UNT Libraries Government Documents Department - 639 Matching Results

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Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

Description: The method of coordinate perturbation is applied to the unsteady flow of a compressible fluid in ducts of variable cross section. Solutions, in the form of perturbation series, are obtained for unsteady flows in ducts for which the logarithmic derivative of area variation with respect to the space coordinate is a function of the 'smallness' parameter of the perturbation series. This technique is applied to the problem of the interaction of a disturbance and a shock wave in a diffuser flow. It i… more
Date: September 1958
Creator: Himmel, Seymour C.
Item Type: Refine your search to only Report
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An Approach to the Problem of Estimating Severe and Repeated Gust Loads for Missile Operations

Description: Note presenting an analysis of available airplane measurements of vertical gust velocity in order to arrive at a simple description of the frequency and intensity of gust velocities experienced by airplanes in operations. For the purpose of application to missile operations, the results obtained are modified to eliminate the effects of storm-avoidance procedures normally followed in airplane operations.
Date: September 1958
Creator: Press, Harry & Steiner, Roy
Item Type: Refine your search to only Report
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An approximate analytical method for studying entry into planetary atmospheres

Description: Report presenting a single, ordinary, nonlinear differential equation of second order that can be used for determining entry into an exponential planetary atmosphere. The reduced equation includes various terms, some of which represent the gravity force, the centrifugal acceleration, and the lift force. A number of solutions for lifting and nonlifting vehicles entering at various initial angles are obtained from the complete nonlinear equation.
Date: May 1958
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
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Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll

Description: Report presenting an extension of a method for calculating motions in angles of attack and sideslip resulting from a trim angle of attack and steady rolling velocity to the condition of pitching- and yawing-moment inputs. The resulting formulas are intended primarily for rolling-velocity conditions in which rolling divergence is not encountered.
Date: September 1958
Creator: Moul, Martin T. & Brennan, Teresa R.
Item Type: Refine your search to only Report
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Approximate Method for Calculation of Laminar Boundary Layer With Heat Transfer on a Cone at Large Angle of Attack in Supersonic Flow

Description: Note presenting the use of an integral technique to reduce the laminar boundary-layer equations on the windward generator of the plane of symmetry to a set of simultaneous algebraic equations. The method enables the skin friction coefficients and Stanton number to be calculated in a much shorter time than was needed to obtain exact numerical solutions from the boundary-layer equations.
Date: September 1958
Creator: Brunk, William E.
Item Type: Refine your search to only Report
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An Approximate Method for Design or Analysis of Two-Dimensional Subsonic-Flow Passages

Description: Note presenting a method for the design and analysis of two-dimensional subsonic-flow passages with isentropic nonviscous flow. The method is based on the relation between the pressure change across a stream tube and the centrifugal force resulting from the curvature of the flow. In an example, the method was applied to the design of an expanding elbow at each of two Mach numbers.
Date: April 1958
Creator: Valentine, E. Floyd
Item Type: Refine your search to only Report
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Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Description: Report presenting an analysis for obtaining approximate solutions of the similarity equations for three-dimensional laminar-boundary-layer flows over a flat surface under main-flow streamlines that are translates and representable as infinite series expansions.
Date: September 1958
Creator: Hansen, Arthur G. & Herzig, Howard Z.
Item Type: Refine your search to only Report
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Approximations for the thermodynamic and transport properties of high-temperature air

Description: Report presenting the thermodynamic and transport properties of high-temperature air in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, specific heats, speed of sound, coefficients of viscosity and thermal conductivity, and Prandtl numbers for air are provided for a range of temperatures and pressures.
Date: March 1958
Creator: Hansen, C. Frederick
Item Type: Refine your search to only Report
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Area-Suction Boundary-Layer Control as Applied to the Trailing-Edge Flaps of a 35 Degree Swept-Wing Airplane

Description: "A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying area-suction boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effect of boundary-layer control in the handling qualities and operation of the airplane, particularly during landing. The wind-tunnel and flight tests indicated that area suction applied to the trailing-edge flaps pro… more
Date: May 6, 1958
Creator: Cook, Woodrow L.; Anderson, Seth B. & Cooper, George E.
Item Type: Refine your search to only Report
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Behavior of Some Materials and Shapes in Supersonic Free Jets at Stagnation Temperatures Up to 4,210 Degrees F, and Descriptions of the Jets

Description: Report presenting testing of a number of materials and shapes in two supersonic free jets at stagnation temperatures of up to 4,210 degrees Fahrenheit. Some testing was conducted in a supersonic chemical jet and some was conducted in a ceramic-heated air jet. Materials tested included aluminum alloy, copper, Inconel, magnesium, mild steel, molybdenum, stainless steel, titanium, alumina, zirconia, graphite, bakelite, and nylon.
Date: February 24, 1958
Creator: Fields, E. M.; Hopko, Russell N.; Swain, Robert L. & Trout, Otto F., Jr.
Item Type: Refine your search to only Report
open access

Blowing-type boundary-layer control as applied to the trailing-edge flaps of a 35 degree swept-wing airplane

Description: A wind-tunnel investigation was made to determine the effects on the aerodynamic characteristics of a 35 degree swept-wing airplane of applying blowing-type boundary-layer control to the trailing-edge flaps. Flight tests of a similar airplane were then conducted to determine the effects of boundary-layer control on the handling qualities and operation of the airplane, particularly during landing and take-off. The wind-tunnel and flight tests indicated that blowing over the flaps produced large … more
Date: April 30, 1958
Creator: Kelly, Mark W.; Anderson, Seth B. & Innis, Robert C.
Item Type: Refine your search to only Report
open access

A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

Description: From Summary: "Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possib… more
Date: July 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Item Type: Refine your search to only Report
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Boron and zirconium from crucible refractories in a complex heat-resistant alloy

Description: In a laboratory study of the factors involved in the influence of induction vacuum melting on 55ni-20cr-15co-4mo-3ti-3al heat resistant alloy, it was found that the major factor was the type of ceramic used as the crucible. The study concluded that trace amounts of boron or zirconium derived from reaction of the melt with the crucible refactories improved creep-rupture properties at 1,600 degrees F. Boron was most effective and, in addition, markedly improved hot-workability.
Date: August 5, 1958
Creator: Decker, R. F.; Rowe, John P. & Freeman, J. W.
Item Type: Refine your search to only Report
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Boundary-Induced Downwash Due to Lift in a Two-Dimensional Slotted Wind Tunnel

Description: Note presenting a solution obtained for the complete tunnel-interference flow for a lifting vortex in a two-dimensional slotted tunnel. Curves are presented for the longitudinal distribution of tunnel-induced downwash angle for various values of boundary openness parameter and various heights of the vortex above the tunnel center line.
Date: June 1958
Creator: Katzoff, S. & Barger, Raymond L.
Item Type: Refine your search to only Report
open access

Boundary-layer stability diagrams for electrically conducting fluids in the presence of a magnetic field

Description: From Summary: "The effectiveness of a magnetic field in stabilizing the laminar flow of an incompressible, electrically conducting fluid is studied. The neutral stability curves pertaining to a two-dimensional sinusoidal disturbance are presented for flow over a semi-infinite flat plate in the presence of either a coplanar or transverse magnetic field and for channel flow in the presence of a coplanar or transverse magnetic field and for channel flow in the presence of a coplanar magnetic field… more
Date: August 1958
Creator: Rossow, Vernon J.
Item Type: Refine your search to only Report
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Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages… more
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
open access

Boundary-layer transition on an open-nose cone at Mach 3.1

Description: Report presenting comparison of transition locations for an open-nose cone, a conventional sharp cone, and a hollow cylinder showed that transition locations on the open-nose cone and hollow cylinder were identical but differed from the sharp cone. Bluntness effects on the open-nose cone were quite similar to those observed on the hollow cylinder.
Date: February 1958
Creator: Brinich, Paul F.
Item Type: Refine your search to only Report
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Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests

Description: Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet inpu… more
Date: February 21, 1958
Creator: Davis, Don D., Jr. & Wornom, Dewey E.
Item Type: Refine your search to only Report
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Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests

Description: Report presenting an investigation of the buffet characteristics of a model of an attack airplane at a variety of Mach numbers. The wing had a modified delta plan form with two NACA airfoils, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet input force are provided.
Date: February 21, 1958
Creator: Davis, Don D., Jr. & Wornom, Dewey E.
Item Type: Refine your search to only Report
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Calculation of Flutter Characteristics for Finite-Span Swept or Unswept Wings at Subsonic and Supersonic Speeds by a Modified Strip Analysis

Description: Report presenting a method for calculating flutter characteristics of finite-span swept or unswept wings at subsonic and supersonic speeds. Flutter characteristics were calculated using this method for 12 wings of varying sweep angle, aspect ratio, taper ratio, and center-of-gravity position at a range of Mach numbers.
Date: March 18, 1958
Creator: Yates, E. Carson, Jr.
Item Type: Refine your search to only Report
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Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data

Description: "A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could t… more
Date: June 24, 1958
Creator: Shanks, Robert E.
Item Type: Refine your search to only Report
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Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58

Description: Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date: June 20, 1958
Creator: Hollinger, James A.
Item Type: Refine your search to only Report
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