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Control characteristics at transonic speeds of a linked flap and spoiler on a tapered 45 degrees sweptback wing of aspect ratio 3

Description: Report presenting an investigation at transonic speeds to determine the control characteristics of a linked flap and spoiler. The control consisted of a linked combination of a quarter-span inboard plug-type spoiler and a full-span flap. Results regarding the hinge-moment, pitching-moment, lift, and rolling-moment are provided.
Date: July 11, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.
Partner: UNT Libraries Government Documents Department

Flight measurements of the transonic drag of models of several isolated external stores and nacelles

Description: Report presenting drag measurements on models of 20 isolated external stores and nacelles flown from the helium gun at a range of Mach numbers. Results regarding fineness-ratio and shape effects, drag correlation, and friction drag are provided. Generally, the shape variations among the various types of stores and nacelles had the expected effects on isolated body drag.
Date: March 11, 1955
Creator: Stevens, Joseph E. & Purser, Paul E.
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 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

Investigation of a transonic turbine designed for a maximum rotor-blade suction-surface relative Mach number of 1.57

Description: From Summary: "A transonic turbine designed for a maximum blade-surface relative Mach number of 1.57 was investigated experimentally. The performance of the turbine is compared with that of three other transonic turbines that were previously investigated."
Date: October 11, 1954
Creator: Whitney, Warren J.; Wong, Robert Y. & Monroe, Daniel E.
Partner: UNT Libraries Government Documents Department

Investigation of transient combustion characteristics in a single tubular combustor

Description: An investigation was conducted to determine the combustion response to rapid fuel-flow changes in a single tubular combustor at two simulated altitude-rotor speed conditions of 25,000 feet-70 percent rated engine speed and 50,000 feet-70 percent rated engine speed. Limiting rates of change of fuel flow (acceleration limits) were determined and the effects of certain combustion air flow variables on the transient combustion characteristics were studied with the aid of rapid-response instrumentation.
Date: February 11, 1954
Creator: Donlon, Richard H.; McCafferty, Richard J. & Straight, David M.
Partner: UNT Libraries Government Documents Department

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics

Description: Report presenting an investigation to determine the low-speed lateral characteristics of a triangular-wing airplane model. The model consisted of an aspect ratio 2 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail.
Date: February 11, 1952
Creator: Graham, David & Koenig, David G.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64

Description: From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."
Date: September 11, 1956
Creator: Swanson, Andrew G. & Rumsey, Charles B.
Partner: UNT Libraries Government Documents Department

Preliminary empirical design requirements for the prevention of tumbling of airplanes having no horizontal tails

Description: Report presenting an investigation of the design characteristics and loadings conducive to the tumbling of airplanes with no horizontal tails. Empirical design requirements based on model testings of 18 different configurations and an explanation of the phenomena of tumbling are provided.
Date: October 11, 1950
Creator: Bryant, Robert L.
Partner: UNT Libraries Government Documents Department

Preliminary analysis of a nuclear-powered supersonic airplane using ramjet engines

Description: Report presenting performance estimates for a family of airplanes designed to cruise at Mach number 4.25 and using General Electric AC-210 ramjet engines. The airplane was designed to carry a payload of 10,000 pounds and use a crew of one. Results regarding the shield weight, engine weight, number of engines, and nozzle-velocity coefficient are provided.
Date: April 11, 1958
Creator: Weber, Richard J. & Connolley, Donald J.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of an asymmetric swept nose inlet of circular projection at Mach number 3.85

Description: Report presenting an experimental investigation of the performance capabilities of an asymmetric swept nose inlet of circular projection in the supersonic wind tunnel at a Mach number of 3.85. The aysmmetric inlet was evaluated in terms of its pressure recovery and mass-flow characteristics for angles of attack up to 9 degrees. Results regarding diffuser performance, supercritical flow patterns, oblique shocks, subcritical stability ranges, and Mach number profiles are provided.
Date: October 11, 1954
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department

Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane

Description: During the acceptance tests of the Bell X-5 airplane, measurements of the static stability and control characteristics and horizontal-tail loads were obtained by the NACA High-Speed Flight Research Station. The results of the stability and control measurements are presented in this paper. A change in sweep angle between 20 deg and 59 deg had a minor effect on the longitudinal trim, with a maximum change of about 2.5 deg in elevator deflection being required at a Mach number near 0.85; however, sweeping the wings produced a total stick-force change of about 40 pounds.
Date: February 11, 1953
Creator: Finch, Thomas W. & Briggs, Donald W.
Partner: UNT Libraries Government Documents Department

Longitudinal frequency-response characteristics of the Douglas D-558-I airplane as determined from experimental transient-response histories to Mach number of 0.90

Description: Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.
Date: February 11, 1952
Creator: Angle, Ellwyn E. & Holleman, Euclid C.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and drag characteristics at Mach numbers from 0.75 to 1.5 of an airplane configuration having a 60 degree swept wing of aspect ratio 2.24 as obtained from rocket-propelled models

Description: Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.
Date: April 11, 1952
Creator: Vitale, A. James; McFall, John C., Jr. & Morrow, John D.
Partner: UNT Libraries Government Documents Department

Measured and estimated lateral static and rotary derivatives of a 1/12-scale model of a high-speed fighter airplane with unswept wings

Description: Report presenting a low-speed investigation to determine the lateral static and rotary derivatives of a model of a high-speed fighter airplane. The purpose was to compare experimental stability derivatives with derivatives estimated for a wing-fuselage combination, a vertical- and horizontal-tail combination, and a complete model.
Date: January 11, 1954
Creator: Williams, James L.
Partner: UNT Libraries Government Documents Department

Free-spinning-tunnel investigation of a 1/28-scale model of the North American FJ-4 airplane: TED No. NACA AD-3112

Description: Report presenting an investigation in the 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/28-scale dynamic model of the North American FJ-4 airplane. Results indicated that either a flat-type or a steep-type spin maybe obtained when the airplane is spinning erect. Results regarding inverted spins, loading condition, spin-recovery rocket tests, and spin-recovery parachute tests are provided.
Date: February 11, 1958
Creator: Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Effect of flight speed on dynamics of a turboprop engine

Description: Report presenting an investigation of transient operation of a turboprop engine in an altitude wind tunnel at 35,000 feet over a range of Mach numbers to determine the effect of flight speed upon the dynamic response of the engine. The generalized time constant of the engine-propeller combination varied with flight speed and power level.
Date: April 11, 1955
Creator: Nakanishi, S.; Craig, R. T. & Wile, D. B.
Partner: UNT Libraries Government Documents Department

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. The purpose behind the investigation was to investigate the idea that luminous radiation from nongaseous substances in the afterburner gas stream might be present and vary significantly with pressure.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Comparison of measured and predicted indicated angles of attack near the fuselages of a triangular-wing wind-tunnel model and a swept-wing fighter airplane in flight

Description: Report presenting measurements of the local flow angles near the fuselages of a triangular-wing wind-tunnel model and an F-86A-5 airplane in flight using airflow detectors on the fuselages. A comparison of the measured and predicted flow angles is provided. Results indicated that the accuracy of the predicted indicated angles of attack was not sufficient to eliminate the necessity of a flight calibration of a detector mounted on a fuselage.
Date: March 11, 1953
Creator: McFadden, Norman M.; McCloud, John L., III & James, Harry A.
Partner: UNT Libraries Government Documents Department

Analysis of fully developed turbulent heat transfer at low Peclet numbers in smooth tubes with application to liquid metals

Description: From Introduction: "Analyses of heat transfer for liquid metals flowing turbulently in smooth tubes (low Pradtl numbers) are given in reference 1 and 2. The predicted heat-transfer coefficients from these analyses are considerably higher than those determined in the experimental heat-transfer investigations for mercury and lead bismuth given in references 2 to 4. If the analytical and experimental results for flow of gases are compared at low Peclet numbers, they are also found to be in disagreement (references 5 and 6)."
Date: August 11, 1952
Creator: Deissler, Robert G
Partner: UNT Libraries Government Documents Department

Effect of inlet-annulus area blockage on over-all performance and stall characteristics of an experimental 15-stage axial-flow compressor

Description: Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.
Date: May 11, 1954
Creator: Lucas, James G.; Finger, Harold B. & Filippi, Richard E.
Partner: UNT Libraries Government Documents Department

Performance evaluation of reduced-chord rotor blading as applied to J23 two-stage turbine 6: stage performance with standard rotor blading at inlet conditions of 35 inches of mercury absolute and 700 degrees R

Description: Report presenting an evaluation of the stage performance of the J73 turbine on the basis of previous performance investigations of the first stages alone and of the two-stage turbines with standard and with reduced-chord rotor blading for a range of rotational speeds and pressure ratios. The results demonstrated that both of the two-stage turbines and first-stage turbines had comparable performance.
Date: July 11, 1957
Creator: Davidson, Elmer H. & Schum, Harold J.
Partner: UNT Libraries Government Documents Department