UNT Libraries Government Documents Department - 196 Matching Results

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Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale … more
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Item Type: Refine your search to only Report
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Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51

Description: Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date: June 23, 1958
Creator: Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
Item Type: Refine your search to only Report
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Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines

Description: Memorandum presenting seven injectors of four different types that were tested for use with JP-4-oxygen-fluorine propellant combinations. By using the best of the injectors, high characteristic velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date: June 11, 1958
Creator: Nored, Donald L. & Douglass, Howard W.
Item Type: Refine your search to only Report
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Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65

Description: Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.
Date: June 30, 1958
Creator: Turner, Kenneth L. & Appich, W. H., Jr.
Item Type: Refine your search to only Report
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Maneuver Performance of Interceptor Missiles

Description: "From these preliminary wind-tunnel tests of interceptor missile configurations and the analysis of point defense against ballistic missiles, it is concluded that adequate aerodynamic lift is readily available and should be utilized when operating under high-dynamic-pressure conditions and that more work should be done on controls, either aerodynamic or reaction type, so that the configurations may be trimmed to the angles of attack required to develop the necessary turning force" (p. 5).
Date: June 27, 1958
Creator: Stone, David G.
Item Type: Refine your search to only Report
open access

Exploratory wind-tunnel investigation to determine the lift effects of blowing over flaps from nacelles mounted above the wing

Description: Report presenting an exploratory wind-tunnel investigation to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model with a delta wing of aspect ratio 3. The results indicate that the values of jet-circulation lift coefficient larger than the jet reaction were produced with blowing over flaps fro nacelles mounted above the wing. Results regarding lift coefficients, pitching-moment coefficients, and drag coefficients are provided.
Date: June 1958
Creator: Riebe, John M. & Davenport, Edwin E.
Item Type: Refine your search to only Report
open access

Effect of Dissociation on Exhaust-Nozzle Performance

Description: Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Net jet thrusts for equilibrium flow were three to five times that for frozen flow at Mach 10 for the three fuels cited, a hydrocarbon, hydrogen, and pentaborane. Results regarding dissociation energies, reaction rate, residence time, and estimated minimum performance are provided.
Date: June 11, 1958
Creator: Reynolds, T. W.
Item Type: Refine your search to only Report
open access

An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers From 3.0 to 6.3

Description: Memorandum presenting static longitudinal stability and control characteristics of a flare-stabilized body of revolution employing a movable portion of the flare surface as a pitch control determined for a range of Mach numbers, angles of attack, and control deflections. The variation of lift coefficient with pitching-moment coefficient for the basic configuration with control undeflected was found to be essentially linear, and the stability to increase slightly with increasing Mach number.
Date: June 24, 1958
Creator: Gloria, Hermilo R.
Item Type: Refine your search to only Report
open access

Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58

Description: Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date: June 20, 1958
Creator: Hollinger, James A.
Item Type: Refine your search to only Report
open access

Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Item Type: Refine your search to only Report
open access

Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System

Description: Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date: June 25, 1958
Creator: Smith, Arthur L. & Grobman, Jack S.
Item Type: Refine your search to only Report
open access

The Prospects for Laminar Flow on Hypersonic Airplanes

Description: The factors which affect the extent of laminar flow on airplanes for hypersonic flight are discussed on the basis of the available data. Factors considered include flight Reynolds number, surface roughness, angle of attack, angle of leading-edge sweepback, and aerodynamic interference. Test data are presented for one complete configuration.
Date: June 27, 1958
Creator: Seiff, Alvin
Item Type: Refine your search to only Report
open access

Calculation of the Lateral Stability of a Directly Coupled Tandem-Towed Fighter Airplane and Correlation with Experimental Data

Description: "A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could t… more
Date: June 24, 1958
Creator: Shanks, Robert E.
Item Type: Refine your search to only Report
open access

Some Altitude Operational Characteristics of a Prototype Iroquois Turbojet Engine, COORD. NO. AF-P-6

Description: The evaluation of the altitude operational characteristics was part of the over-all investigation of the early developmental Iroquois engine. Engine steady-state windmilling characteristics were evaluated over a range of flight Mach numbers from 0.48 to 1.72 at altitudes of 35,000 and 50,000 feet. Engine altitude ignition limits were obtained over a range of flight Mach numbers from 0.5 to 1.5 with the standard engine ignition system and also with an oxygen boost system. A short investigation o… more
Date: June 17, 1958
Creator: Peters, Daniel J. & McAulay, John E.
Item Type: Refine your search to only Report
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
open access

Results of an experimental investigation of small viscous dampers

Description: Report presenting the results of an experimental investigation of several small viscous dampers. The characteristics of the dampers are presented in the form of the magnitudes of the damping forces and spring forces as a function of the maximum velocity of the piston. The results indicated that the temperature has a large effect on the force produced by the dampers and demonstrated the necessity for consideration of the heat generated and dissipated as a result of work done by the dampers.
Date: June 1958
Creator: Silveira, Milton A.; Maglieri, Domenic J. & Brooks, George W.
Item Type: Refine your search to only Report
open access

A numerical method for evaluating wave drag

Description: "A numerical method for evaluating the Von Karman wave-drag equation has been developed and applied to the calculation of wave drag for several bodies of revolution. Results indicated good agreement with the exact solution. Sufficient accuracy of wave drag was obtained by using a simple numerical method to determine the second derivatives of the area distributions" (p. 1).
Date: June 1958
Creator: Cahn, Maurice S. & Olstad, Walter B.
Item Type: Refine your search to only Report
open access

Flutter analysis of rectangular wings of very low aspect ratio

Description: Report presenting a flutter analysis for rectangular wings of very low aspect ratio with a constant thickness, which used slender-body aerodynamic theory and thin-plate theory. The results show that the variation of flutter speed and mode shape with aspect ratio. Approximation of the chordwise deflection shape by use of parabolic or cubic curves yields flutter speeds in fair agreement with those of the "exact" theory for a ratio of chord to semispan less than 3 with the cubic approximation givi… more
Date: June 1958
Creator: Fralich, Robert W. & Hedgepeth, John M.
Item Type: Refine your search to only Report
open access

Further Investigation of Fatigue-Crack Propagation in Aluminum-Alloy Box Beams

Description: Report presenting testing of twenty-one box beams constructed according to nine designs that were subjected to fatigue tests at one load level to study fatigue-crack propagation and accompanying stress redistribution. Six designs had stiffeners riveted to the skin, two had integrally stiffened covers, and one had stiffeners bonded to the skin. Results regarding crack initiation, crack propagation, and stresses are provided.
Date: June 1958
Creator: Hardrath, Herbert F. & Leybold, Herbert A.
Item Type: Refine your search to only Report
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