UNT Libraries Government Documents Department - 57 Matching Results

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Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Description: Report presenting an experimental investigation of several airplane configurations at Mach 3.0 in a continuous flow tunnel. The configurations had circular fuselage cross sections and a sweptback wing and either two nacelles or two side inlets.
Date: March 18, 1958
Creator: Dryer, Murray & Luidens, Roger W.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Description: From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."
Date: March 24, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
open access

An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

Description: Memorandum presenting an investigation made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds. Results regarding the leading-edge temperature rise, influence of conduction on leading-edge temperature for skins of uniform thickness, and surface-temperature distribution are provided.
Date: March 17, 1958
Creator: Neel, Carr B.
Item Type: Refine your search to only Report
open access

Analysis of two-stage counterrotating turbine efficiencies in terms of work and speed requirements

Description: From Introduction: "This report represents an extension of the material presented in reference 4 to the case of the counterrotating turbine where the inter-stage stator is omitted and the second-stage rotor blade velocity is in the direction opposite to that of the first-stage rotor."
Date: March 18, 1958
Creator: Wintucky, William T. & Stewart, Warner L.
Item Type: Refine your search to only Report
open access

Application of a high-temperature static strain gage to the measurement of thermal stresses in a turbine stator vane

Description: From Introduction: "This report describes the high-temperature static strain gage and presents the results obtained in a determination of the thermal stresses in a turbine stator vane resulting from the temperature distribution obtained under steady-state conditions at rated speed and temperature of the engine."
Date: March 1958
Creator: Kemp, R. H.; Morse, C. R. & Hirschberg, M. H.
Item Type: Refine your search to only Report
open access

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
open access

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
open access

Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds

Description: Report presenting an investigation of the jet effects on several afterbody shapes of a single-engine fighter-airplane model in the 16-foot transonic tunnel at a range of Mach numbers and angles of attack. The afterbody-geometry variables were boattail angle, afterbody length, and base area. Results regarding evaluation of support interference, afterbody-pressure-distribution characteristics, and drag characteristics are provided.
Date: March 4, 1958
Creator: Norton, Harry T., Jr. & Swihart, John M.
Item Type: Refine your search to only Report
open access

Effect of a stringer on the stress concentration due to a crack in a thin sheet

Description: From Summary: "A coefficient is obtained for determining the effect of reinforcing stringer on the stress concentration factor at the tip of a crack in a thin sheet. The results are given for the case in which the stringer is intact and for the case in which the stringer is broken. In the first case the stress concentration factor for the stringer is also given."
Date: March 1958
Creator: Sanders, J. Lyell, Jr.
Item Type: Refine your search to only Report
open access

Effect of Distributed Granular-Type Roughness on Boundary-Layer Transition at Supersonic Speeds With and Without Surface Cooling

Description: Report presenting an investigation to determine the effect of a distributed granular-type roughness on boundary-layer transition at several temperatures. The roughness was not found to introduce any disturbances of significant magnitude to influence transition. Surface cooling did not increase the value of the critical roughness Reynolds number for a distributed granular-type roughness either.
Date: March 10, 1958
Creator: Braslow, Albert L.
Item Type: Refine your search to only Report
open access

Effect of jet temperature on jet-noise generation

Description: Report presenting an experimental investigation in order to determine the effect of jet temperature on jet-noise generation. Jet pressure ratios from 1.3 to 1.9 and temperature from 80 to 1000 degrees Fahrenheit. Results showed that sound power can be adequately predicted by the Lighthill parameter based on ambient temperature over the range of temperatures investigated.
Date: March 1958
Creator: Rollin, Vern G.
Item Type: Refine your search to only Report
open access

Effect of overheating on creep-rupture properties of M-252 alloy

Description: Report presenting a study on the influence of periodic overheats of 2-minutes duration to four different temperatures on the creep-rupture properties of M-252 alloy at 1500 degrees Fahrenheit. The purpose of the study was to provide information regarding the estimation of the effects of overheating on creep-rupture performance of gas-turbine parts. Results regarding normal rupture properties of experimental materials, overheats on heat HT-28, overheats on heats 837 and 43642, comparative effect… more
Date: March 1958
Creator: Rowe, John P. & Freeman, J. W.
Item Type: Refine your search to only Report
open access

Effect of Wall Cooling on Inlet Parameters of a Scoop Operating in a Turbulent Boundary Layer on a Flat or Conical Surface for Mach Numbers 2 to 10

Description: Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.
Date: March 1958
Creator: Beke, Andrew
Item Type: Refine your search to only Report
open access

The effects of a modified roll-command system on the flight-path stability and tracking accuracy of an automatic interceptor

Description: From Summary: "In order to improve the tracking characteristics of an automatic interceptor, a revised roll-command computer was tested both on an analog computer and in flight. This report presents flight-test results which indicate a significant improvement in flight-path stability and tracking accuracy. The modified roll computer was designed on the basis of previous analytical studies."
Date: March 4, 1958
Creator: Triplett, William C.
Item Type: Refine your search to only Report
open access

The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes

Description: Memorandum presenting a technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement the calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.
Date: March 24, 1958
Creator: Nielsen, Jack N.
Item Type: Refine your search to only Report
open access

The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes

Description: Memorandum describing a calculative technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.
Date: March 24, 1958
Creator: Nielsen, Jack N.
Item Type: Refine your search to only Report
open access

Effects of Canard Surface Size on Stability and Control Characteristics of Two Canard Airplane Configuration at Mach Numbers of 1.41 and 2.01

Description: Memorandum presenting an investigation in the supersonic pressure tunnel to determine the stability and control characteristics of two canard airplane configurations equipped with various sizes of canard control surfaces. Two wings of equal area but differing in plan form were provided. Results regarding longitudinal characteristics and lateral characteristics are provided.
Date: March 6, 1958
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
open access

Effects of Surface Roughness and Extreme Cooling on Boundary-Layer Transition for 15 Degrees Cone-Cylinder in Free Flight at Mach Numbers to 7.6

Description: Report presenting an investigation of three cone-cylinder bodies to obtain boundary-layer-transition data at very low ratios of wall to local stream temperature. Surface finishes at several levels of roughness height were tested. Results regarding the smooth body and rough bodies are provided.
Date: March 5, 1958
Creator: Rabb, Leonard & Krasnican, Milan J.
Item Type: Refine your search to only Report
open access

Experimental Investigation of the Effect of Circumferential Inlet Flow Distortion on the Performance of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages

Description: Memorandum presenting an investigation of the performance of a five-stage transonic research compressor with distorted inlet flow. Both overall performance and individual blade-row performance results over a range of compressor speeds and equivalent weight flows were obtained with three circumferential inlet flow-distortion patterns covering annular extents of 60, 120, and 180 degrees. Results regarding compressor-inlet conditions and overall performance and individual blade-row performance are… more
Date: March 5, 1958
Creator: Robbins, William H. & Glaser, Frederick
Item Type: Refine your search to only Report
open access

Experimental Lift-Drag Ratios for Two Families of Wing-Body Combinations at Supersonic Speeds

Description: Memorandum presenting experimental force and moment characteristics, including lift-drag ratios, which have been measured and briefly studied for two families of wing-body combinations. One family consisted of essentially arrow wings with half conical bodies. The other consisted of a fineness-ratio-12 body of revolution alone and with flat-plate triangular wings of aspect ratios ranging from 0.375 to 1.8.
Date: March 10, 1958
Creator: Jorgensen, Leland H.
Item Type: Refine your search to only Report
open access

Feasibility of Nose-Cone Cooling by the Upstream Ejection of Solid Coolants at the Stagnation Point

Description: Report presenting an investigation in a chemical jet at a stagnation temperature of 4,000 degrees Fahrenheit at a Mach number of 2.8 to determine the feasibility of cooling models by the ejection of a solid coolant at the stagnation point. A series of conical models were tested with glass, Lucite, nylon, Teflon, and Texolite rods as coolants. Results regarding the cooling properties of each of the materials are provided, and all materials performed adequately with the exception of Teflon.
Date: March 24, 1958
Creator: Kinard, William H.
Item Type: Refine your search to only Report
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