National Advisory Committee for Aeronautics (NACA) - 22 Matching Results

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Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

Description: Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern w… more
Date: August 11, 1952
Creator: Connors, James F. & Woollett, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Tips on a 45 Degree Sweptback Wing and Body Combination

Description: Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.
Date: January 11, 1952
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at a Mach Number of 1.2 of Two 45 Degree Sweptback Wings Utilizing NACA 2-006 and NACA 65A006 Airfoil Sections

Description: Report presenting an investigation in the low-turbulence pressure tunnel at Mach number 1.2 to determine lift, drag, and moment characteristics of a wing with an airfoil section designed for maximum lift at low speeds, 45 degrees of sweepback, aspect ratio 4, and taper ratio 0.6. A similar wing with the NACA 65A006 airfoil section was also investigated and compared to the experimental wing.
Date: September 11, 1952
Creator: Wilson, Homer B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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 disagre… more
Date: August 11, 1952
Creator: Deissler, Robert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force characteristics in the submerged and planing condition of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane

Description: From Summary: "Force characteristics determined from tank tests of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions."
Date: July 11, 1952
Creator: Land, Norman S. & Pelz, Charles A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests at Mach Number 1.62 of a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces

Description: Memorandum presenting an investigation at a Mach number of 1.62 in the 9-inch supersonic tunnel of a series of missile configurations with tandem lifting surfaces of low aspect ratio and of nearly equal span. Some of the variables investigated were interdigitation angle, wing and tail plan form, and longitudinal location of wing with respect to tail. Lift, drag, and pitching-moment data are presented, together with center-of-pressure locations and tail-lift efficiency factors.
Date: January 11, 1952
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Low-Speed Longitudinal Stability Characteristics of a Swept-Wing Airplane Model With Two Modifications to the Wing-Root Plan Form

Description: Report presenting a wind-tunnel investigation to determine the effects of two wing-root leading-edge plan-form modifications, including a notched leading-edge fillet and a rounded leading-edge fillet, on the low-speed longitudinal stability characteristics of an airplane model with a 50.7 degree sweptback wing. Results regarding stability at zero lift, variation of stability with lift coefficient, and lift and drag characteristics are provided.
Date: July 11, 1952
Creator: Kemp, William B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed longitudinal aerodynamic characteristics of a twisted and cambered wing of 45 degree sweepback and aspect ratio 8 with and without high-lift and stall-control devices and a fuselage at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6

Description: Report presenting a low-speed investigation of the static longitudinal aerodynamic characteristics of a twisted and cambered wing with 45 degrees of sweepback and an aspect ratio of 8.0 in the 19-foot pressure tunnel. Testing included the effects of leading- and trailing-edge flaps, flow control fences, and a fuselage. Report presenting longitudinal stability characteristics, lift characteristics, drag characteristics, fuselage effects, Reynolds number effects, effect of wing roughness are prov… more
Date: June 11, 1952
Creator: Salmi, Reino J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Description: "A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and … more
Date: April 11, 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented.
Date: January 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Mach Numbers of 1.62 and 1.93 of the Lift Effectiveness and Integrated Downwash Characteristics of Several In-Line Missile Configurations Having Equal-Span Wings and Tails

Description: Memorandum presenting an investigation made at Mach numbers of 1.62 and 1.93 to determine the lift effectiveness and average downwash characteristics of several in-line missile configurations with rectangular and triangular tail plan forms. Breakdown tests were made for combinations of a body and four wing plan forms and two tail plan forms. Results regarding lift and drag results, pitching-moment results, and integrated downwash effects are provided.
Date: April 11, 1952
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Time Histories of Maneuvers Performed With an F-86A Airplane During Squadron Operations

Description: Report presenting some preliminary time-history results of maneuvers performed during US Air Force squadron operations with an F-86A jet-fighter airplane. The information covers a speed range from stall to 530 mph-indicated airspeed and pressure altitudes varying from sea level to approximately 25,000 feet.
Date: February 11, 1952
Creator: Hamer, Harold A. & Henderson, Campbell
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Initial results of instrument-flying trials conducted in a single-rotor helicopter

Description: "Instrument-flying trials have been conducted in a single-rotor helicopter, the maneuver stability of which could be changed from satisfactory to unsatisfactory. The results indicated that existing longitudinal flying-qualities requirements based on contact flight were adequate for instrument flight at speeds above that for minimum power. However, lateral-directional problems were encountered at low speeds and during precision maneuvers" (p. 1).
Date: March 11, 1952
Creator: Crim, Almer D.; Reeder, John P. & Whitten, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some control considerations for ram-jet engines

Description: Control requirements were determined from calculated engine performance maps for a fixed-geometry ram jet of a configuration suitable for strategic supersonic missile propulsion. Several control schemes for attaining desired engine performance and for stabilizing missile flight velocity during cruise are presented. The advantages and disadvantages of each system are discussed.
Date: August 11, 1952
Creator: Himmel, Seymour C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers

Description: "The static longitudinal stability characteristics of a 0.15-scale model of the Hermes A-lE2 missile have been determined in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.98, corresponding to Reynolds numbers, based on body length, of 12.3 x 10(exp 6) to 17.1 x 10(exp 6). This paper presents results obtained with body alone and body-fins combinations at 0 degrees (one set of fins vertical and the other set horizontal) and 45 degree angle of roll. The results … more
Date: September 11, 1952
Creator: Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Normal Component of the Induced Velocity in the Vicinity of a Lifting Rotor and Some Examples of Its Application

Description: "Paper presents a practical method for computing the approximate values of the normal component of the induced velocity at points in the flow field of a lifting rotor. Tables and graphs of the relative magnitudes of the normal component of the induced velocity are given for selected points in the longitudinal plane of symmetry of the rotor and on the lateral rotor axis. A method is also presented for utilizing the tables and graphs to determine the interference induced velocities arising from t… more
Date: August 11, 1952
Creator: Castles, Walter, Jr. & De Leeuw, Jacob Henri
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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