Resource Type
Serial/Series Title
NACA Research Memorandums
173
Atomic Energy Commission Reports
61
NACA Technical Reports
30
Hanford Works Reports
20
HW (Series)
16
Oak Ridge National Laboratory Reports
15
University of California Radiation Laboratory Reports
12
AEC research and development report
6
AECU (Series)
6
BNL (Series)
6
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331 Matching Results
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Investigation of the Structural Damping of a Full-Scale Airplane Wing
"An investigation to determine the structural damping characteristics of a full-scale airplane wing was conducted by the shock-excitation method wherein the wing was loaded to a predetermined deflection and the load suddenly released. The test specimen vibrated at its fundamental bending frequency of 1.69 cycles per second. Only the first 2 or 3 cycles showed any indication of a higher frequency being superimposed upon the fundamental bending frequency" (p. 1).
Date:
March 9, 1951
Creator:
Fearnow, Dwight O.
Object Type:
Report
System:
The UNT Digital Library
Performance of 4600-Pound-Thrust Centrifugal-Flow-Type Turbojet Engine With Water-Alcohol Injection at Inlet
"An experimental investigation of the effects of injecting a water-alcohol mixture of 2:1 at the compressor inlet of a centrifugal-flow type turbojet engine was conducted in an altitude test chamber at static sea-level conditions and at an altitude of 20,000 feet with a flight Mach number of 0.78 with an engine operating at rated speed. The net thrust was augmented by 0.16 for both flight conditions with a ratio of injected liquid to air flow of 0.05. Further increases in the liquid-air ratio did not give comparable increases in thrust" (p. 1).
Date:
October 9, 1950
Creator:
Glasser, Philip W.
Object Type:
Report
System:
The UNT Digital Library
Model flight investigation of a nonlifting winged tow target
Report presenting an investigation in the free-flight tunnel to study the dynamic stability characteristics at low speeds of a winged tow-target model, the wings of which were free to float about a spanwise axis. Results regarding the wing panels fixed rigidly to the fuselage, wing panels hinged to move together, and wing panels hinged independently are provided.
Date:
October 9, 1950
Creator:
Shanks, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Over-all performance of the J71 three-stage turbine
Report presenting an investigation to determine the overall performance of the three-stage turbine from the J71 turbojet engine. The turbine operated with a maximum brake internal efficiency of approximately 0.84 at an equivalent overall pressure ratio of approximately 3.6 and an equivalent rotor speed of about 110 percent of the equivalent design value.
Date:
July 9, 1952
Creator:
Berkey, William E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the hydrodynamic stability and resistance of two streamline fuselages
Report presenting an investigation of a dynamic model to determine the effects of hull form, gross load, and aerodynamic trimming moments on the trim limits, trim, hydrodynamic moment, hydrodynamic resistance, total resistance, and rise of two streamline fuselages modified by chine strips. Results regarding effects of hull form and effects of gross load are provided.
Date:
April 9, 1952
Creator:
Weinflash, Bernard & Shuford, Charles L., Jr.
Object Type:
Report
System:
The UNT Digital Library
The Effect of Entrance Mach Number and Lip Shape on the Subsonic Characteristics of a Scoop-Type-Air-Induction System for a Supersonic Airplane
Report presenting an investigation at subsonic speeds to determine the effects of lip shape and entrance Mach number on the characteristics of a scoop-type air-induction system designed for an airplane flying at supersonic speeds. Results regarding the ram-recovery ratio, static-pressure distribution, and drag are provided.
Date:
January 9, 1952
Creator:
Holzhauser, Curt A.
Object Type:
Report
System:
The UNT Digital Library
Pressure distribution at Mach numbers up to 0.90 on a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10, including the effects of fences
Report presenting pressure measurements on a semispan model of a cambered and twisted wing, alone and in combination with a fuselage. The wing had 40 degrees of sweepback, an aspect ratio of 10, a taper ratio of 0.4, and 5 degrees of washout at the tip. Results regarding the pressure distribution and flow separation, section characteristics, and span loading characteristics are provided.
Date:
March 9, 1953
Creator:
Boltz, Frederick W. & Shibata, Harry H.
Object Type:
Report
System:
The UNT Digital Library
An analysis of the potentialities of a two-stage counterrotating supersonic compressor
From Introduction: "The supersonic axial-flow compressor, for example, appears to offer advantages of high stage pressure ratio and height weight flows (reference 1) but problems peculiar to this compressor type have accompanied its introduction. For high single-stage pressure ratios (>4) the problem of converting the high dynamic energy to useful pressure arises (reference 2). In addition, the high tip speeds and weight flows combine to create a difficult situation for the turbine designer."
Date:
July 9, 1952
Creator:
Wilcox, Ward W.
Object Type:
Report
System:
The UNT Digital Library
Altitude performance investigation of single- and double-annular turbojet-engine combustors with various size fuel nozzles
From Introduction: "The purpose of the investigation conducted at the NACA Lewis laboratory and reported herein was to determine the improvements possible in full-scale turbojet-engine performance when a single-annular combustor with slotted air-inlet orifices was used."
Date:
June 9, 1952
Creator:
Harp, James L., Jr. & Vincent, Kenneth R.
Object Type:
Report
System:
The UNT Digital Library
Gust-Tunnel Investigation of a Delta-Wing Model With the Leading Edge Swept Back 60 Degrees
Report discussing an investigation of a delta-wing model with the leading edge swept back 60 degrees. Testing indicated that the gust load is greater than would be predicted by using a slope of the lift curve determined from steady-flow force tests. An aspect-ratio relation was determined for this type of wing with the selected apex angle, but it does not appear to be applicable to other wings with different apex angles.
Date:
April 9, 1952
Creator:
Pierce, Harold B. & Johns, Slaton L.
Object Type:
Report
System:
The UNT Digital Library
Flame velocities of four alkylsilanes
Report presenting the rates of flame propagation of four alkylsilanes as determined by the tube method. Results regarding alkylsilane flame velocities, blends of diethylsilane and n-pentane, and flame propagation theories are provided.
Date:
March 9, 1951
Creator:
Gerstein, Melvin; Wong, Edgar L. & Levine, Oscar
Object Type:
Report
System:
The UNT Digital Library
Ignition delay experiments with small-scale rocket engine at simulated altitude conditions using various fuels with nitric acid oxidants
"Ignition delay determinations of several fuels with nitric oxidants were made at simulated altitude conditions utilizing a small-scale rocket engine of approximately 50 pounds thrust. Included in the fuels were aniline, hydrazine hydrate, furfuryl alcohol, furfuryl mercaptan, turpentine, and mixtures of triethylamine with mixed xylidines and diallyaniline. Red fuming, white fuming, and anhydrous nitric acids were used with and without additives. A diallylaniline - triethylamine mixture and a red fuming nitric acid analyzing 3.5 percent water and 16 percent NO2 by weight was found to have a wide temperature-pressure ignition range, yielding average delays from 13 milliseconds at 110 degrees F to 55 milliseconds at -95 degrees F regardless of the initial ambient pressure that ranged from sea-level pressure altitude of 94,000 feet" (p. 1).
Date:
January 9, 1952
Creator:
Ladanyi, Dezso J.
Object Type:
Report
System:
The UNT Digital Library
Dynamic Stability and Control Characteristics of a Delta-Wing Vertically Rising Airplane Model in Take-Offs, Landings, and Hovering Flight
Report presenting an investigation by means of tests of a flying model in still air to determine the dynamic stability and control characteristics of a delta-wing vertically rising airplane in take-off, landing, and hovering phases of flight. The uncontrolled pitching motion consisted of an unstable oscillation which was more unstable with a rearward than with the normal center-of-gravity location.
Date:
October 9, 1951
Creator:
Lovell, Powell M., Jr.; Bates, William R. & Smith, Charles C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Power Unit for High-Intensity Light Source
"A light-source power unit has been developed that provides reliable trigger, and easy synchronization with rotating elements or electric impulses. When used with conventional spark gaps and flash tubes, this power unit provides a light pulse of high intensity and short duration" (p. 1).
Date:
July 9, 1951
Creator:
Young, Allen E.; McCullough, Stuart & Smith, Richard L.
Object Type:
Report
System:
The UNT Digital Library
The Effects of Increasing the Leading-Edge Radius and Adding Forward Camber on the Aerodynamic Characteristics of a Wing With 35 Degrees of Sweepback
Report presenting a wind-tunnel investigation to determine the effects of a section modification on the aerodynamic characteristics of a wing with 35 degrees of sweepback. The wing was modified by increasing the leading-edge radius of the NACA 64A010 section and adding a small amount of camber to the forward portion of the chord. Lift, drag, pitching-moment, and trailing-edge-flap hinge-moment characteristics of the modified wing are compared with results from the original wing.
Date:
February 9, 1951
Creator:
Demele, Fred A. & Sutton, Fred B.
Object Type:
Report
System:
The UNT Digital Library
Static Directional Stability of a Tandem-Helicopter Fuselage
Memorandum presenting an investigation to determine the static directional stability of a fuselage typical of tandem helicopters. The model consisted of a body with an elliptical cross section, a rear rotor pylon which was faired to form a large vertical tail with a very thick airfoil section, and a small horizontal tail mounted at about the midpoint of the height of the vertical tail. Results regarding the stability of the original model, the causes of low directional stability, and tests of some practical modifications of increasing directional stability are provided.
Date:
August 9, 1950
Creator:
Smith, Charles C., Jr.
Object Type:
Report
System:
The UNT Digital Library
A Transonic Wind-Tunnel Investigation of the Effects of Body Indentation, as Specified by the Transonic Drag-Rise Rule, on the Aerodynamic Characteristics and Flow Phenomena of a 45 Degree Sweptback-Wing-Body Combination
Memorandum presenting a comparison of the aerodynamic characteristics and flow phenomena at transonic speeds for a 45 degree sweptback wing mounted alternatively on a cylindrical body and an indented body. Indentation eliminated the zero-lift drag rise associated with the wing at a Mach number of 1. Results regarding the lift, drag, and pitching moment, flow surveys, level-flight characteristics, and flow phenomena are provided.
Date:
February 9, 1953
Creator:
Robinson, Harold L.
Object Type:
Report
System:
The UNT Digital Library
Charts for the Determination of Wing Torsional Stiffness Required for Specified Rolling Characteristics or Aileron Reversal Speed
From Summary :"A series of charts are presented by which the wing torsional stiffness required to meet a given standard of rolling effectiveness may be quickly determined. The charts may also be used to obtain quickly the aileron reversal speed and the variation of the loss in rolling effectiveness with airspeed. The charts apply to linearly tapered wings and elliptical wings of tubular-shell construction having various aspect ratios with aileron span and location of ailerons as variables. In the derivation of the charts, induced lift effects have been taken into account and the form of the wing-torsional-stiffness curve has been assumed."
Date:
November 9, 1944
Creator:
Pearson, Henry A. & Aiken, William S., Jr.
Object Type:
Report
System:
The UNT Digital Library
The Variation of Atmospheric Turbulence With Altitude and Its Effect on Airplane Gust Loads
Report presenting information on the amount and relative intensity of atmospheric turbulence for altitudes up to 60,000 as obtained by airplanes and balloon-borne instruments. Analysis of the data obtained indicated that there are substantial reductions in turbulence at higher altitudes in the weather conditions measured in the tests. Results regarding gust distributions, including non-thunderstorm turbulence, thunderstorm turbulence, total gust distributions, and a comparison of gusts are also provided.
Date:
November 9, 1953
Creator:
McDougal, Robert L.; Coleman, Thomas L. & Smith, Philip L.
Object Type:
Report
System:
The UNT Digital Library
Effect of flame-holder design on altitude performance of louvered-liner afterburner
Report presenting an investigation in an altitude test chamber to determine criteria for the design of flame holders for a turbojet-engine afterburner. The performance of ten flame holders was obtained in a louvered-liner afterburner operated at constant afterburner-inlet temperature over a range of fuel air ratio and total pressures. Results regarding the effect of gutter cross-sectional shape, effect of gutter width, effect of flame-holder blocked area, effect of trailing and interconnecting gutters, and effect of altitude on V-gutter flame holders are provided.
Date:
October 9, 1953
Creator:
Renas, Paul E. & Jansen, Emmert T.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube
From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."
Date:
April 9, 1953
Creator:
Deissler, Robert G. & Taylor, Maynard F.
Object Type:
Report
System:
The UNT Digital Library
Measurements of Heat-Transfer and Friction Coefficients for Air Flowing in a Tube of Length-Diameter Ratio of 15 at High Surface Temperatures
Report presenting measurements of average heat-transfer and friction coefficients for air flowing through a smooth, electrically heated tube with a bellmouth entrance with a length-to-diameter ratio of 15 and a range of average surface temperatures, Reynolds numbers, exit Mach numbers, and heat fluxes. Results regarding the axial-wall-temperature distribution, heat balance, correlation of heat-transfer coefficients, and correlation of friction coefficient are provided.
Date:
July 9, 1953
Creator:
Weiland, Walter F. & Lowdermilk, Warren H.
Object Type:
Report
System:
The UNT Digital Library
Static aeroelastic phenomena of M-, W-, and A-wings
Report presenting spanwise lift distributions, lift coefficients, spanwise centers of pressure, shifts in aerodynamic center, coefficients of damping in roll, aileron rolling-moment coefficients, and rates of steady roll per unit aileron deflection have been calculated for nine M-, W-, and delta wings, as well as for comparable ordinary sweptforward, unswpet, and sweptback wings. Certain qualitative conclusions are drawn concerning the plan forms most suitable from the aeroelastic point of view. M and W plan forms exist which are superior aeroelastically and structurally to ordinary swept wings.
Date:
February 9, 1953
Creator:
Diederich, Franklin W. & Foss, Kenneth A.
Object Type:
Report
System:
The UNT Digital Library
Design procedure and limited test results for a high solidity, 12-inch transonic impeller with axial discharge
Report presenting an approximate inverse impeller design procedure based on the assumption of axisymmetric, nonviscous flow along with some limited experimental data obtained from a high solidity, 12-inch transonic impeller. The design procedure includes a point-by-point solution of the impeller flow conditions along a series of streamlines in the radial-axial plane. Results regarding the overall performance, impeller flow limits, and blade structural failure are provided.
Date:
April 9, 1953
Creator:
Wright, Linwood C. & Kovach, Karl
Object Type:
Report
System:
The UNT Digital Library