfoil sections of a rotating propeller. The pressures were measured at nine radial sections of the NACA 10-(3)(08)-03 two-blade propeller. Results regarding sectional critical Mach number, and aerodynamic coefficients are also presented.
Date:
November 8, 1950
Creator:
Evans, Albert J.
Object Type:
Report
System:
The UNT Digital Library
Free-Spinning Tunnel Tests of a 1/20-Scale Model of the McDonnell XF3H-1 Airplane : TED No. NACA DE 343
Memorandum presenting an investigation conducted in the 20-foot free-spinning tunnel with a scale model to determine the spin and recovery characteristics of the McDonnell XF3H-1 airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined. Results regarding design gross weight loading, variation of loading, spin-recovery parachutes, pilot escape, landing condition, control forces, and recommended recovery technique are provided.
Date:
September 8, 1950
Creator:
Berman, Theodore
Object Type:
Report
System:
The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation
Report presenting a study of the supersonic longitudinal stability and control characteristics of a canard missile configuration using flight tests and wind-tunnel tests at a range of Mach numbers and Reynolds numbers. Good correlation was noted for the two techniques for slopes of lift and moment coefficients against angle of attack and for aerodynamic-center location.
Date:
August 8, 1952
Creator:
Curfman, Howard J., Jr. & Grigsby, Carl E.
Object Type:
Report
System:
The UNT Digital Library
The transonic characteristics of 38 cambered rectangular wings of varying aspect ratio and thickness as determined by the transonic-bump technique
Report presenting an investigation to determine the effects of camber on the aerodynamic characteristics of a series of rectangular wings with various aspect ratios and thickness-to-chord ratios using the transonic-bump method. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching-moment characteristics are presented for wings of 5 aspect ratios, NACA 63A2XX and 63A4XX sections, and 5 thickness-to-chord ratios.
Date:
July 8, 1952
Creator:
Nelson, Warren H. & Krumm, Walter J.
Object Type:
Report
System:
The UNT Digital Library
Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method
Report presenting an investigation utilizing the transonic-bump technique through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of retractable spoiler and plug-type spoiler-slot ailerons. The wing had a sweepback of 60 degrees at the quarter-chord line, an aspect ratio of 2, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The plug-type spoiler-slot aileron was found to be more effective in producing roll than the retractable spoiler aileron through the entire range of values tested.
Date:
August 8, 1952
Creator:
Hammond, Alexander D. & Watson, James M.
Object Type:
Report
System:
The UNT Digital Library
Transonic Drag Characteristics and Pressure Distribution on the Body of a Wing-Body Combination Consisting of a Body of Revolution of Fineness Ratio 12 and a Wing Having Sweepback of 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections
Report presenting free-fall testing of the airplane configuration described in the title to evaluate certain new testing techniques for near sonic speeds. Results regarding the drag measurements and pressure data are provided. The data obtained from this test is also compared to free-fall tests in the high-speed tunnel and for a rocket-powered free-flight model, and the results show generally satisfactory agreement.
Date:
April 8, 1952
Creator:
Kurbjun, Max C. & Thompson, Jim Rogers
Object Type:
Report
System:
The UNT Digital Library
An experimental cascade study of the effects of a solidity reduction on the two-dimensional aerodynamic characteristics of a turbine-rotor blade suitable for air cooling
Report presenting an experimental two-dimensional investigation of the mechanism of the flow and losses involved in the operation of a low-solidity highly loaded turbine-blade profile suitable for use in an air-cooled turbine, which has been made in a cascade.
Date:
May 8, 1952
Creator:
Plohr, Henry W. & Nusbaum, William J.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation at transonic speeds of the effect of balancing tabs on the hinge-moment and other aerodynamic characteristics of a full-span flap on a tapered 45 degree sweptback wing of aspect ratio 3
Report presenting an investigation at transonic speeds of the control balancing characteristics of three tabs on a full-span flap on an aspect-ratio-3, 45 degree sweptback wing. The results indicated that all the tabs tested, inset, attached, or detached, would balance the flap hinge moments throughout the speed range.
Date:
April 8, 1952
Creator:
Lockwood, Vernard E. & Fikes, Joseph E.
Object Type:
Report
System:
The UNT Digital Library
The Preparation, Physical Properties, and Heats of Combustion of Four Alkylsilanes
Memorandum presenting a group of alkylsilanes consisting of monoethylsilane, diethylsilane, and trimethylsilane prepared in 65- and 90-percent yield by reduction of the respective alkylchlorosilanes with either lithium hydride or lithium aluminum hydride. The boiling points, densities, refractive indices, and freezing points were determined and presented with a survey of literature values.
Date:
March 8, 1951
Creator:
Tannenbaum, Stanley & Murphy, Maurice F.
Object Type:
Report
System:
The UNT Digital Library
Sound from a two-blade propeller at supersonic tip speeds
Report presenting sound measurements at static conditions for a two-blade, 47-inch-diameter propeller over a range of tip Mach numbers. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. Results regarding the experimental results and comparison with theory are provided.
Date:
May 8, 1951
Creator:
Hubbard, Harvey H. & Lassiter, Leslie W.
Object Type:
Report
System:
The UNT Digital Library
Derivation of the Equations of Motion of a Symmetrical Wing-Tip-Coupled Airplane Configuration With Rotational Freedom at the Junctures
"The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).
Date:
October 8, 1951
Creator:
Schy, Albert A.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Experimental Investigation of Flutter Characteristics of M and W Wings
Report presenting the results of nine experimental flutter tests involving two flat-plate models and two rib and spar models of NACA 0012 airfoil sections in order to give a comparison of the flutter characteristics of wings with M and W type plan forms. The W plan form generally gave higher flutter speeds than the M plan forms.
Date:
August 8, 1951
Creator:
Herr, Robert W.
Object Type:
Report
System:
The UNT Digital Library
Comparison of airfoil sections on two triangular-wing-fuselage configurations at transonic speeds from tests by the NACA wing-flow method
Report presenting tests using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of four triangular-wing-fuselage models. Measurements of the normal force, chord force, and pitching moment for various angles of attack. Two models had wings of aspect ratio 2.31, one with an NACA 65-009 airfoil section and one with a 9-percent-thick biconvex section, and two with wings of aspect ratio 4, one with an NACA 65-006 airfoil and one with a 6-percent-thick double-wedge airfoil.
Date:
August 8, 1951
Creator:
Hall, Albert W. & McKay, James M.
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 4 with 3-percent-thick, biconvex section
Report presenting a wing-body combination with a plane triangular wing of aspect ratio 4 and 3-percent-thick, biconvex 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:
June 8, 1951
Creator:
Heitmeyer, John C.
Object Type:
Report
System:
The UNT Digital Library
Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback
Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.
Date:
October 8, 1951
Creator:
Fields, E. M. & Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
Altitude operational characteristics of a prototype model of the J47D (RX1-1 and RX1-3) turbojet engines with integrated electronic control
Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.
Date:
January 8, 1952
Creator:
Bloomer, Harry E.; Conrad, E. William & Sobolewski, Adam E.
Object Type:
Report
System:
The UNT Digital Library
Some Effects of Fuselage Interference, Wing Interference, and Sweepback on the Damping in Roll of Untapered Wings as Determined by Techniques Employing Rocket-Propelled Vehicles
Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.
Date:
October 8, 1951
Creator:
Bland, William M., Jr. & Dietz, Albert E.
Object Type:
Report
System:
The UNT Digital Library
Low-Speed Investigation of the Effect of Several Flap and Spoiler Ailerons on the Lateral Characteristics of a 47.5 Degree Sweptback-Wing-Fuselage Combination at a Reynolds Number of 4.4. X 10(6)
Report presenting an investigation of the low-speed lateral characteristics of a 47.5 degree sweptback-wing-fuselage combination with several flap and spoiler aileron arrangements. Results regarding aileron control characteristics, spoiler-control characteristics, and a comparison of the two are provided.
Date:
December 8, 1950
Creator:
Pasamanick, Jerome & Sellers, Thomas B.
Object Type:
Report
System:
The UNT Digital Library
Damping in Pitch of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds
Memorandum presenting the application of the concept of indicial functions to the analysis of the aerodynamic phenomena associated with the short-period pitching mode of wings in subsonic and supersonic flight. Simple physical relationships are pointed out and are used to study the effect on the rotary-damping-moment coefficient of changes in center-of-gravity position, Mach number, aspect ratio, plan form, frequency, and thickness.
Date:
April 8, 1953
Creator:
Tobak, Murray
Object Type:
Report
System:
The UNT Digital Library