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A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition

Description: Report describing the effects of an area of roughness on the velocity and turbulence measurements of an airfoil. It details the effects of the size, location, and height of the roughness on the Reynolds number. From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition."
Date: 1958
Creator: Horton, Elmer A. & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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
Partner: UNT Libraries Government Documents Department
open access

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
Partner: UNT Libraries Government Documents Department
open access

Qualitative Simulator Study of Longitudinal Stick Forces and Displacements Desirable During Tracking

Description: In this study in which an airplane simulator with one degree of freedom (pitch) was used, results were determined for three conditions of airplane dynamics. For an undamped natural frequency of 1/2 cps with a damping ratio of 0.18 and for an undamped natural frequency of 1 cps with a damping ratio of 0.11, moderate longitudinal stick forces and displacements were desired.
Date: February 1958
Creator: Faber, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental measurements of the effects of airplane motions on wing and tail angles of attack of a swept-wing bomber in rough air

Description: Report presenting flight test data obtained from a large swept-wing bomber airplane in flight through rough air at 5,000 feet to determine the effects of vertical translation and pitching motions on the angles of attack of the wing and tail. The results indicate that the motions, particularly the pitching motions, significantly amplify the angles of attack of the wing and tail for the test airplane.
Date: August 1958
Creator: Engel, Jerome N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Effects of Atmospheric Turbulence and Moderate Maneuvers on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade

Description: Note presenting flight tests conducted with a medium-size single-rotor helicopter, of which one blade was equipped with strain gages, to determine the relative effects of atmospheric turbulence and moderate maneuvers on the periodic rotor blade moments. The results indicate no significant increase in the total blade moments due to atmospheric turbulence of moderate pull-up maneuvers which produced center-of-gravity acceleration increments of less than about 0.15g. Results regarding moment recor… more
Date: February 1958
Creator: Ludi, LeRoy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of experimental heat-transfer measurements in turbulent flow for a Mach number range from 0.87 to 5.05

Description: Report presenting heat-transfer measurements made in turbulent flow at a variety of Mach and Reynolds numbers through the use of an axially symmetric annular nozzle consisting of an inner shaped center body and an outer cylindrical sleeve. The results are presented as Stanton number and recovery factor as a function of Reynolds number. Stanton number was found to decrease with an increase in Reynolds number and usually decreases with an increase in Mach number.
Date: May 1958
Creator: Brevoort, Maurice J. & Arabian, Barbara D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Procedure for calculating flutter at high supersonic speed including camber deflections, and comparison with experimental results

Description: Report presenting a method that can be used at high supersonic Mach numbers for calculating the flutter speed of wings with camber in their deflection modes. It is used to calculate the flutter speed of some wings that had been tested at Mach numbers of 1.3 and 3.0. Theoretical comparisons of the tested wings are also provided.
Date: September 1958
Creator: Morgan, Homer G.; Huckel, Vera & Runyan, Harry L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A theoretical analysis of the effect of engine angular momentum on longitudinal and directional stability in steady rolling maneuvers

Description: From Summary: "The effect of engine momentum on the longitudinal and directional stability of aircraft in steady rolling maneuvers has been investigated. The results presented indicate that the gyroscopic moments produced on the aircraft by a rotating engine in rolling maneuvers can have an appreciable effect on the range of rolling velocities for which longitudinal or directional instability might occur."
Date: April 1958
Creator: Gates, Ordway B., Jr. & Woodling, C. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of axial and normal force characteristics of skewed nozzles

Description: Report presenting an investigation of normal forces produced by several skewed nozzles and a series of ejectors with skewed shrouds discharging into quiescent air as conducted with cold air at jet total-pressure ratios up to 6.5. Nozzles were terminated at angles of 30 degrees, 45 degrees, 60 degrees, and 75 degrees relative to the normal plane. Results regarding basic data, effect of skew angle and indentation, and effect of a skewed shroud are provided.
Date: September 1958
Creator: Carter, David J., Jr. & Vick, Allen R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements in a Shock Tube of Heat-Transfer Rates at the Stagnation Point of a 1.0-Inch-Diameter Sphere for Real-Gas Temperatures Up to 7,900 R

Description: Note presenting heat-transfer rates at the stagnation point of 1.0-inch-diameter glass spherical models in shock-tube flows in air which correspond to free-flight conditions between Mach numbers of 6.4 and 13.9 with stagnation temperatures up to 7900 degrees R. The heat-transfer rates were determined from measurements of the surface-temperature change with time of a thin-film-platinum resistance thermometer.
Date: August 1958
Creator: Sabol, Alexander P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of some phenomena relating to aural detection of airplanes

Description: Report presenting an investigation to determine the effect of modifications made in the propulsion system of a single-engine airplane to substantially reduce its external noise, and, thereby, to evaluate the significance of the external noise level of an airplane with regard to the problem of its detection by ground observers.
Date: September 1958
Creator: Hubbard, Harvey H. & Maglieri, Domenic J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of the proximity of the wing first-bending frequency and the short-period frequency on the airplane dynamic-response factor

Description: Report presenting a study of the effect of the frequency of the lowest wing structural mode on the airplane center-of-gravity dynamic-response factor was made my employing simplified transfer functions.
Date: June 1958
Creator: Huss, Carl R. & Donegan, James J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Graphs of reduced variables for computing histories of vaporizing fuel drops, and drop histories under pressure

Description: Report presenting an investigation with two purposes: to obtain a simplified calculation technique for replacing complicated automatic computer calculations and to obtain experimental data for single droplets vaporizing at pressures greater than 1 atmosphere and to check the histories against experimental data.
Date: September 1958
Creator: Borman, G. L.; El Wakil, M. M.; Uyehara, O. A. & Myers, P. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of wake effects on hydro-skis

Description: Report presenting an experimental investigation to determine the effects of planing in a wake on the forces of a planing surface and to locate desirable positions in the wake with regard to the lift and lift-drag ratio of the planing surface. Two combinations of hydro-skis were tested: one with two in tandem and one with three arranged with one hydro-ski in the front and two in the back. Results indicated that the rear hydro-ski in tandem arrangement could have large increases in lift coefficie… more
Date: May 1958
Creator: McBride, Ellis E. & Fisher, Lloyd J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low tip Mach number stall characteristics and high tip Mach number compressibility effects on a helicopter rotor having an NACA 0009 tip airfoil section

Description: Report presenting an investigation conducted on the helicopter test tower to determine experimentally the low tip Mach number stall and high tip Mach number drag divergence characteristics of a helicopter rotor with an NACA 0009 tip airfoil section. Results regarding rotor hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are provided.
Date: July 1958
Creator: Powell, Robert D., Jr. & Carpenter, Paul J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Impact Loads of a -20 Degree Dead-Rise Inverted-V Model and Comparisons With Loads of a Flat-Bottom Model

Description: Note presenting a model with an inverted-V transverse shape and a dead-rise angle of -20 degrees as part of a study of hydrodynamic impact loads on chine-immersed bodies. A series of fixed-trim impacts of the inverted-V model were made in smooth water over a wide range of trim and initial flight-path angles at a beam-loading coefficient of 19.15 with a few impacts at beam-loading coefficients of 27.90 and 36.07. The data are presented in tables and in figures as variations of loads and motions … more
Date: August 1958
Creator: Edge, Philip M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Simplified T-Tail Oscillating in Yaw About the Fin Midchord

Description: Report presenting some experimental measurements of aerodynamic forces and moments on a simple T-tail configuration oscillating in yaw about an axis through the midchord of the vertical fin. Coefficients regarding the rolling moment of the horizontal stabilizer, rolling moment, yawing moment, and side force of the tail are provided.
Date: September 1958
Creator: Clevenson, Sherman A. & Leadbetter, Sumner A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the high-subsonic static longitudinal stability characteristics of several wing-body configurations designed for high lift-drag ratios at a Mach number of 1.4

Description: Report presenting testing in the high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at Mach number 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65-A series airfoil sections. Results regarding longitudinal stability, lift, drag, and lift-drag ratio are provided.
Date: July 1958
Creator: Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Effects of Retreating-Blade Stall on Bending and Torsional Moments Encountered by a Helicopter Rotor Blade

Description: Note presenting flight tests conducted with a medium-size single-rotor helicopter, one blade of which was equipped with strain gages, to determine the effects of retreating-blade stall on the rotor blade bending and torsional moments during high-speed flight and pull-up maneuvers. The results indicate that retreating-blade stall has a substantial effect on the periodic rotor blade moments. Results regarding the effect of stall in steady forward flight and effect of stall in pull-up maneuvers ar… more
Date: May 1958
Creator: Ludi, LeRoy H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of Ring-Stiffened Circular Cylinders Subjected to a Transverse Shear Load

Description: "Thirty-four circular cylinders stiffened by heavy rings were loaded to failure in combined bending and shear with a transverse shear load. The results are presented in the form of an interaction curve which is applicable to the design of ring-stiffened cylinders that fail as a result of local buckling" (p. 1).
Date: September 1958
Creator: Peterson, James P. & Updegraff, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed experimental determination of the effects of leading-edge radius and profile thickness on static and oscillatory lateral stability derivatives for a delta wing with 60 degrees of leading-edge sweep

Description: Report presenting an investigation to determine the effects of leading-edge radius and profile thickness on the oscillatory lateral stability derivatives for a series of delta wings with 60 degrees of leading-edge sweep. The wings were oscillated in yaw about their vertical axes. Results indicated that there were noticeable decreases in all the derivatives due to increase in leading-edge radius at angles of attack above approximately 12 degrees.
Date: July 1958
Creator: Fletcher, Herman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Vibratory Bending and Torsional Stresses on a Modified Supersonic Propeller for Forward Mach Numbers up to 0.95

Description: Note presenting vibratory stress measurements obtained in flight on a modified supersonic propeller for forward mach numbers up to 0.95. The magnitude of the vibratory bending stress was low in relation to the strength of the material throughout the flight range of the airplane. Results of a propeller feathering operation at a Mach number of 0.95 indicated no excessive stresses.
Date: June 1958
Creator: O'Bryan, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Propeller Position and Overlap on the Slipstream Deflection Characteristics of a Wing-Propeller Configuration Equipped With a Sliding and Fowler Flap

Description: Report of an investigation in a static-test facility to determine some of the effects of propeller position and overlap on the slipstream deflection characteristics of a configuration equipped with a sliding and Fowler flap. An investigation of a leading-edge slat, nacelle size, flap segmentation, and number of propellers was also conducted. Results regarding the effect of number of propellers, effect of vertical position of propeller, effect of extending nacelles through flaps, effect of chord… more
Date: September 1958
Creator: Hayes, William C., Jr.; Kuhn, Richard E. & Sherman, Irving R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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