National Advisory Committee for Aeronautics (NACA) - 47 Matching Results

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Analysis of measured pressures on airfoils at Mach numbers near 1

Description: Report presenting measured pressure over airfoils at Mach number 1, with subsonic velocities at the nose and supersonic velocities throughout the rear portion, are analyzed by comparison with calculations for similar cases. Results regarding the theoretical basis of approximation, comparison of Prandtl-Meyer flow with measurements, comparison of linear-velocity extrapolation with measurements, and effect of boundary layer upon airfoil pressures are provided.
Date: September 19, 1949
Creator: Habel, Louis W. & Miller, Mason F.
Partner: UNT Libraries Government Documents Department

Cyclic engine operation of cast vitallium turbine blades at an exhaust-cone gas temperature of 1440 plus or minus 20 F

Description: Report presenting an investigation conducted to determine the effects of increased gas temperatures on the performance of cast Vitallium blades in a turbojet engine. Results regarding the experimental investigation and metallurgical investigation are provided.
Date: September 19, 1949
Creator: Yaker, Charles & Garrett, Floyd B.
Partner: UNT Libraries Government Documents Department

An introduction to the physical aspects of helicopter stability

Description: In order to provide engineers interested in rotating-wing aircraft, but with no specialized training in stability theory, some understanding of the factors that influence the flying qualities of the helicopter, an explanation is made of both the static stability and the stick-fixed oscillation in hovering and forward flight in terms of fundamental physical quantities. Three significant stability factors -- static stability with angle of attack, static stability with speed, and damping due to a pitching or rolling velocity -- are explained in detail.
Date: September 19, 1949
Creator: Gessow, Alfred & Amer, Kenneth B.
Partner: UNT Libraries Government Documents Department

Investigation of low-speed aileron control characteristics at a Reynolds number of 6,800,000 of a wing with leading edge swept back 42 degrees with and without high-lift devices

Description: Report presenting an investigation at a Reynolds number of 6,800,000 to determine the low-speed lateral control characteristics of a 20-percent-chord half-span outboard aileron on a wing with 42 degrees of sweepback at the leading edge. The lateral control, aileron hinge-moment, aileron load, and balance-chamber-pressure characteristics were determined for the wing with and without high-lift and stall-control devices for an angle-of-attack range from -4 degrees through the stall.
Date: July 19, 1949
Creator: Bollech, Thomas V. & Pratt, George L.
Partner: UNT Libraries Government Documents Department

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Effects of split flaps, elevons, and leading-edge devices at low speed

Description: Report presenting an investigation to evaluate the effects of split flaps, elevons, sharp leading edges, drooped-nose flaps, and extended-nose flaps on the lift, drag, and pitching-moment characteristics at low speed of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and an aspect ratio of 3.5. Results regarding the plain wing and wing-fuselage combinations, Reynolds number, split flaps, elevons, leading-edge devices, and highest lift coefficient attained before longitudinal instability are provided.
Date: May 19, 1949
Creator: Hopkins, Edward J.
Partner: UNT Libraries Government Documents Department

Chordwise and spanwise loadings measured at low speed on large triangular wings

Description: Report presenting pressure distributions of three triangular wing models: a wing-alone model, the same wing combined with a body, and a mock-up of a triangular-wing airplane. Results regarding the separation-vortex air flow over triangular wings, general comments regarding the applicability of the study, chordwise pressure distribution, section lift characteristics, center of pressure, and span load distribution are provided.
Date: April 19, 1949
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department

Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Description: A low-scale wind-tunnel investigation was conducted in rolling flow to determine the effects of aspect ratio and sweep (when varied independently) on the rolling stability derivatives for a series of untapered wings. The rolling-flow equipment of the Langley stability tunnel was used for the tests. The data of the investigation have been used to develop a method of accounting for the effects of the drag on the yawing moment due to rolling throughout the lift range.
Date: January 19, 1949
Creator: Goodman, Alex & Fisher, Lewis R.
Partner: UNT Libraries Government Documents Department

Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats

Description: Report presenting an investigation of two NACA 6-series airfoils, the NACA 64(sub)1-212 and NACA 65A109 with leading edge slats and split flaps deflected 60 degrees. Information about optimum slat positions, airfoil section lift characteristics, pitching-moment characteristics, and effect of roughness on the lift characteristics was obtained.
Date: January 19, 1949
Creator: Gottlieb, Stanley M.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at subsonic and supersonic Mach numbers of a thin triangular wing of aspect ratio 2 1: maximum thickness at 20 percent of the chord

Description: From Summary: "This report presents the results of a wind-tunnel investigation conducted to determine the effects of Mach number on the aerodynamic characteristics of a wing of triangular plan form."
Date: November 19, 1948
Creator: Berggren, Robert E. & Summers, James L.
Partner: UNT Libraries Government Documents Department

Drag measurements in flight on the 10-percent-thick and 8-percent-thick wing X-1 airplanes

Description: Report presenting drag measurements made on a 10-percent-thick wing and 8-percent-thick tail and a 8-percent-thick wing, 6-percent-thick tail version of the X-1 airplane at a variety of Mach numbers. The drag of the thicker wing was found to be much higher than that of the thinner wing. The fuselage was found to cause interference with the wing of both models, making the separation of wing and fuselage drag difficult to determine.
Date: November 19, 1948
Creator: Gardner, John J.
Partner: UNT Libraries Government Documents Department

Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel. III: the effectiveness of a constant-chord aileron

Description: Report presenting a wind-tunnel investigation at a range of Mach numbers with a constant Reynolds number of a semispan model of a thin, unswept wing of aspect ratio 4 and taper ratio 0.5 with a constant-chord aileron and a modified diamond profile. Results regarding lift and rolling-moment characteristics and aileron effectiveness are provided.
Date: November 19, 1948
Creator: Johnson, Ben H., Jr. & Demele, Fred A.
Partner: UNT Libraries Government Documents Department

An Investigation of the Low-Speed Static Stability Characteristics of Complete Models Having Sweptback and Sweptforward Wings

Description: "An investigation has been conducted in the Langley 300 MPH 7- by 10-foot tunnel to determine the static stability characteristics at low speeds of complete models with various swept wings so that comparisons might be made with available theoretical and empirical methods of predicting the stability characteristics. Longitudinal and lateral stability characteristics, flaps up and down, were obtained for models having 0 degree, 15 degrees, 30 degrees, and 45 degrees sweptforward and sweptback wings. The results of the investigation indicate that static stability characteristics can be estimated with reasonable accuracy in the low-lift range by means of existing theories" (p. 1).
Date: November 19, 1948
Creator: Spearman, M. Leroy & Comisarow, Paul
Partner: UNT Libraries Government Documents Department

Investigation of two pitot-static tubes at supersonic speeds

Description: The results of tests at a Mach number of 1.94 of an ogives-nose cylindrical pitot-static tube and similar tests at Mach numbers of 1.93 and 1.62 of a service pitot-static tube to determine body static pressures and indicated Mach numbers are presented and discussed. The radial pressure distribution on the cylindrical bodies is compared with that calculated by an approximate theory.
Date: November 19, 1948
Creator: Hasel, Lowell E. & Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Simulated Altitude Performance of Combustors for the Westinghouse 24C Jet Engine I-24C-2 Combustor

Description: "A Westinghouse 24C-2 combustor was investigated at conditions simulating operation of the 24C Jet engine at zero ram over ranges of altitude and engine speed. The investigation was conducted to determine the altitude operational limits, that is, the maximum altitude for various engine speeds at which an average combustor-outlet gas temperature sufficient for operation of the jet engine could be obtained. Information was also obtained regarding the character of the flames, the combustion efficiency, the combustor-outlet gas temperature and velocity distributions, the extent of afterburning, the flow characteristics of the fuel manifolds, the combustor inlet-to-outlet total-pressure drop, and the durability of the combustor basket" (p. 1).
Date: November 19, 1948
Creator: Manganiello, Eugene J.; Bernardo, Everett & Schroeter, Thomas T.
Partner: UNT Libraries Government Documents Department

An experimental investigation at large scale of several configurations of an NACA submerged air intake

Description: From Summary: "An investigation of an NACA submerged air intake was conducted on a full-scale model of a fighter-type airplane. This study was made to determine the large-scale aerodynamic characteristics of a submerged air intake proposed as the result of small-scale tests and to compare the pressure-recovery characteristics of the large- and small-scale installations. Additional tests were made to determine the effect on pressure recovery of a systematic variation of ramp divergence."
Date: October 19, 1948
Creator: Martin, Norman J. & Holzhauser, Curt A.
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

Longitudinal Stability and Control Characteristics of a Semispan Airplane Model at Transonic Speeds as Obtained by the Transonic-Bump Method

Description: Memorandum presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the longitudinal stability and control characteristics of a semispan airplane model at transonic speeds. The results indicated an increase in the maneuvering stability through the transonic range, but regions of instability were indicated by the slope of the curve stabilizer incidence for trim against Mach number at all positions tested.
Date: July 19, 1948
Creator: Weil, Joseph & Spearman, M. Leroy
Partner: UNT Libraries Government Documents Department

Performance of several air ejectors with conical mixing sections and small secondary flow rates

Description: An investigation of several ejector configurations to determine the ability to handle the air required for engine cooling. The results are limited to investigations of conical-type mixing-section ejectors at ratios of mixing-section minimum diameter to primary-jet-nozzle diameter using unheated air. Results regarding experimental data, generalization of experimental data, spacing for maximum weight-flow ratio, ejector thrust, ejector configurations for constant weight-flow ratio, and selection of ejector design are provided.
Date: July 19, 1948
Creator: Huddleston, S. C.; Wilsted, H. D. & Ellis, C. W.
Partner: UNT Libraries Government Documents Department

General handling-qualities results obtained during acceptance flight tests of the Bell XS-1 airplane

Description: Report presenting measurements of the handling qualities of the Bell XS-1 transonic airplane using NACA instruments. Information regarding the stability and control characteristics and aerodynamic loads was obtained using two different airplanes in gliding and powered flight. Results regarding the longitudinal and lateral stability and control and stalling characteristics are provided.
Date: April 19, 1948
Creator: Williams, Walter C.; Forsyth, Charles M. & Brown, Beverly P.
Partner: UNT Libraries Government Documents Department

Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92

Description: Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87.
Date: April 19, 1948
Creator: Drake, Hubert M.; McLaughlin, Milton D. & Goodman, Harold R.
Partner: UNT Libraries Government Documents Department

Cyclic engine test of cast vitallium turbine buckets I

Description: Report presenting an investigation to correlate the engine service performance of cast Vitallium turbine buckets with standard laboratory metallurgical data. Data was obtained on four turbine wheels of Timken alloy with cast Vitallium buckets. Results regarding the engine test and metallurgical examination are provided.
Date: February 19, 1948
Creator: Farmer, J. Elmo; Darmara, F. N. & Poulson, Francis D.
Partner: UNT Libraries Government Documents Department

Ditching Tests of a 1/8-Scale Model of the Chance Vought XF6U-1 Airplane, TED No. NACA DE319

Description: Tests were made with a 1/8-scale dynamically similar model of the Chance Vought XF6U-1 airplane to study its behavior when ditched. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, by recording time histories of the accelerations, and by taking motion pictures of the ditchings. From the results of the tests it was concluded that the airplane should be ditched at the near-stall, tail-down attitude (12 deg). The flaps should be fully extended to obtain the lowest possible landing speed. The wing-tip tanks should be jettisoned. The underside of the fuselage will be critically damaged in a ditching and the airplane will dive violently after a run of about three fuselage lengths. Maximum longitudinal decelerations up to about 7g and maximum vertical accelerations up to about 5g will be encountered.
Date: January 19, 1948
Creator: Fisher, Lloyd J., Jr. & McBride, Ellis E.
Partner: UNT Libraries Government Documents Department

High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep

Description: A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression shock and extended to higher Mach numbers the speeds at which such changes occurred.
Date: December 19, 1947
Creator: Luoma, Arvo A.; Bielat, Ralph P. & Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department