UNT Libraries Government Documents Department - 12,435 Matching Results

Search Results

prev Results: 8065 - 8088 next
open access

Some approximate methods for estimating the effects of aeroelastic bending of rocket-propelled model-booster combinations

Description: Report presenting methods for estimating the aeroelastic effects and structural requirements of rocket-propelled model-booster combinations that are nearly symmetrical. The methods differ principally in the manner in which booster stiffness, reference axis, and inertia loading are considered. Special conditions and accuracy for each of the three models are provided.
Date: March 27, 1953
Creator: Arbic, Richard G.; White, George & Gillespie, Warren, Jr.
Item Type: Refine your search to only Report
open access

Transonic wind-tunnel measurements of static lateral and directional stability and vertical-tail loads for a model with a 45 degree sweptback wing

Description: Report presenting an investigation to determine the vertical-tail loads and airplane characteristics in sideslip for a model of a swept-wing fighter-type airplane in the 16-foot transonic tunnel at a range of Mach numbers and angles of attack. Results regarding the effect of the unsealed vertical-tail root on airplane coefficients, directional and lateral stability, vertical-tail loads, effect of leading-edge chord-extensions on lateral and directional characteristics and on tail loads, and pit… more
Date: May 17, 1956
Creator: Hallissy, Joseph M., Jr.
Item Type: Refine your search to only Report
open access

Effect of leading-edge droop on the aerodynamic and loading characteristics of a 4-percent-thick unswept-wing-fuselage combination at transonic speeds

Description: Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the aerodynamic and loading characteristics of an unswept wing with a taper ratio of 0.5, an aspect ratio of 4, and NACA 65A004 airfoil sections parallel to the plane of symmetry. The results indicate that, below a Mach number of 0.94, leading-edge droop delayed the onset of leading-edge separation and moved the main wing-compression shock rearward.
Date: May 23, 1956
Creator: Schmeer, James W.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Description: Report presenting flight testing of a rocket-propelled model of a typical multiengine airplane configuration to obtain data on drag, stability, and nacelle performance. Data were obtained at a variety of Mach numbers, lift coefficients, and subsonic and supersonic speeds. Results regarding airplane performance, nacelle performance, longitudinal characteristics, and lateral characteristics are provided.
Date: September 2, 1955
Creator: Chapman, Rowe, Jr.
Item Type: Refine your search to only Report
open access

Some Notes on the Violent Lateral-Longitudinal Coupling Motions of the Douglas X-3 Airplane in Aileron Rolls

Description: Report presenting a study of the potentially large violent coupled motions encountered by the Douglas X-3 in flight. Testing indicated that the motions encountered appeared to be caused by the inclination of the principal axis below the flight path at the onset of rolling maneuvers and the existence of pitching moment due to side slip combined with a trim change near Mach number 1. Results regarding the effect of principal-axis inclination, effect of changes in directional stability, effect of … more
Date: May 17, 1956
Creator: Stone, Ralph W., Jr.
Item Type: Refine your search to only Report
open access

Maximum Altitude and Maximum Mach Number Obtained With the Modified Douglas D-558-II Research Airplane During Demonstration Flights

Description: "Flights to explore the high altitude and Mach number regions were made with the Douglas D-558-II research airplane in August 1951. Maximum pressure altitude recorded was 77,500 feet and the maximum geometric altitude obtained from radar data was 79,500 feet above sea level. The maximum Mach number obtained was 1.87. When a standard atmosphere is assumed, this value represents a true airspeed of 1238 miles per hour; or at the existing temperature, 3 degrees Fahrenheit above standard, this repre… more
Date: April 20, 1953
Creator: Dahlen, Theodore E.
Item Type: Refine your search to only Report
open access

Lift, drag, and static longitudinal stability characteristics of configurations consisting of three triangular wing panels and a body of equal length at Mach numbers from 3.00 to 6.28

Description: Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for three highly swept three-wing tailless configurations determined from tests at a range of Mach numbers and angles of attack.
Date: February 7, 1956
Creator: Savin, Raymond C. & Wong, Thomas J.
Item Type: Refine your search to only Report
open access

Two Experiments on Applications of the Transonic Area Rule to Asymmetric Configurations

Description: "Two experiments concerning the transonic area rule have shown that the wing of a configuration has a powerful effect as a dividing plate. The approximation of store plus interference wave drag (near a Mach number of 1) for underwing stores was more accurately made by considering the normal area development of the configuration above and below the wing separately instead of the total area development. Indenting a fuselage on only one side of the wing to allow for the exposed wing volume gave ap… more
Date: April 20, 1956
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
open access

A summary of results obtained during flight simulation of several aircraft prototypes with variable-stability airplanes

Description: Report presenting testing of two airplanes, the F6F-3 and F-86A, fitted with servo equipment for varying in flight the lateral and directional stability and handling characteristics and flown by test pilots to simulate the predicted dynamic behavior of six prototype airplanes. Results regarding the aerodynamic characteristics and pilot opinions for each plane are provided.
Date: May 25, 1956
Creator: McNeill, Walter E. & Creer, Brent Y.
Item Type: Refine your search to only Report
open access

Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel

Description: Memorandum presenting tests of a scale model of a B-36J/RF-84F tip-coupled airplane in the 19-foot pressure tunnel in order to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain an indication of the dynamic stability characteristics of the configuration. The variables studied in the investigation included skew angle of the fighter-bomber coupling, fighter longitudinal position, fighter and bomber loading, angle of sideslip, degrees of body freedom, and the… more
Date: March 15, 1956
Creator: Neely, Robert H.
Item Type: Refine your search to only Report
open access

An Experimental Investigation of the Effects of Several Diffusers and Diffuser-Entrance-Mixing-Section Combinations on the Power Requirements of a 4 1/2-Inch by 4 1/2-Inch Slotted Transonic Wind Tunnel

Description: Report presenting testing of a 4.5 inch by 4.5 inch tunnel with slots in two opposite walls in order to determine the effects of various slot exit shapes, mixing sections, and diffusers on power requirements. Some of the data obtained included measurements of the pressure ratio required to operate the tunnel, the effects of auxiliary bleed flow, diffuser static-pressure ratios and distributions, and diffuser total pressure distributions.
Date: June 5, 1956
Creator: Dennard, John S.
Item Type: Refine your search to only Report
open access

Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Description: This report details a study that was conducted by the U.S. Naval Air Development Center to "determine the feasibility of several airborne magnetic mine-sweeping methods. The advantages of a satisfactory airborne method are greater safety and speed than are possible with existing surface methods." The configurations and results of the double Q-sweep, the modified double-catenary sweep, and the M-sweep are examined.
Date: December 1, 1955
Creator: Shanks, Robert E.
Item Type: Refine your search to only Report
open access

Preflight and flight-test investigation of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin engine ram-jet vehicle

Description: Report presenting an investigation conducted by means of preflight and flight tests to determine the performance of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin-engine ramjet test vehicle. Data were obtained over a range of Mach numbers. Although a successful flight test was carried out, the performance obtained from preflight testing was below theoretical values.
Date: May 31, 1956
Creator: Trout, Otto F., Jr. & Kennedy, Thomas L.
Item Type: Refine your search to only Report
open access

Investigation at high subsonic speeds of some effects of sideslip on the aerodynamic loads on finned and unfinned bodies mounted from the wing of a swept-wing-fuselage model

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel at a range of Mach numbers to determine the aerodynamic loads on finned and unfinned bodies in the presence of a swept wing. A tip-mounted body at 1.04 semispan and an underwing pylon-mounted body at 0.33 semispan were investigated. Results regarding the body loading characteristics and effect of angle of attack are provided.
Date: April 26, 1956
Creator: King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Methods for calculating thrust augmentation and liquid consumption for various turbojet-afterburner fuels

Description: "Methods are presented for calculating net thrust using air specific-impulse data for various fuels. Nomographic solutions are given to adapt the methods to turbojet-afterburner calculations. These nomographs can be used to compute net thrusts obtained by expanding exhaust gases to either a Mach number of 1.0 or the ambient static pressure at the nozzle exit. Thermodynamic data for several fuels are also presented" (p. 1).
Date: October 10, 1956
Creator: Morris, James F.
Item Type: Refine your search to only Report
open access

Factors Controlling Air-Inlet Flow Distortions

Description: Memorandum presenting a study of several typical air induction systems for modern aircraft, which indicates that flow distortions of about-pipe-flow magnitudes can be expected at near-optimum inlet-engine matched air-flow conditions and at small angles of attacks. The distortions may be seriously increased by operation at large angles of attack or yaw, or by supercritical operation of the inlets. Boundary-layer bleed, duct overexpansion and contraction, and freely rotating fans appear promising… more
Date: April 6, 1956
Creator: Sterbentz, William H.
Item Type: Refine your search to only Report
open access

Some Examples of the Applications of the Transonic and Supersonic Area Rules to the Prediction of Wave Drag

Description: Report presenting a comparison of the experimental wave drags of bodies and wing-body combinations over a wide range of Mach numbers with the computed drags utilizing a 24-term Fourier series application of the supersonic area rule and results of equivalent-body tests. The equivalent-body technique was found to provide a good method for predicting the wave drag of certain wing-body combinations at and below a Mach number of 1, but becomes misleading at Mach numbers greater than 1.
Date: March 20, 1957
Creator: Nelson, Robert L. & Welsh, Clement J.
Item Type: Refine your search to only Report
open access

Free-flight investigation over a Mach number range from 0.74 to 1.43 at lift coefficients from minus 0.15 to 0.75 of an airplane-configuration model having a 52.5 degree delta wing and a low swept horizontal tail

Description: Report presenting a free-flight investigation over a range of Mach numbers at a range of lift coefficients to determine the aerodynamic characteristics of an airplane-configuration model with a 52.5 degree delta wing and a low, swept horizontal tail. Results regarding time history, longitudinal trim, lift, drag, longitudinal static stability, side-force characteristics, and theoretical comparisons are provided.
Date: September 28, 1956
Creator: Kehlet, Alan B.
Item Type: Refine your search to only Report
open access

A preliminary investigation of the static stability characteristics of four airplane-like configurations at Mach numbers from 3.00 to 6.28

Description: Report presenting side-force and directional-stability characteristics of four airplane-like configurations determined at a range of Mach numbers and angles of sideslip at zero angle of attack. Two configurations had trapezoidal wing and tail surfaces and two had triangular wing and tail surfaces. The directional stability of the configurations generally decreased with increasing Mach number.
Date: March 26, 1956
Creator: Wong, Thomas J. & Gloria, Hermilo R.
Item Type: Refine your search to only Report
open access

Investigation of two-stage counterrotating compressor 2: first-rotor blade-element performance

Description: Report presenting an analysis of the blade-element performance of a highly loaded transonic rotor with double-circular-arc blades. The rotor was purposely loaded beyond the prudent level for exploratory purposes. Results regarding the radial-distribution plots, blade-element data, element blade-to-blade loss variation, and a comparison of steady-state and hot-wire measurements are provided.
Date: October 5, 1956
Creator: Wright, Linwood C. & Wilcox, Ward W.
Item Type: Refine your search to only Report
open access

A Brief Investigation of the Effect of Waves on the Take-Off Resistance of a Seaplane

Description: Report presenting testing to determine the resistance of a model of a seaplane with a length-beam ratio of 15 and a wing loading of 120 pounds per square foot was determined in smooth water and three wave heights under various conditions of load, speed, elevator setting, angle of dead rise, and center-of-gravity position.
Date: April 24, 1956
Creator: Mottard, Elmo J.
Item Type: Refine your search to only Report
open access

Effects of Reynolds number and leading-edge shape on the low-speed longitudinal stability of a 6-percent-thick 45 degree sweptback wing

Description: Report presenting force-test data showing the effects of change in leading-edge radius on the low-speed longitudinal stability of a 6-percent-thick 45 degree sweptback wing of aspect ratio 3 for several ranges of Mach and Reynolds numbers. The results indicated that as the airfoil sections were thinned at the nose, separation effects occurred at lower values of lift coefficient.
Date: April 18, 1956
Creator: Schneider, William C.
Item Type: Refine your search to only Report
open access

Presentation on facility problems in high-temperature structures research

Description: Presentation regarding the current general approach of NACA to the problems of high-temperature structures research facilities. The field is rapidly changing and many investigations discussed are still in the exploratory stage. The main areas of importance are heating, loading, and structural model accommodation as well as having the proper research equipment and heat exchangers.
Date: March 27, 1956
Creator: Purser, Paul E. & Heldenfels, Richard R.
Item Type: Refine your search to only Report
open access

Experimental investigation of air-cooled turbine rotor blade temperatures in a turbojet engine operating at turbine-inlet temperatures up to 2580 R and altitudes of 50,000 and 60,000 feet

Description: Report presenting temperature data for air-cooled turbine rotor blades obtained during an experimental investigation conducted in an altitude test chamber to determine some of the problems pertinent to the operation of air-cooled turbojet engines at a range of turbine-inlet temperatures. Results regarding local blade temperatures, effect of blade-inlet cooling-air temperature on average rotor blade temperature with two types of cooling, effect of cooling-air flow on average rotor blade temperat… more
Date: August 20, 1956
Creator: Slone, Henry O.; Cochran, Reeves P. & Dengler, Robert P.
Item Type: Refine your search to only Report
Back to Top of Screen