Technical Report Archive and Image Library (TRAIL) - 986 Matching Results

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Aerodynamic interference of slender wing-tail combinations

Description: From Introduction: "In the present paper, the emphasis is placed on calculating the variations of total forces and moments with angles of attack and sideslip for a number of slender plane and cruciform wing-tail combinations and for some airplane-type arrangements of a plane wing and a horizontal and vertical tail."
Date: January 1957
Creator: Sacks, Alvin H
Partner: UNT Libraries Government Documents Department

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Description: Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
Date: December 5, 1957
Creator: West, F. E., Jr; Whitcomb, Charles F. & Schmeer, James W.
Partner: UNT Libraries Government Documents Department

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Description: Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory. A relatively simple, but general, theoretical method for calculating these load and moment characteristics is described, and the results from this method are found to be in good agreement with experiment provided the initial positions of the forebody vortices are known. It is shown that a simple application of slender-body theory can be used to predict the side loads due to sideslip that are contributed by a vertical tail on a wide variety of wing-body-tail combinations at low angles of attack. For several configurations, changes are indicated which reduced the vertical-tail loads per unit yawing moment of each complete configuration at large angles of attack. Some results are presented on the effect of high angle of attack on the induced-flow field and tail loads due to a wing at supersonic speed.
Date: July 23, 1957
Creator: Polhamus, E. C. & Spahr, J. R.
Partner: UNT Libraries Government Documents Department

Aging Characteristics of Hastelloy B

Description: Report issued by the Oak Ridge National Laboratory discussing the aging characteristics of the alloy Hastelloy B. Materials, equipment, experimental procedures, and results used to determine the characteristics of the alloy are presented. This report includes tables, illustrations, and photographs.
Date: August 12, 1957
Creator: Clausing, Robert E.; Patriarca, P. & Manly, W. D.
Partner: UNT Libraries Government Documents Department

An air-borne target simulator for use with scope-presentation type fire-control systems

Description: Report describing the design and flight evaluation of an air-borne target simulator using precomputed relative kinematics for use in tracking studies of fighter aircraft equipped with scope-presentation type fire-control systems. Testing occurred in an F86D airplane equipped with a Hughes E-4 fire-control system. Results regarding relative kinematic programming considerations and restrictions to system evaluation are provided.
Date: May 10, 1957
Creator: Foster, John V.; Fulcher, Elmer C. & Heinle, Donovan R.
Partner: UNT Libraries Government Documents Department

Airplane measurements of atmospheric turbulence for altitudes between 20,000 and 55,000 feet over the western part of the United States

Description: Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.
Date: August 23, 1957
Creator: Coleman, Thomas L. & Coe, Emilie C.
Partner: UNT Libraries Government Documents Department

Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Description: From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date: August 19, 1957
Creator: Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
Partner: UNT Libraries Government Documents Department

Altitude free-jet investigation of dynamics of a 28-inch-diameter ram-jet engine

Description: From Introduction: "The feasibility of closed-loop control of ram-jet-engine thrust is demonstrated in references 1 and 2. The dynamic behavior of a 28-inch-diameter ram-jet engine designed to operate in Mach number range of 2.35 to 2.70 is evaluated herein."
Date: January 15, 1957
Creator: Wentworth, Carl B.; Dunbar, William R. & Crowl, Robert J.
Partner: UNT Libraries Government Documents Department

Altitude performance of a full-scale turbojet engine using pentaborane fuels

Description: From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."
Date: February 28, 1957
Creator: Useller, James W; Kaufman, Warner B & Jones, William L
Partner: UNT Libraries Government Documents Department

Altitude performance of a turbojet engine using pentaborane fuel

Description: From Summary: "The primary objectives of the investigation reported herein were to determine the effect of this new combuster design on boric oxide deposition on engine parts and to determine the effect of boric oxide on the performance of multistage turbine. Pentaborance fuel (approx. 130 lb) was used in the engine performance evaluation reported herein. The data presented herein show the engine component and over-all performance deterioration with operation on pentaborane fuel".
Date: May 20, 1957
Creator: Sivo, Joseph N
Partner: UNT Libraries Government Documents Department

Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Description: From Introduction: "Experimental investigations of the combustion characteristics of diborane, pentaborane, and pentaborane-hydrocarbon blends in modified turbojet combustors have been conducted at this laboratory at the request of the Bureau of Aeronautics, Department of the Navy, as part of Project Zip. Results of these single-combustor tests are presented in references 2 to 5."
Date: April 17, 1957
Creator: Branstetter, J Robert & Kaufman, Warner B
Partner: UNT Libraries Government Documents Department

Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.
Date: September 13, 1957
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Partner: UNT Libraries Government Documents Department

Altitude starting tests of a small solid propellant rocket

Description: From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date: June 21, 1957
Creator: Sloop, John L. & Krawczoner, Eugene M.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of the 19B-2, 19B-8, and 19XB-1 Jet Propulsion Engines, 3, Performance and Windmilling Drag Characteristics

Description: The performance characteristics of the 19B-8 and 19XB-1 turbojet engines and the windmilling-drag characteristics of the 19B-6 engine were determined in the Cleveland altitude wind tunnel. The investigations were conducted on the 19B-8 engine at simulated altitudes from 5000 to 25,000 feet with various free-stream ram-pressure ratios and on the 19XB--1 engine at simulated altitudes from 5000 to 30,000 feet with approximately static free-stream conditions. Data for these two engines are presented to show the effect of altitude, free-stream ram-pressure ratio, and tail-pipe-nozzle area on engine performance. A 21-percent reduction in tail-pipe-nozzle area of the 19B-8 engine increased the let thrust 43 percent the net thrust 72 percent, and the fuel consumption 64 percent. An increase in free-stream ram-pressure ratio raised the jet thrust and the air flow and lowered the net thrust throughout the entire range of engine speeds for the 19B-8 engine. At similar operating conditions, the corrected jet thrust and corrected air flow were approximately the same for both engines, and the corrected specific fuel consumption based on jet thrust was lower for the 19XB-1 engine than for the 19B-8 engine. The thrust and air-flow data obtained with both engines at various altitudes for a given free-stream rampressure ratio were generalized to standard sea-level atmospheric conditions. The performance parameters involving fuel consumption generalized only at high engine speeds at simulated altitudes as high as 15,000 feet. The windmilling drag of the 19B-8 engine increased rapidly as the airspeed was increased.
Date: March 13, 1957
Creator: Fleming, William A. & Dietz, Robert O., Jr.
Partner: UNT Libraries Government Documents Department

An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability

Description: From Introduction: "The purpose of the present study is to investigate these suggested methods for reducing the undesirable pitching and yawing motions of an airplane during roll maneuvers. The airplane characteristics used in this study were those of the F-100A airplane having the original small vertical tail as shown in figure 1."
Date: February 19, 1957
Creator: Creer, Brent Y
Partner: UNT Libraries Government Documents Department

Analog computer study of some filtering, command-computer, and automatic-pilot problems connected with the attack phase of the automatically controlled supersonic interceptor

Description: From Summary: "Presented herein are the results of a study of some of the problems associated with the cross-roll filter, command computer, and g-limiter of an automatic interceptor system."
Date: October 3, 1957
Creator: Sherman, Windsor L
Partner: UNT Libraries Government Documents Department

Analyses for turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine

Description: From Introduction: "This report presents net thrusts computed for hydrogen, diborance, and hydrazine with fuel-air ratios form stoichiometric values to 0.5. Net thrusts for fuel-rich afterburning are compared with those for stoichiometric combustion of the turbojet fuel and air augmented with a 220-second specific-impulse rocket."
Date: June 18, 1957
Creator: Morris, James F
Partner: UNT Libraries Government Documents Department

Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Description: From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."
Date: May 7, 1957
Creator: Slone, Henry O & Donoughe, Patrick L
Partner: UNT Libraries Government Documents Department