Resource Type
Serial/Series Title
NACA Research Memorandums
181
Atomic Energy Commission Reports
66
Hanford Works Reports
32
HW (Series)
27
NACA Technical Reports
25
University of California Radiation Laboratory Reports
24
Oak Ridge National Laboratory Reports
19
BNL (Series)
16
Brookhaven National Laboratory Reports
16
Report (U.S. Atomic Energy Commission)
13
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389 Matching Results
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The Effect of Spanwise Aileron Location on the Rolling Effectiveness of Wings With 0 Degree and 45 Degree Sweep at Subsonic, Transonic, and Supersonic Speeds
Report discussing an investigation of the effect of spanwise aileron location on the rolling effectiveness of plain faired ailerons on untapered wing plan forms with designated sweep, airfoil sections, and aspect ratio using rocket-propelled test vehicles. Drag data is also presented for all configurations tested. Spanwise aileron location was found to have little effect on the effectiveness of the aileron on an unswept wing plan form.
Date:
April 25, 1950
Creator:
Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
Effect of combustion-chamber pressure and nozzle expansion ratio on theoretical performance of several rocket propellant systems
Theoretical calculations of specific impulse to determine the separate effects of increasing the combustion-chamber pressure and the nozzle expansion ratio on the performance of the propellants, hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine and AN-F-58 fuel - white fuming nitric acid (95 percent). The results indicate that an increase in specific impulse obtainable with an increase in combustion-chamber pressure is almost entirely caused by the increased expansion ratio through the nozzle.
Date:
May 25, 1956
Creator:
Morrell, Virginia E.
Object Type:
Report
System:
The UNT Digital Library
Determination by the Free-Fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds
Report discussing the stability and control characteristics and drag of a canard or tail-first configuration explored using the free-fall method. Information about the basic flight characteristics, experimental coefficients, zero-lift drag configurations, and longitudinal stability and trim characteristics is provided.
Date:
August 25, 1950
Creator:
Kraft, Christopher C., Jr. & Mathews, Charles W.
Object Type:
Report
System:
The UNT Digital Library
Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions
A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.
Date:
May 25, 1950
Creator:
Acker, Loren W. & Kleinknecht, Kenneth S.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Thrust Augmentation of a 1600-Pound Thrust Centrifugal-Flow-Type Turbojet Engine by Injection of Refrigerants at Compressor Inlets
Investigations were conducted to determine effectiveness of refrigerants in increasing thrust of turbojet engines. Mixtures of water an alcohol were injected for a range of total flows up to 2.2 lb/sec. Kerosene was injected into inlets covering a range of injected flows up to approximately 30% of normal engine fuel flow. Injection of 2.0 lb/sec of water alone produced an increase in thrust of 35.8% of rate engine conditions and kerosene produced a negligible increase in thrust. Carbon dioxide increased thrust 23.5 percent.
Date:
August 25, 1947
Creator:
Jones, William L. & Dowman, Harry W.
Object Type:
Report
System:
The UNT Digital Library
Effects of Compressibility on the Characteristics of Five Airfoils
Report presenting the results of pressure-distribution tests to determine the effects of compressibility on the characteristics of the NACA 66,2-215, 66,2-015, 65(216)-418, 16-212, and 23015 airfoil sections. Schileren photographs of the air flow and data on the wake characteristics was also obtained.
Date:
April 25, 1947
Creator:
Daley, Bernard N.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Low-Speed Stability and Control Characteristics of a Model With a Sweptback Vee Tail and a Sweptback Wing
Report presenting testing in the 300 mph tunnel of a model with a sweptback vee tail and a sweptback wing to determine its low-speed stability and control characteristics. The results are compared to testing with the same tail panel with zero dihedral on the same wing-fuselage combination. The longitudinal stability characteristics, downwash at the tail, longitudinal control characteristics, lateral stability characteristics, and rudder control characteristics are provided.
Date:
May 25, 1948
Creator:
Polhamus, Edward C.
Object Type:
Report
System:
The UNT Digital Library
Investigations of an Annular Diffuser-Fan Combination Handling Rotating Flow
Memorandum presenting an investigation of two annular diffusers of different conical angles of expansion but constant outer diameters with rotating flow behind a fan. The performance characteristics are determined and the rotational-kinetic-energy effects on the overall energy transformation are observed over a range of inlet mach numbers from 0.1 to 0.44 and angles of flow up to 28 degrees.
Date:
April 25, 1949
Creator:
Schwartz, Ira R.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Free-Flight Investigation of the Effect of Airfoil Section on Aileron Rolling Effectiveness at Transonic and Supersonic Speeds
"Results have been obtained by means of a free-flight technique utilizing rocket propulsion which indicate that aileron-rolling-effectiveness characteristics are affected adversely by variations in airfoil section which procedure large increases in the trailing-edge angle" (p. 1).
Date:
June 25, 1948
Creator:
Sandahl, Carl A.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a Two-Step Nozzle in an 11-Inch Hypersonic Tunnel
Report discussing flow surveys made of several nozzles using two 2-dimensional steps at Mach number 6.98. Results regarding wall-pressure surveys, disturbance patterns in expansion, total-pressure survey, temperature recovery, and general nozzle characteristics are provided.
Date:
October 25, 1949
Creator:
McLellan, Charles H.; Williams, Thomas W. & Bertram, Mitchel H.
Object Type:
Report
System:
The UNT Digital Library
Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap
Report presenting an investigation of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. Results are given for pressure distributions, Schileren and liquid-film studies, and wing section characteristics are provided.
Date:
January 25, 1950
Creator:
Czarnecki, K. R. & Mueller, James N.
Object Type:
Report
System:
The UNT Digital Library
Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70
Report presenting testing of a full-scale, semispan, horizontal tail surface for a jet-propelled fighter airplane in the 16-foot high-speed tunnel to determine the variation of the chordwise and spanwise pressure distributions with Mach number. Surface irregularities were found to cause appreciable distortion of the pressure distribution. Results regarding chordwise distributions, spanwise distribution, effect of Mach number on root bending moment, and estimated critical Mach numbers are provided.
Date:
June 25, 1947
Creator:
Schueller, Carl F.
Object Type:
Report
System:
The UNT Digital Library
The use of perforated inlets for efficient supersonic diffusion
Report presenting the use of wall perforations on supersonic diffusers to avoid the internal contraction-ratio limitation. Experimental results on a preliminary model of a perforated diffuser at Mach number 1.85 are provided. A theoretical discussion of the flow coefficients and the size and spacing of the perforations are included.
Date:
June 25, 1947
Creator:
Evvard, John C. & Blakey, John W.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Bomb-Bay Configurations Intended to Minimize the Tumbling of Light-Weight Bombs
Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine what modifications could be made to conventional bomb bays to reduce the tumbling difficulties experienced with light-weight bombs. The investigation indicated that there is a definite region of reversed flow inside the bomb bay which must be weakened or destroyed if good drops are to be obtained.
Date:
June 25, 1947
Creator:
Kuhn, Richard E. & Polhamus, Edward C.
Object Type:
Report
System:
The UNT Digital Library
Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness of a 42.7 Degree Sweptback Wing Having Partial-Span Ailerons
An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.
Date:
October 25, 1948
Creator:
Sandahl, Carl A.
Object Type:
Report
System:
The UNT Digital Library
NACA Transonic Wing-Tunnel Test Sections
Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date:
October 25, 1948
Creator:
Wright, Ray H. & Ward, Vernon G.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Investigation at a Mach Number of 1.9 and a Reynolds Number of 2,200,000 of Three Ailerons Applicable to the Bell XS-2 Airplane Design
Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.
Date:
May 25, 1948
Creator:
Sivells, James C. & Conner, D. William
Object Type:
Report
System:
The UNT Digital Library
A preliminary experimental investigation of a submerged cascade inlet
Report presenting an experimental investigation of a submerged air inlet incorporating a cascade of airfoils for turning and diffusing the entering air. Variables associated with submerged air inlets and airfoil-cascade designs were considered, including changes to the ramp plan form and angle for the submerged inlet and the cascade-axis inclination, cascade-blade angle, solidity, and inclination of the center line of the duct for the cascade.
Date:
March 25, 1949
Creator:
Christiani, R. Duane & Randall, Lauros M.
Object Type:
Report
System:
The UNT Digital Library
Wing-flow measurements of longitudinal stability and control characteristics of a canard airplane configuration with a 45 degree sweptback wing and a triangular all-movable control surface
Report presenting measurements of the longitudinal stability and control characteristics of a canard airplane configuration using the wing-flow method. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model with control settings between several different degrees. The experimental data are presented in summarized or abridged form and calculated trim curves are presented for various flight loading conditions.
Date:
August 25, 1950
Creator:
Crane, Harold L. & Adams, James J.
Object Type:
Report
System:
The UNT Digital Library
Experimental investigation of the drag of 30 degree, 60 degree, and 90 degree cone cylinders at Mach numbers between 1.5 and 8.2
Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.
Date:
April 25, 1952
Creator:
Seiff, Alvin & Sommer, Simon C.
Object Type:
Report
System:
The UNT Digital Library
Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight
Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.
Date:
June 25, 1951
Creator:
Carman, L. Robert & Carden, John R.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Stresses Due to Thermal Gradients in Typical Aircraft Structures
Memorandum presenting an investigation of a series of five 75S-T6 aluminum-alloy elementary skin and spar-cap combinations with skin varying from 0.051 to 0.500 inch in thickness to determine the temperature and stress gradients resulting from the application of heat to the surface. The data are presented in the form of tables of the measured temperatures and stresses calculated from the measured strains.
Date:
January 25, 1952
Creator:
Barzelay, Martin E. & Boison, James C.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of the Longitudinal Stability and Control Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Up to 0.89
Report presenting results and analysis of the longitudinal stability and control characteristics of the Douglas D-558-I airplane at a range of altitudes and Mach numbers. It was found that large and rapid changes in elevator deflection and force were required for balance at Mach numbers above 0.84 due to a sharp decrease in elevator-stabilizer effectiveness.
Date:
June 25, 1951
Creator:
Sadoff, Melvin; Roden, William S. & Eggleston, John M.
Object Type:
Report
System:
The UNT Digital Library
Investigation of annular liquid flow with concurrent air flow in horizontal tubes
Report presenting visual observations and flow analyses made of annular liquid flow with cocurrent air flow in 2- and 4-inch-diameter horizontal transparent tubes. The experiments occurred over a range of air mass velocities, air temperatures, and Reynolds numbers. Results regarding the velocity and thickness of liquid films, description of water-film disturbances, effect of flow variables on liquid-film characteristics, and relation between disturbances and flow conditions are provided.
Date:
May 25, 1951
Creator:
Kinney, George R. & Abramson, Andrew E.
Object Type:
Report
System:
The UNT Digital Library