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Flight performance of a twin-engine supersonic ram jet from 2,300 to 67,200 feet altitude

Description: Report presenting a flight investigation of a ground-launched supersonic twin ram-jet test vehicle using short flame-length burners. Results were obtained for a range of Mach numbers, altitudes, and fuel-air-ratios. Engine performance, gross thrust, fuel rate, total impulse, values of combustion efficiency and impulse, and overall combustion efficiency are also included.
Date: February 19, 1951
Creator: Dettwyler, H. Rudolph & Bond, Aleck C.
Partner: UNT Libraries Government Documents Department

A flight study of the effects on tracking performance of changes in the lateral-oscillatory characteristics of a fighter airplane

Description: A study of the effects of variations in lateral-oscillatory characteristics on air-to-air tracking performance has been made, using a conventional, propeller-driven fighter airplane equipped with servo devices for varying these characteristics in flight. Tracking runs were made both in smooth air and in simulated rough air. The lateral-oscillation period, damping, and roll coupling were varied over wide ranges during the investigation.
Date: October 9, 1953
Creator: McNeill, Walter E.; Drinkwater, Fred J., III & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Flight test of a solid-fuel ram jet with the internal surface of the combustor air cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. Having an internally cooled combustor averted combustor burn-out during the flight test. Results regarding acceleration, altitude, air specific impulse, and fuel specific impulse are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Flight test of NACA FR-1-B, a low-acceleration rocket-propelled vehicle for transonic flutter research

Description: Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department

A flight study of requirements for satisfactory lateral oscillatory characteristics of fighter aircraft

Description: Report presenting a pilot-opinion survey conducted with a conventional fighter airplane fitted with special servo devices for varying in flight the dihedral effect, static directional stability, and directional damping. Results showing the boundaries that define satisfactory and tolerable lateral oscillatory characteristics are presented.
Date: July 25, 1951
Creator: Liddell, Charles J., Jr.; Creer, Brent Y. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Flight tests of a man standing on a platform supported by a teetering rotor

Description: Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.
Date: March 24, 1954
Creator: Hill, Paul R. & Kennedy, T. L.
Partner: UNT Libraries Government Documents Department

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
Partner: UNT Libraries Government Documents Department

Flight performance of a 2.8 KS 8100 Cajun solid-propellant rocket motor

Description: From Summary: "The performance of a 2.8 KS 8100 Cajun solid-propellant rocket motor has been determined from the free-flight test of a single-stage model which reached a velocity of 5,268 feet per second (Mach number, 4.74). Thrust data from the flight test are compared with data obtained from a ground firing test made by the manufacturer and the two are shown to be in agreement." Report presenting general drag, data, and acceleration are also provided.
Date: January 21, 1957
Creator: Lee, Dorothy B.
Partner: UNT Libraries Government Documents Department

Flight tests of a two-dimensional wedge diffuser at transonic and supersonic speeds

Description: From Summary: "A two-dimensional wedge diffuser, designed to be used with a ducted-airfoil ram jet, was tested on a rocket-powered test vehicle up to a Mach number of 1.45. Orifice plates and a choking section behind the diffuser exit simulated burning in a combustion chamber by providing the proper pressure drop. Results obtained from these tests showed there was no abrupt changes in mass flow and pressure recovery as the model velocity increased through the transonic region."
Date: August 11, 1948
Creator: Faget, M. A.
Partner: UNT Libraries Government Documents Department

Flight measurements of the lateral stability and control characteristics of a high-speed fighter airplane

Description: Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.
Date: September 23, 1952
Creator: Crane, H. L.; Beckhardt, A. R. & Matheny, C. E.
Partner: UNT Libraries Government Documents Department

Flight Measurements of the Stability Characteristics of the Bell X-5 Research Airplane in Sideslips at 59 Deg Sweepback

Description: Flight measurements of the stability characteristics of the Bell X-5 research airplane at 59 deg sweepback were made in steady sideslips at Mach numbers from 0.62 to 0.97 at altitudes ranging between 35,000 and 40,000 feet. The results showed that the apparent directional stability was positive and increased at Mach numbers above 0.90. The apparent effective dihedral was positive and high, increasing at Mach numbers above 0.75. The cross-wind force coefficient per degree of sideslip was positive and increased rapidly at Mach numbers above 0.94.
Date: February 11, 1953
Creator: Childs, Joan M
Partner: UNT Libraries Government Documents Department

Flow separation from rods ahead of blunt noses at Mach number 2.72

Description: From Summary: "An experimental investigation in the Langley Gas Dynamics Laboratory has been made of the flow separation from slender rods mounted to extend forward along the axes of symmetry of blunt-nosed bodies. The mechanism of the separation and its governing criteria are discussed. Drag data at a Mach number of 2.72 for various rod lengths and nose radii at an angle of attack of zero degrees are presented. It was found that the drag coefficients of blunt noses could be appreciably reduced by the use of protruding rods. Criteria for rod length which gives lowest drag are given."
Date: July 15, 1952
Creator: Jones, Jim J.
Partner: UNT Libraries Government Documents Department

Flutter and divergence of rectangular wings of very low aspect ratio

Description: From Summary: "Slender-body aerodynamic theory is used in conjunction with thin-plate theory in the flutter analysis of low-aspect-ratio rectangular wings of constant thickness when chordwise variations of deflections are considered. The spanwise variation of deflection is given by a parabola, and the chordwise variation is allowed complete freedom. The results show the variation of flutter speed and mode shape with aspect ratio."
Date: June 28, 1957
Creator: Fralich, Robert W.; Hedgepeth, John M. & Tuovila, W. J.
Partner: UNT Libraries Government Documents Department

Flow diffusion in a constant-diameter duct downstream of an abruptly terminated center body

Description: Report presenting an investigation of the flow properties of a constant-outer-wall annual diffuser in combination with a tailpipe in order to come up with a configuration suitable for turbojet afterburners. Information about axial inlet flow and whirling inlet flow is provided. During testing, a vena contrata region formed downstream from the center body terminal and rendered the first 1/2 diameter of the tailpipe ineffective.
Date: July 8, 1953
Creator: Wood, Charles C. & Higginbotham, James T.
Partner: UNT Libraries Government Documents Department

Free-jet tests of a 6.5-inch-diameter ram-jet engine at Mach numbers 1.81 and 2.00

Description: Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Date: March 7, 1951
Creator: Faget, Maxime A.; Watson, Raymond S. & Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the low-speed stability and control characteristics of a model having a fuselage of relatively flat cross section

Description: Report presenting an experimental investigation in the free-flight tunnel to determine the low-speed stability and control characteristics of a model with a fuselage of relatively flat cross section. The model was found to exhibit an erratic behavior in pitch and yaw, which appeared to be due to random trim changes associated with the flow from the forward portion of the flat fuselage. Results regarding the longitudinal stability and control characteristics and lateral stability and control characteristics are provided.
Date: February 24, 1953
Creator: Paulson, John W. & Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department

Free-spinning characteristics of a 1/21-scale model of the Douglas AD-2W Airplane: TED No. NACA DE329

Description: Report presenting an investigation to determine the spin and recovery characteristics of a model of the Douglas AD-2W airplane, which has a large radome installation. Results indicated that the plane has satisfactory erect and inverted spin-recovery characteristics. Information about erect spins, inverted spins, and recommended recovery technique is provided.
Date: June 9, 1948
Creator: White, Richard P.
Partner: UNT Libraries Government Documents Department

Free-spinning tunnel investigation of a 1/20-scale model of the Douglas X-3 airplane

Description: Report discussing the spin and spin-recovery characteristics of a model of the Douglas X-3 airplane in a free-spinning tunnel. The pitching-moment characteristics of the scale model were not found to be typical of larger scale results. The results indicated that at an altitude range of 15,000 to 30,000 feet, the X-3 will not exhibit unusual trim tendencies and it will be difficult to obtain erect spins unless the ailerons are full with the spin.
Date: December 26, 1951
Creator: Hultz, Burton E.
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel tests of a target-seeking glide-bomb model with flicker lateral control

Description: Report presenting an investigation of control systems suitable for target-seeking missiles. Testing occurred in the free-flight tunnel of the GB-5 glide bomb equipped with a light-seeker control unit which applied flicker control. Results indicated that good stability could be obtained with the control system, but was somewhat less stable than with a proportional control system.
Date: July 28, 1948
Creator: McKinney, Marion O., Jr. & Drake, Hubert M.
Partner: UNT Libraries Government Documents Department

Techniques for determining thrust in flight for airplanes equipped with afterburners

Description: From Summary: "An experimental technique has been developed which enables a determination of the net propulsive force acting on an afterburner-equipped airplane in flight. The thrust measurement is based on the variation of static and total pressure and stagnation temperature across the fuselage exit as determined by a swinging pitot-static pressure and temperature probe. The details are also presented for an air-cooled fixed-pressure probe for the determination of basic engine thrust."
Date: January 19, 1953
Creator: Rolls, L. Stewart; Havill, C. Dewey & Holden, George R.
Partner: UNT Libraries Government Documents Department

Effects of the spanwise, chordwise and vertical location of an external store on the aerodynamic characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the effects of external store location on the lift, drag, and pitching-moment characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96. Brief comparative tests were also made to determine the effect of changing the sweep of the strut attaching the store to the wing and of changing the chordwise location of the swept strut.
Date: October 27, 1952
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Effects on control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degrees sweptback wing at a Mach number of 1.9

Description: Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.
Date: December 4, 1951
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Control characteristics of trailing-edge spoilers on untapered blunt trailing-edge wings of aspect ratio 2.7 with 0 degree and 45 degrees sweepback at Mach numbers of 1.41 and 1.96

Description: Report presenting an investigation in the supersonic blowdown tunnel to determine the control characteristics of full-span trailing-edge spoilers on two related full-blunt wings with the same aspect ratio but differing angles of sweepback. A similar unswept wing that was larger and had a partially blunt trailing edge was also tested with a full-span trailing-edge spoiler. Results regarding the lift, rolling-moment, and pitching-moment coefficients for unswept wings, the 45-degree sweptback wing, and a comparison of spoiler data with flap data are provided.
Date: December 3, 1952
Creator: Jacobsen, Carl R.
Partner: UNT Libraries Government Documents Department

Theoretical analysis of one-stage windmills for reducing flow distortion

Description: Report presenting an analysis of two windmills for reducing flow distortion. Results regarding the windmill design, flow conditions, velocity distortions, total-pressure distortions, total-temperature distortions, and design value of the ratio of axial velocity to blade tip speed are provided.
Date: June 12, 1957
Creator: English, Robert E. & Yohner, Peggy L.
Partner: UNT Libraries Government Documents Department