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Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel

Description: Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date: December 19, 1952
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

An experimental study of five annular air inlet configurations at subsonic and transonic speeds

Description: Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, and propulsive thrust comparison are provided.
Date: August 19, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R.; Fleming, Frank F. & Bryan, Carroll R.
Partner: UNT Libraries Government Documents Department

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

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

Investigation of a supersonic-compressor rotor with turning to axial direction 1: rotor design and performance

Description: Report presenting an approximate, quasi-three-dimensional design procedure adapted to the design of high solidity, impulse-type supersonic compressors. The method is applied to a compressor rotor with a tip speed of 1600 feet per second in air, an inlet hub-tip radius ratio of 0.75, and an axial discharge relative to the rotor. Results regarding the overall performance, rotor-entrance conditions, static-pressure profiles, discharge conditions, and discharge surveys are provided.
Date: August 19, 1953
Creator: Tysl, Edward R.; Klapproth, John F. & Hartmann, Melvin J.
Partner: UNT Libraries Government Documents Department

A flight comparison of a submerged inlet and a scoop inlet at transonic speeds

Description: Report presenting flight tests conducted on two different inlet configurations, a submerged divergent-wall inlet and scoop inlet, to determine their characteristics when installed on a YF-93 airplane. Measurements were made of the pressure-recovery characteristics of the inlets and overall airplane drag for each configuration. Results regarding the induction-system efficiency, airplane drag, and a relative comparison of the inlet installations are provided.
Date: March 19, 1953
Creator: Rolls, L. Stewart
Partner: UNT Libraries Government Documents Department

Stability and control characteristics at low speed of a modified 1/10-scale model of the MX-1554A design

Description: Report presenting an investigation of the low-speed stability and control characteristics of a modified scale model of the MX-1554A design. It employs a triangular wing and triangular stabilizing surfaces. The modifications of the design included an increase in slotted-flap span, a redesigned tip aileron, fuselage tail cone, and speed brakes.
Date: November 19, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

A low-speed experimental study of the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip

Description: Report presenting an investigation to determine the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip. The fuselage was found to experience a large increase in yawing moment as the angle of attack increases. The results also indicated that a ring or other roughness used on the nose caused a large decrease in the yawing moment obtained at high angles of attack.
Date: November 19, 1952
Creator: Letko, William
Partner: UNT Libraries Government Documents Department

Measurement and analysis of turbulent flow containing periodic flow fluctuations

Description: Report presenting techniques for the measurement of the energy spectrum of flow fluctuations in both axial and lateral flow directions. Data indicated that the energy spectrum of the turbulence is not affected by periodic and random sound disturbances outside the frequency containing the disturbances.
Date: August 19, 1953
Creator: Mickelsen, William R. & Laurence, James C.
Partner: UNT Libraries Government Documents Department

Free-spinning-tunnel investigation of a 1/20-scale model of the Douglas A4D-1 airplane: TED No. NACA DE 389

Description: Report presenting an investigation of the spin and recovery characteristics of a 1/20-scale dynamic model of the Douglas A4D-1 attack airplane in the 20-foot free-spinning tunnel. Erect spins and recoveries were investigated with the model in the clean condition and the loading condition, which includes a center external store with and without two external wing fuel tanks installed. Results regarding several conditions, including erect spins, no external stores, horizontal-tail incidence, 4 degrees leading edge up; erect spins, stores installed; landing conditions, inverted spins, spin-recovery parachute tests, and recommended recovery technique and control forces are provided.
Date: January 19, 1955
Creator: Klinar, Walter J.; Scher, Stanley H. & Healy, Frederick M.
Partner: UNT Libraries Government Documents Department

Heat-transfer and pressure measurements from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and Reynolds number per foot of 23 x 10(exp 6): COORD. No. AF-AM-70

Description: From Summary: "Boundary-layer transition and heat-transfer measurements were obtained from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and a Reynolds number per foot of 23 x 10(exp 6). Boundary-layer transition was observed on the nose of the model. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions. The drag coefficient of the configuration was also obtained for a Mach number range of 1.25 to 3.75."
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department

Free-flight tests at Mach numbers from 0.8 to 1.4 to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a 45 degree sweptback wing having an NACA 65A009 airfoil

Description: Report presenting rocket-propelled models flown at transonic and supersonic speeds to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a sweptback wing. Results regarding the total drag coefficient, wing-plus-interference drag coefficients, and force-break Mach number are provided.
Date: August 19, 1952
Creator: Pepper, William B., Jr.
Partner: UNT Libraries Government Documents Department

Effect of full-span trailing-edge elevons on the transonic longitudinal aerodynamic characteristics of a wing-body combination having a 3-percent-thick triangular wing with 60 degree leading-edge sweep

Description: Report presenting the results of an investigation to determine the effects of full-span trailing-edge flaps on the static longitudinal characteristics of a triangular wing-body combination. Data was obtained for the basic configuration and for a wing with the control surfaces deflected for longitudinal control.
Date: September 19, 1957
Creator: Critzos, Chris C. & Foss, Willard E., Jr.
Partner: UNT Libraries Government Documents Department

Drag investigation of a swept-wing fighter-airplane model incorporating two drag-rise-reducing fuselage revisions

Description: Report discussing several configurations of a swept-wing fighter airplane to determine the effects of modified applications of the transonic and supersonic area rules on the transonic drag-rise characteristics. Information about the lift and pitching-moment characteristics is also provided.
Date: July 19, 1955
Creator: Whitcomb, Charles F. & Lee, Edwin E., Jr.
Partner: UNT Libraries Government Documents Department

Downwash and dynamic pressure at the horizontal tail of a six-engine pusher-propelled airplane

Description: Report discussing an investigation of the vertical plane of the elevator hinge line of a powered model of a bomber to determine the values of downwash and the dynamic-pressure ratio. The equations for calculating these values and the testing procedures are described.
Date: July 19, 1948
Creator: Furlong, G. Chester
Partner: UNT Libraries Government Documents Department

Design and performance of fuel control for aircraft hydrogen fuel system

Description: Report presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The system was designed to explore some problems associated using hydrogen as an aircraft fuel. Results regarding the steady-state response, transient response, and performance in engine-speed loop for the system are provided.
Date: August 19, 1957
Creator: Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
Partner: UNT Libraries Government Documents Department

Design and test of mixed-flow impellers 1: aerodynamic design procedure

Description: Report presenting the design of a mixed-flow impeller with special emphasis on the reduction or elimination of velocity deceleration along the wetted surfaces, especially the blade suction surface. With the use of a provisional hub-shroud profile, the blade shape at the blade mean height was determined from a prescribed velocity distribution.
Date: September 19, 1952
Creator: Osborn, Walter M. & Hamrick, Joseph T.
Partner: UNT Libraries Government Documents Department

A comparison of carrier approach speeds as determined from flight tests and from pilot-operated simulator studies

Description: Report presenting a simplified analog simulator that can be used to predict the minimum comfortable approach speeds that could be used in carrier landings for airplanes that are limited by their ability to control altitude. Predicted speeds from initial tests on several planes are compared with values from flight tests in order to indicate the validity of simulator results.
Date: June 19, 1957
Creator: White, Maurice D. & Drinkwater, Fred J., III
Partner: UNT Libraries Government Documents Department

Analysis of experimental low-speed loss and stall characteristics of two-dimensional compressor blade cascades

Description: From Introduction: "In the present report, the concept of velocity diffusion is applied in an analysis of blade losses expressed in terms of the fundamental parameter of wake momentum thickness. Restrictions and limitations involved in the application of the results to cascade performance analyses are discussed."
Date: March 19, 1957
Creator: Lieblein, Seymour
Partner: UNT Libraries Government Documents Department

Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85

Description: Report presenting an experimental study of the compression fields around axially symmetric isentropic spikes with varying degrees of compressive flow turning made at a Mach number of 3.85 to analyze the basic shock structures and thereby establish further design criteria for supersonic-inlet applications. Results regarding the original isentropic spike and cowl, isentropic survey-spike configurations, and external-compression limitations are provided.
Date: August 19, 1954
Creator: Connors, James F. & Wollett, Richard R.
Partner: UNT Libraries Government Documents Department

Bibliography of NACA reports related to aircraft control and guidance systems January 1949 - April 1954

Description: This report lists pertinent NACA papers presenting research results which have a direct bearing on control system design and performance for both piloted and automatically controlled aircraft. Limited reference is also made to NACA reports on aircraft engine controls and to research techniques and instrumentation pertinent to the study of control systems and aircraft dynamics in flight. Reports published between January 1949 and April 1954 are listed in chronological order and cross referenced.
Date: July 19, 1954
Creator: Niewald, Roy J. & Brewer, Jack D.
Partner: UNT Libraries Government Documents Department

Blow-out velocities of various petroleum, slurry, and hydride fuels in a 1 7/8-inch diameter combustor

Description: Report presenting testing using a 1 7/8-inch inside-diameter combustor that can measure and compare the blow-out velocities of single-component fuels, slurries, and fuel mixtures with a wide range of reactivity and physical properties. The blow-out velocities of isooctane, n-heptane, isopentane, allyl chloride, and propylene oxide varied int he same way as flame speeds of the fuels. Results regarding the effects of different additives are also provided.
Date: April 19, 1954
Creator: Cook, Preston N., Jr.; Lord, Albert M. & Kaye, Samuel
Partner: UNT Libraries Government Documents Department