UNT Libraries Government Documents Department - 437 Matching Results

Search Results

Results: 1 - 24 next
open access

The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Description: Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.
Date: December 17, 1954
Creator: Abramovitz, Marvin & Van Dyke, Rudolph D., Jr.
Item Type: Refine your search to only Report
open access

Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal accelerat… more
Date: December 31, 1952
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Belsley, Steven E.
Item Type: Refine your search to only Report
open access

Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Description: From Introduction: "The analysis of flight data in the present report is, to a large extent, based on analyses and information contained in references 1 and 2 for wing deflections, reference 3 for horizontal-tail parameters, reference 4 for airplane lift-curve slopes and angles of zero lift, and reference 5 for wing centers of pressure."
Date: December 1957
Creator: Aiken, William S., Jr.
Item Type: Refine your search to only Report
open access

Preliminary Low-Speed Wind-Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions Near Airplane Wings

Description: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be tr… more
Date: December 27, 1954
Creator: Alford, William J., Jr.; Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
open access

Chemical and Physical Properties of Modified Hi-Cal-2

Description: Memorandum presenting some physical and chemical properties of a sample of modified Hi-Cal-2. Some of the results obtained include chemical analysis, heat of combustion, density, freezing point, self-ignition temperature, flash point, oxygen stability, water stability test, infrared spectrum, and vapor pressure and decomposition are provided.
Date: December 1955
Creator: Allen, Harrison, Jr.; McDonald, Glen E. & Pusanski, Barbara J.
Item Type: Refine your search to only Report
open access

Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1

Description: Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successfu… more
Date: December 28, 1956
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Description: Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.
Date: December 28, 1956
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

Preliminary investigation of effect on performance of dividing conical-spike nose inlets into halves at Mach numbers 1.5 to 2.0

Description: Inserting a splitter plate in the subsonic diffuser caused a pressure-recovery loss of about 1 percent for an inlet with a long nearly constant-area throat section. The loss was due to the increased surface area. Another inlet, which had a comparatively rapid area increase immediately after the throat, experienced pressure-recovery losses of 5 and 6 percent at Mach numbers of 1.8 and 2.0, respectively, and about 1 percent at Mach 1.5.
Date: December 19, 1955
Creator: Allen, John L.
Item Type: Refine your search to only Report
open access

On the Calculation of Shallow Shells

Description: This paper considers a sufficiently thin shallow shell of nonzero Gaussian curvature. It also presents a system of symmetrically constructed differential equations, constructed by the mixed method through the stress function and the displpacement function.
Date: December 1956
Creator: Ambartsumyan, S. A.
Item Type: Refine your search to only Report
open access

Effect of Concentration on Ignition Delays for Various Fuel-Oxygen-Nitrogen Mixtures at Elevated Temperatures

Description: Note presenting measurements of ignition delays for mixtures of ethane, n-butane, isobutane, hydrogen, or propane with oxygen and nitrogen using a flow system with two experimental procedures. Delays were measured over a range of temperatures for each gas. Results regarding a comparison among fuels and effect of experimental procedure on absolute values of ignition delay are provided.
Date: December 1956
Creator: Anagnostou, E.; Brokaw, R. S. & Butler, J. N.
Item Type: Refine your search to only Report
open access

Longitudinal stability characteristics of the Convair YF-102 airplane determined from flight tests

Description: Report presenting an analysis of the longitudinal stability characteristics of the cambered-wing version of the Convair YF-102 airplane at a range of Mach numbers and altitudes. Results regarding longitudinal trim, stall maneuvers, dynamic longitudinal stability, maneuvering stability, stability and control effectiveness parameters, and artificial-feel system are provided.
Date: December 13, 1956
Creator: Andrews, William H.; Sisk, Thomas R. & Darville, Robert W.
Item Type: Refine your search to only Report
open access

Lateral Motions Encountered with the Douglas D-558-II All-Rocket Research Airplane During Exploratory Flights to a Mach Number of 2.0

Description: Memorandum presenting flight tests performed with the Douglas D-558-II research airplane in order to determine the lateral handling characteristics in straight flight at supersonic speeds. It primarily describes the lateral motions obtained at moderate and low angles of attack during a preliminary survey in pushovers and straight flight at supersonic Mach numbers up to about 2.0 at altitudes between 50,000 and 70,000 feet.
Date: December 17, 1954
Creator: Ankenbruck, Herman O. & Wolowicz, Chester H.
Item Type: Refine your search to only Report
open access

Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotor blade-setting angles at solidities. of 1.0 and 0.5

Description: Report presenting testing of a medium-camber compressor rotor with particular NACA blades in a low-speed 28-inch test blower. Testing was made at solidities of 1.0 and 0.5 without guide vanes or stators over a wide range of blade-setting angles and quantity flow rates. Results regarding overall rotor performance, comparison between measured and estimated section efficiencies near design angle of attack, comparison between low-speed rotor and cascade turning angles, and detailed blade section pe… more
Date: December 27, 1954
Creator: Ashby, George C., Jr.
Item Type: Refine your search to only Report
open access

Operating Characteristics of an Acceleration Restrictor as Determined by Means of a Simulator

Description: Note presenting the operating characteristics of an acceleration restrictor which limits the normal acceleration of an airplane in maneuvers determined from tests on a simulator. The simulator consisted of a control stick geared to a magnetic brake unit and an analog computer which simulated the dynamic characteristics of the airplane.
Date: December 1954
Creator: Assadourian, Arthur
Item Type: Refine your search to only Report
open access

Downwash Behind a Triangular Wing of Aspect Ratio 3 - Transonic Bump Method

Description: Report presenting an investigation of the lift, drag, pitching-moment, and downwash characteristics of a triangular wing of aspect ratio 3 with an NACA 63A006 section. Downwash was measured by using an all-movable horizontal tail at five locations. Results regarding basic wing characteristics and stability contribution of the tail are also provided.
Date: December 1, 1953
Creator: Axelson, John A.
Item Type: Refine your search to only Report
open access

Flight Test of a Radial-Burning Solid-Fuel Ram Jet

Description: Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.
Date: December 10, 1952
Creator: Bartlett, Walter A., Jr. & Dettwyler, H. Rudolph
Item Type: Refine your search to only Report
open access

Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration

Description: Report presenting an investigation of the static stability and control characteristics of a scale model of a preliminary Bell X-5 airplane design in the landing configuration with and without dive brakes. Results regarding the effects of slats, flaps, landing gear, gear doors, dive brakes and gap at the wing root are provided.
Date: December 18, 1950
Creator: Becht, Robert E.
Item Type: Refine your search to only Report
open access

Heat transfer and recovery temperatures on a sphere with laminar, transitional, and turbulent boundary layers at Mach numbers of 2.00 and 4.15

Description: Report presenting an investigation of the pressure and equilibrium-temperature distributions on a sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic heat transfer was measured on a sphere at Mach number 2.00 and on a hemisphere-cylinder at Mach number 4.15. Results regarding pressure distributions, equilibrium and recovery temperatures, heat-transfer coefficients, and effect of roughness on transition are provided.
Date: December 1957
Creator: Beckwith, Ivan E. & Gallagher, James J.
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

Effects of additives on pressure limits of flame propagation of propane-air mixtures

Description: Report presenting a study of seven additives in 0.5-volume-percent concentration for their effects on the low-pressure limits of flame propagation of propane-air mixtures. Limits were measured in a flame tube of new design. Results regarding propane-air mixtures, propane-air-additive mixtures, and flame propagation qualities are provided.
Date: December 18, 1953
Creator: Belles, Frank E. & Simon, Dorothy M.
Item Type: Refine your search to only Report
open access

Variation of the pressure limits of flame propagation with tube diameter for propane-air mixtures

Description: An investigation was made of the variation of the pressure limits of flame propagation with tube diameter for quiescent propane with tube diameter for quiescent propane-air mixtures. Pressure limits were measured in glass tubes of six different inside diameters, with a precise apparatus. Critical diameters for flame propagation were calculated and the effect of pressure was determined. The critical diameters depended on the pressure to the -0.97 power for stoichiometric mixtures. The pressure d… more
Date: December 5, 1951
Creator: Belles, Frank E. & Simon, Dorothy M.
Item Type: Refine your search to only Report
open access

Lift and drag characteristics of the Douglas X-3 research airplane obtained during demonstration flights to a Mach number of 1.20

Description: Report presenting lift and drag data obtained during the Douglas X-3 airplane. The data covered the Mach number range from 0.82 to 1.20 with considerable variation in lift. A comparison of the flight data with data from wind-tunnel and rocket-model tests shows that the model tests adequately predict the performance of the airplane.
Date: December 6, 1954
Creator: Bellman, Donald R. & Murphy, Edward D.
Item Type: Refine your search to only Report
Back to Top of Screen