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Effects of Canard Surface Size on Stability and Control Characteristics of Two Canard Airplane Configuration at Mach Numbers of 1.41 and 2.01
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
System:
The UNT Digital Library
Investigation of a High-Flow Transonic-Compressor Inlet Stage Having a Hub-Tip Radius of 0.35
Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.
Date:
March 6, 1958
Creator:
Felix, A. Richard
System:
The UNT Digital Library
Investigation of the Longitudinal Aerodynamic Characteristics of a Trapezoidal-Wing Airplane Model With Various Vertical Positions of Wing and Horizontal Tail at Mach Numbers of 1.41 and 2.01
Report presenting an investigation in the supersonic pressure tunnel to determine the effects of various vertical positions of a wing and horizontal tail on the static longitudinal aerodynamic characteristics of a trapezoidal wing model. Results regarding effect of wing vertical position and tail-on characteristics are provided.
Date:
March 6, 1958
Creator:
Foster, Gerald V.
System:
The UNT Digital Library
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
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.
System:
The UNT Digital Library
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
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 provided.
Date:
March 5, 1958
Creator:
Robbins, William H. & Glaser, Frederick
System:
The UNT Digital Library
An Investigation of the Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane With Alternate Nose Configurations With and Without Wing Fuel Tanks, TED No. NACA AD 395
"A supplementary investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/24-scale model of the Grumman F11F-1 airplane to determine the spin and recovery characteristics with alternate nose configurations, the production version and the elongated APS-67 version, with and without empty and full wing tanks. When spins were obtained with either alternate nose configuration, they were oscillatory and recovery characteristics were considered unsatisfactory on the basis of the fact that very slow recoveries were indicated to be possible. The simultaneous extension of canards near the nose of the model with rudder reversal was effective in rapidly terminating the spin" (p. 1).
Date:
March 5, 1958
Creator:
Bowman, James S., Jr.
System:
The UNT Digital Library
Performance of a Two-Dimensional Cascade Inlet at a Free-Stream Mach Number of 3.05 and at Angles of Attack of -3 Degrees, 0 Degrees, 3 Degrees, and 6 Degrees
Memorandum presenting an investigation of a double-ramp cascade inlet at Mach number 3.05 in order to determine the penalties associated with decreasing the length of inlets by means of cascades. Total-pressure recovery and profile distortion of the cascade inlet were compared with a similar single-passage inlet that captured the same mass flow.
Date:
March 5, 1958
Creator:
Woollett, Richard R. & Ferguson, Harold M.
System:
The UNT Digital Library
Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds
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.
System:
The UNT Digital Library
The effects of a modified roll-command system on the flight-path stability and tracking accuracy of an automatic interceptor
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.
System:
The UNT Digital Library
Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: lateral-directional characteristics of a triangular wing and canard
Report presenting the results of an investigation of the static lateral-directional stability characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for various combinations of the canard, body, wing, and vertical tail. Data were obtained at a variety of angles of attack, sideslip angles, and canard angles.
Date:
March 4, 1958
Creator:
Peterson, Victor L. & Menees, Gene P.
System:
The UNT Digital Library
Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer
Report using an analog computer to study the effects of aerodynamic parameters on the ability of a pilot to control a hypersonic research airplane capable of flight at very high altitudes. The results, which are based on pilot opinion of the difficulty of the control task, are illustrated by time histories of angle of attack, angle of sideslip, and roll angle. The basic airplane configuration was generally found to be unflyable and the arrangement of the information on the pilot's display was found to have an important influence on the control task.
Date:
March 4, 1958
Creator:
Sherman, Windsor L.; Faber, Stanley & Whitten, James B.
System:
The UNT Digital Library
A flight study of longitudinal-control-system dynamic characteristics by the use of a variable-control-system airplane
Report presenting flight tests with an airplane equipped to vary the longitudinal-control-system dynamic characteristics over a wide range. Control is obtained through a stabilizer force-command position-feedback longitudinal-control system. Results at a Mach number of 0.80 at 35,000 feet altitude, Mach number of 0.35 at 5,000 feet altitude, and normal-acceleration response are provided.
Date:
March 3, 1958
Creator:
McFadden, Norman M.; Pauli, Frank A. & Heinle, Donovan R.
System:
The UNT Digital Library
Static Longitudinal and Lateral Stability and Control Characteristics of a Model of a Swept-Wing Fighter-Bomber-Type Airplane With a Top Inlet at Mach Numbers From 1.6 to 2.35
"Static longitudinal and lateral stability characteristics of a swept-wing fighter-bomber airplane model with a top inlet have been determined experimentally. In addition, vertical-tail effectiveness, spoiler effectiveness, effects of several store configurations, and effects of mass flow were investigated. Tests were made at Mach numbers of 1.6, 1.8, 2.0, 2.2, and 2.35 and Reynolds numbers, based upon mean aerodynamic chord, of between 2.0x10(exp 6) and 2.5x10(exp 6)" (p. 1).
Date:
March 3, 1958
Creator:
Gnos, A. Vernon & Kurkowski, Richard L.
System:
The UNT Digital Library
Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957
"A summary of the locations, extents, and intensities of turbulent areas encountered during a flight investigation of the jet stream is presented. The data were obtained from NACA VGH time-history records" (p. 1).
Date:
March 3, 1958
Creator:
Copp, Martin R.
System:
The UNT Digital Library
Analysis of stresses and deflections in a disk subjected to gyroscopic forces
From Summary: "Results are presented in dimensionless form suitable for design purposes. The method for solving the problem of a disk of variable thickness with a temperature gradient is also presented."
Date:
March 1958
Creator:
Hirschberg, M. H. & Mendelson, A.
System:
The UNT Digital Library
An Analysis of the Optimization of a Beam Rider Missile System
"The paper begins with a discussion of the optimum system and the corresponding minimum error. A brief discussion of this miss as a function of the parameters which determine it is then given" (p. 2).
Date:
March 1958
Creator:
Shinbrot, Marvin & Carpenter, Grace C.
System:
The UNT Digital Library
Application of a high-temperature static strain gage to the measurement of thermal stresses in a turbine stator vane
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.
System:
The UNT Digital Library
Approximations for the thermodynamic and transport properties of high-temperature air
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
System:
The UNT Digital Library
Drop-size distributions for impinging-jet breakup in airstreams simulating the velocity conditions in rocket combustors
Report presenting drop-size-distribution data obtained for heptane sprays produced by pairs of impinging jets in airstreams over ranges of orifice diameter, liquid-jet velocity, and velocity difference between the airstream and the liquid jet.
Date:
March 1958
Creator:
Ingebo, Robert D.
System:
The UNT Digital Library
Effect of a stringer on the stress concentration due to a crack in a thin sheet
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.
System:
The UNT Digital Library
Effect of jet temperature on jet-noise generation
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.
System:
The UNT Digital Library
Effect of overheating on creep-rupture properties of M-252 alloy
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 effects of overheating on S-816, HS-31, and M-252 alloys, mechanism of damage from overheating, interpretation of results in terms of overheating in a turbine, and some limitations of results are provided.
Date:
March 1958
Creator:
Rowe, John P. & Freeman, J. W.
System:
The UNT Digital Library
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
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
System:
The UNT Digital Library
The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube
"Ideally, the reflection of a shock from the closed end of a shock tube provides, for laboratory study, a quantity of stationary gas at extremely high temperature. Because of the action of viscosity, however, the flow in the real case is not one-dimensional, and a boundary layer grows in the fluid following the initial shock wave. In this paper simplifying assumptions are made to allow an analysis of the interaction of the shock reflected from the closed end with the boundary layer of the initial shock afterflow. The analysis predicts that interactions of several different types will exist in different ranges of initial shock Mach number" (p. 1).
Date:
March 1958
Creator:
Mark, Herman
System:
The UNT Digital Library