159 Matching Results

Search Results

Results: 1 - 24 next
open access

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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Model Ditching Investigations of Three Airplanes Equipped With Hydro-Skis

Description: "Model investigations were made to determine the ditching characteristics of three typical multiengine airplanes equipped with possible arrangements of hydro-ski ditching gear. The behavior of the models was determined from visual observations, acceleration records, and motion pictures of the landings. Data are presented in tabular form and sequence photographs" (p. 1).
Date: April 25, 1950
Creator: Fisher, Lloyd J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Model ditching investigations of three airplanes equipped with hydro-skis

Description: Report presenting an investigation to determine the ditching characteristics of three typical multiengine airplanes equipped with different arrangements of hydro-ski ditching gear. The behavior was determined from visual observations, acceleration records, and motion pictures of the landings. Results regarding ski size, shape, and location are provided.
Date: April 25, 1950
Creator: Fisher, Lloyd J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Description: 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… more
Date: May 25, 1950
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination by the Free-Fall Method of the Drag and Longitudinal Stability and Control Characteristics of a Canard Model at Transonic Speeds

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A theoretical investigation of the influence of auxiliary damping in pitch on the dynamic characteristics of a proportionally controlled supersonic canard missile configuration

Description: Report presenting a theoretical analysis of a supersonic canard missile configuration to show the means that might be used to improve its dynamic performance characteristics. The analysis was conducted by using the best available estimates of aerodynamic and airframe parameters. Results regarding missile longitudinal performance, selection of rate factor, angle of attack and normal acceleration, frequency response, pole plots, and tip control are provided.
Date: August 25, 1950
Creator: Nelson, Walter C. & Passera, Anthony L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of Aerodynamic Characteristics of a 35 Degree Sweepback NACA 65-009 Airfoil Model With 1/4 Chord Flap Having 31 Percent Flap Chord Overhang Balance by the NACA Wing Flow Method

Description: Report of testing on an untapered 35-degree sweptback airfoil-flap model, representative of a wing or tail surface, with several 1/4-chord full-span flaps differing in aerodynamic balance. A plain flap, a horn-balanced flap, and a beveled-trailing-edge flap were compared to a flap that had a 31-percent-flap-chord overhang balance. Information about lift, pitching-moment, and hinge-moment characteristics is provided.
Date: September 25, 1950
Creator: Johnson, Harold I. & Goodman, Harold R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of large scale flight measurements of zero lift drag at Mach numbers from 0.9 to 1.7 of two wing-body combinations having similar 60 degree triangular wings with NACA 65A003 sections

Description: Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination made at high-subsonic and supersonic speeds in a range of Reynolds numbers. The data are presented with that from a wingless body and similar winged body with a slightly different ratio of body frontal area to wing area. Results regarding total drag and wing-plus-interference drag are provided.
Date: October 25, 1950
Creator: Schult, Eugene D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Correlation of physical properties with molecular structure for some dicyclic hydrocarbons having high thermal-energy release per unit volume -- 2-alkylbiphenyl and the two isomeric 2-alkylbicyclohexyl series

Description: Three homologous series of related dicyclic hydrocarbons are presented for comparison on the basis of their physical properties, which include net heat of combustion, density, melting point, boiling point, and kinematic viscosity. The three series investigated include the 2-n-alkylbiphenyl, 2-n-alkylbicyclohexyl (high boiling), and 2-n-alkylbiphenyls (low boiling) series through c sub 16, in addition to three branched-chain (isopropyl, sec-butyl, and isobutyl) 2-alkylbiphenyls and their corresp… more
Date: January 25, 1951
Creator: Goodman, Irving A. & Wise, Paul H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Data on the Effect of Body-Nose Bluntness on the Drag and Pressure Recovery of a Side-Inlet-Body Combination at Mach Numbers of 1.4 and 1.7

Description: Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop, side-inlet-body combination measured at Mach number 1.4 and 1.7. The inlet was located on a body having an ogival nose followed by a cylindrical section and a total fineness ratio of 5.
Date: April 25, 1951
Creator: Stroud, John F. & Anderson, Warren E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of annular liquid flow with concurrent air flow in horizontal tubes

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Limits of Flammability of Pure Hydrocarbon-Air Mixtures at Reduced Pressures and Room Temperature

Description: Memorandum presenting a systematic study to determine the effect of molecular structure on the flammability limits of pure hydrocarbon-air mixtures at reduced pressures and room temperature. This report presents results obtained for 17 pure normal paraffins, branched paraffins, and mono-olefins. Results regarding experimental variables and experimental observations are provided.
Date: May 25, 1951
Creator: DiPiazza, James T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0

Description: Memorandum presenting the pressure recovery, mass flow, and axial force of four bodies with nose inlets measured at Mach numbers between 1.4 and 2.0 and angles of attack of 0, 3, 6, and 9 degrees. The drag coefficients of axially symmetric diffusers operating at the maximum mass-flow rates were calculated from schileren photographs of the head shock waves and frictional drag considerations. Results regarding open-nose diffusers and conical-shock diffusers are provided.
Date: June 25, 1951
Creator: Brajnikoff, George B. & Rogers, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Zero-Lift Drag Determined by Flight Tests at Transonic Speeds of Pylon, Underslung, and Symmetrically Mounted Nacelles at 40 Percent Semispan of a 45 Degrees Sweptback Wing and Body Combination

Description: Report presenting the effect on drag of varying the vertical position of a nacelle at 40 percent semispan of a 45 degree sweptback wing and body combination as determined by transonic flight tests at zero lift. Three nacelle positions were investigated: a pylon mounted nacelle, an underslung nacelle, and a symmetrically mounted nacelle. Results regarding total drag coefficient and maximum wing-tip helix angle are provided.
Date: June 25, 1951
Creator: Hoffman, Sherwood
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation in the Ames 12-Foot Pressure Wind Tunnel of a Model Horizontal Tail of Aspect Ratio 3 and Taper Ratio 0.5 Having the Quarter-Chord Line Swept Back 45 Degrees

Description: Memorandum presenting an investigation to evaluate the effect of Reynolds number and Mach number on the aerodynamic characteristics of a horizontal tail of aspect ratio 3 equipped with a plain, sealed, full-span elevator. The line joining the quarter-chord points of the airfoil sections was swept back 45 degrees and the sections perpendicular to this line were the NACA 64A010. Results regarding the effect of Reynolds number and effects of leading-edge roughness and elevator-nose seal are provid… more
Date: June 25, 1951
Creator: Kolbe, Carl D. & Bandettini, Angelo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure-distribution measurements over a 45 degree sweptback wing at transonic speeds by the NACA wing-flow method

Description: Report presenting measurements of pressure made over the chord of a swept-wing model at four stations along the span by the NACA wing-flow method. The model was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. Results regarding the chordwise pressure distributions and spanwise distributions of section lift, drag, and pitching moment.
Date: June 25, 1951
Creator: Danforth, Edward C. B. & O'Bryan, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design of two-dimensional channels with prescribed velocity distributions along the channel walls

Description: "A general method of design is developed for two-dimensional unbranched channels with prescribed velocities as a function of arc length along the channel walls. The method is developed for both compressible and incompressible, irrotational, nonviscous flow and applies to the design of elbows, diffusers, nozzles, and so forth. In part I solutions are obtained by relaxation methods; in part II solutions are obtained by a Green's function. Five numerical examples are given in part I including thre… more
Date: July 25, 1951
Creator: Stanitz, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of the Drag of Round-Nosed Bodies of Revolution at Mach Numbers From 0.6 to 1.5 Using Rocket-Propelled Test Vehicles

Description: "Values of total drag coefficient were measured for four round-nosed bodies of revolution in free flight at Mach numbers from 0.6 to 1.5 and Reynolds numbers from 10 x 10(6) to 50 x 10(6). The bodies were designed by rounding off the sharp, fineness-ratio-3.56 nose of a previously tested configuration. The nose radii tested were 27.4, 38.7, 80.6, and 100 percent of the maximum body radius and corresponded to values of 0.075, 0.150, 0.650, and 1.000, respectively, for the ratio of nose-sphere fr… more
Date: July 25, 1951
Creator: Hart, Roger G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight study of requirements for satisfactory lateral oscillatory characteristics of fighter aircraft

Description: Report presenting a pilot-opinion survey conducted with a conventional fighter airplane fitted with special servo devices for varying in flight the dihedral effect, static directional stability, and directional damping. Results showing the boundaries that define satisfactory and tolerable lateral oscillatory characteristics are presented.
Date: July 25, 1951
Creator: Liddell, Charles J., Jr.; Creer, Brent Y. & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A comparison of the calculated maximum-maneuver response characteristics of three air-to-air, beam-rider, guided missiles having different lift ratios

Description: Report presenting a comparison of the calculated response characteristics corresponding to the maximum maneuver of a variable-incidence, a canard, and a conventional tail-aft-control, beam-rider, guided missile. All the configurations were designed to be the same except for the effects of changes in lift ratio. Results regarding limited control-surface deflection, limited angle of attack of the critical surface, servo energy, surface-deflection interference, and size of surfaces are provided.
Date: September 25, 1951
Creator: Matthews, Howard F. & Stewart, Elwood C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen