UNT Libraries Government Documents Department - 33 Matching Results

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Wind-Tunnel Investigation of the Drag and Lateral-Stability Characteristics of a 1/22-Scale Model of a Bomber Airplane Employing a Low-Aspect-Ratio Triangular Wing

Description: Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.
Date: July 8, 1953
Creator: Phelps, E. Ray
Item Type: Refine your search to only Report
open access

Theory of wing-body drag at supersonic speeds

Description: "The relation of Whitcomb's "area rule" to the linear formulas for wave drag at lightly supersonic speeds is discussed. By adopting an approximate relation between the source strength and the geometry of a wing-body combination, the wave-drag theory is expressed in terms involving the areas intercepted by oblique planes or Mach planes. The resulting formulas are checked by comparison with the drag measurements obtained in wind-tunnel experiments and in experiments with falling models in free ai… more
Date: July 8, 1953
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
open access

Elastic Buckling Under Combined Stresses of Flat Plates With Integral Waffle-Like Stiffening

Description: Theory and experiment were compared and found in good agreement for the elastic Buckling under combined stresses of long flat plates with integral waffle-like stiffening in a variety of configurations. For such flat plates, 45deg waffle stiffening was found to be the most effective of the configurations for the proportions considered over the widest range of combinations of compression and shear.
Date: October 8, 1953
Creator: Dow, Norris F.; Levin, L. Ross & Troutman, John L.
Item Type: Refine your search to only Report
open access

Damping in Pitch of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds

Description: 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
Item Type: Refine your search to only Report
open access

A summary of data on the division of loads for various wing-fuselage combinations

Description: From Summary: "A summary has been made of the available experimental data on division of normal-force loads between the wing and fuselage of aircraft. Comparison of the experimental values with theoretical calculations which include interference effects shows good agreement in general with the greatest differences occurring near a Mach number of 1.0. At high angles of attack, above the range of linear lift curves, the proportion of the total wing-fuselage load carried by the wing decreases and … more
Date: June 8, 1953
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
open access

Theoretical Calculations of the Stability Derivatives at Supersonic Speeds for a High-Speed Airplane Configuration

Description: "Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration are presented. The range of Mach numbers considered includes those cases for which the wing and tail surfaces have subsonic leading edges, supersonic leading edges, and combinations of the two. The methods of analysis are discussed; these represent detailed consideration of the important effects and contributions of the various airplane components utilizing available theories and … more
Date: October 8, 1953
Creator: Margolis, Kenneth & Bobbitt, Percy J.
Item Type: Refine your search to only Report
open access

Investigation at a Mach number of 1.90 of a diverter-type boundary-layer removal system for a scoop inlet

Description: Report presenting an experimental investigation at Mach number 1.90 to determine the effect of a diverter-type boundary-layer removal system on the performance of a scoop inlet. The supersonic portion of the inlet consisted of a two-dimensional, reverse Prandtl-Meyer turn followed by a constant-area throat. Results regarding the effect of fuselage position and subsonic diffuser performance are provided.
Date: June 8, 1953
Creator: Kochendorfer, Fred D.
Item Type: Refine your search to only Report
open access

Preliminary experimental investigation of transpiration cooling for an afterburner with a sintered, porous stainless-steel combustion-chamber wall

Description: Report presenting an experimental investigation of the application of transpiration air-cooling to the combustion-chamber wall of an afterburner. Results regarding the typical temperature and pressure profiles, correlation of wall temperatures, distribution of cooling-air flux density, longitudinal distribution of cooling air, longitudinal distribution of wall temperature, effect of permeability on cooling-air requirements, and fabricating and operating problems are provided.
Date: June 8, 1953
Creator: Koffel, William K.
Item Type: Refine your search to only Report
open access

Longitudinal Stability and Wake-Flow Characteristics of a Twisted and Cambered Wing-Fuselage Combination of 45 Degree Sweepback and Aspect Ratio 8 With a Horizontal Tail and Stall-Control Devices at a Reynolds Number of 4.0 X 10 (Exp 6)

Description: Report presenting an investigation to determine the effects of a horizontal tail on the longitudinal stability characteristics of a swept-back, twisted, and cambered wing in combination with a fuselage and various combinations of high-lift and stall-control devices. The ideal placement of the horizontal tail appeared to be at 6 percent wing semispan below the wing-root-chord plane.
Date: June 8, 1953
Creator: Foster, Gerald V.
Item Type: Refine your search to only Report
open access

An analytical study of sideslip angles and vertical-tail loads in rolling pullouts as affected by some characteristics of modern high-speed airplane configurations

Description: From Introduction: "The rolling-pullout maneuver (any maneuver in which rolls occur during high g flight conditions) has been shown to be pertinent to design considerations from the standpoint of the loads produced on a vertical tail (refs. 1 to 3). In order to understand this problem better, the results of an analytical study of effects of large variations of some of the lateral-stability-derivative coefficients on the maximum angle of sideslip at first peak of its oscillation are presented in… more
Date: October 8, 1953
Creator: Stone, Ralph W., Jr.
Item Type: Refine your search to only Report
open access

Effects of Fuel Temperature and Fuel Distribution on the Combustion Efficiency of a 16-Inch Ram-Jet Engine at a Simulated Mach Number of 2.9

Description: Report presenting the effect of preinjection-fuel temperature on vaporization rates and combustion efficiency of a 16-inch ram-jet engine for two different fuels. Variation of the location of the fuel injectors and use of control sleeves were also explored.
Date: January 8, 1953
Creator: Dangle, E. E.; Cervenka, A. J. & Bahr, D. W.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a spoiler-slot-deflector combination in producing rolling moments in the transonic speed range at angles of attack as high as 24 degrees over a range of Mach numbers. The wing had an aspect ratio of 4, a taper ratio of 0.6, an unswept quarter-chord line, and NACA 65A006 airfoil sections.
Date: December 8, 1953
Creator: Vogler, Raymond D.
Item Type: Refine your search to only Report
open access

A Preliminary Investigation at Mach Number 1.91 of a Diffuser Employing a Pivoted Cone to Improve Operation at Angle of Attack

Description: Report presenting an investigation to determine the performance of a conical-nose supersonic diffuser at angle of attack. The inlet had a pivoting cone which could be oriented to any of several angles independent of the angle of attack of the diffuser. Results regarding total-pressure recovery and mass-flow characteristics, cowl lip position, cone position relative to angle of attack, shadowgraphs, and contour maps are provided.
Date: December 8, 1953
Creator: Beheim, Milton A.
Item Type: Refine your search to only Report
open access

Diffusion factor for estimating losses and limiting blade loadings in axial-flow-compressor blade elements

Description: Report presenting a simplified limiting-blade-loading parameter for axial-flow-compressor blade elements derived from the application of a separation criterion used in two-dimensional boundary-layer theory to a typical suction-surface velocity distribution of a compressor blade element at design angle of attack. Results regarding two-dimensional cascade, compressor rotors, and compressor stators are provided.
Date: June 8, 1953
Creator: Lieblein, Seymour; Schwenk, Francis C. & Broderick, Robert L.
Item Type: Refine your search to only Report
open access

A Preliminary Study by Means of Electrical Frequency-Analysis Techniques of the Response of an Airplane Structure During Buffeting

Description: Report presenting a flight investigation to study in detail the response of an airplane structure during buffeting. Measurements of acceleration on selected points were made during buffeting for two different conditions of lift coefficient and Mach number and the time histories of acceleration were studied using electrical frequency-analysis techniques. Results regarding the ground response measurements, response to buffeting excitation, verification of the measured results, and the pilot's obs… more
Date: December 8, 1953
Creator: Yeates, John E., Jr. & Thompson, Jim Rogers
Item Type: Refine your search to only Report
open access

An Experimental Investigation of Wheel Spin-Up Drag Loads

Description: Report presenting information on landing gear applied drag loads and the nature of wheel spin-up in landing based on testing in the Langley impact basin. Particular attention is paid to the nature and variation of the coefficient of friction between the tire and runway during the wheel spin-up process. Results regarding the fundamentals of the process, comparison of maximum loads, variation of coefficient of friction, and effect of prerotation are provided.
Date: June 8, 1953
Creator: Milwitzky, Benjamin; Lindquist, Dean C. & Potter, Dexter M.
Item Type: Refine your search to only Report
open access

Effects of Span and Spanwise and Chordwise Location on the Control Effectiveness of Spoilers on a 50 Degree Sweptback Wing at Mach Numbers of 1.41 and 1.96

Description: Memorandum presenting an investigation in the supersonic blowdown tunnel to determine the effects of span and spanwise and chordwise location on the control characteristics of spoilers on a 6-percent-thick, 50 degrees sweptback wing of aspect ratio 2.5 and taper ratio of 0.625. The results of the investigation indicate that the inboard spoilers located at the rearward chordwise station produce the highest rolling-moment effectiveness.
Date: April 8, 1953
Creator: Kindell, William H.
Item Type: Refine your search to only Report
open access

Flow Diffusion in a Constant-Diameter Duct Downstream of an Abruptly Terminated Center Body

Description: Report presenting an investigation of the flow properties of a constant-outer-wall annual diffuser in combination with a tailpipe in order to come up with a configuration suitable for turbojet afterburners. Information about axial inlet flow and whirling inlet flow is provided. During testing, a vena contrata region formed downstream from the center body terminal and rendered the first 1/2 diameter of the tailpipe ineffective.
Date: July 8, 1953
Creator: Wood, Charles C. & Higginbotham, James T.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Several Water-Injection Configurations for Turbine-Blade Spray Cooling in a Turbojet Engine

Description: Memorandum presenting an investigation of water spray cooling of turbine rotor blades with a representative centrifugal-flow turbojet engine. Water injection from several stationary configurations was investigated in order to determine the most favorable configuration on an overall basis. Results regarding blade temperature distributions, cooling efficiencies of various configurations, rotor blades failures, rotor blade spray patterns, and overall comparison of injection configurations are prov… more
Date: October 8, 1953
Creator: Freche, John C. & McKinnon, Roy A.
Item Type: Refine your search to only Report
open access

Preliminary Investigation of the Total-Pressure-Recovery Characteristics of a 15 Degree Semiangle Movable-Cone Variable-Geometry Ram-Jet Inlet at Free-Jet Mach Numbers of 1.62, 2.00, 2.53, and 3.05

Description: Report presenting an investigation of a 15 degree semiangle movable-cone variable-geometry ram-jet inlet to determine the variable-geometry effect on total-pressure recovery at free-jet Mach numbers of 1.62, 2.00, 2.53, and 3.05 at zero angles of attack and yaw. Generally, increasing the cowling-position parameter increased the value of both total-pressure recovery and mass-flow ratio. Results regarding the total-pressure recovery, shadowgraphs, and total-pressure recovery as a function of free… more
Date: January 8, 1953
Creator: Hinners, Arthur H., Jr. & Lee, John B.
Item Type: Refine your search to only Report
open access

Flight Determination of Drag of Normal-Shock Nose Inlets With Various Cowling Profiles at Mach Numbers From 0.9 to 1.5

Description: External-drag data are presented for normal-shock nose inlets with NACA 1-series, parabolic, and conic cowling profiles. The tests were made at an angle of attack of 0 degrees by using rocket-propelled models in free flight at Mach numbers from 0.9 to 1.5. The Reynolds number based on body maximum diameter varied from 2.5 x 10 sup 6 to 5.5 x 10 sup 6.
Date: September 8, 1953
Creator: Sears, R. I.; Merlet, C. F. & Putland, L. W.
Item Type: Refine your search to only Report
open access

Lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds

Description: From Summary: "A method is presented for calculating the lift and centers of pressure of wing-body and wing-body-tail combinations at subsonic, transonic, and supersonic speeds. A set of design charts and a computing table are presented which reduce the computations to routine operations. Comparison between the estimated and experimental characteristics for a number of wing-body and wing-body-tail combinations shows correlation to within + or - 10 percent on lift and to within about + or - 0.02… more
Date: July 8, 1953
Creator: Pitts, William C.; Nielsen, Jack N. & Kaattari, George E.
Item Type: Refine your search to only Report
open access

The Ductility of Brazed Stainless Steel Joints

Description: Abstract: "The ductility of Type 310 stainless steel T-joints brazed with GE-62 brazing alloy was measured at room temperatures 1200, 1650, and 1800 F. The measure of ductility was taken as the plastic axial strain required to crack braze fillets in T-section tensile specimens. At elevated temperatures, the ductility of as-brazed joints approximated that of the stainless steel, but at room temperature the brazed joints had only one-tenth the ductility of the base metal. Annealing for 16 hr at 1… more
Date: July 8, 1953
Creator: Saller, Henry A.; Stacy, J. T. & Eddy, N. S.
Item Type: Refine your search to only Report
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