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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1956
 Collection: Technical Report Archive and Image Library
The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams

The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams

Date: April 1956
Creator: Davenport, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acoustics of a nonhomogeneous moving medium.

Acoustics of a nonhomogeneous moving medium.

Date: February 1, 1956
Creator: Blokhintsev, D I
Description: Theoretical basis of the acoustics of a moving nonhomogeneous medium is considered in this report. Experiments that illustrate or confirm some of the theoretical explanation or derivation of these acoustics are also included.
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of Combustion Principles to Aircraft Propulsion, Volume 2, Combustion in Air-Breathing Jet Engines

Adaptation of Combustion Principles to Aircraft Propulsion, Volume 2, Combustion in Air-Breathing Jet Engines

Date: May 2, 1956
Creator: unknown
Description: This volume continues the NACA study of combustion principles for aircraft propulsion. The various aspects of combustion pertinent to jet engines are organized and interpreted with quite extensive information, particularly for basic or fundamental. subject matter. The report concerns only air-breathing engines and hydrocarbon fuels, and not rocket engines and high-energy fuels. Since the references have been selected to illustrate important points, the bibliographies, while thorough, are not complete. This volumes describes the observed performance and design problems of engine combustors of the principal types. These include combustor-inlet conditions; starting, acceleration, combustion limits, combustion efficiency, coke deposits, and smoke formation in turbojets; ram-jet performance; and afterburner performance and design.
Contributing Partner: UNT Libraries Government Documents Department
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Date: September 24, 1956
Creator: Henry, Beverly Z JR & Cahn, Maurice S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Date: December 5, 1956
Creator: Bielat, Ralph P; Coffee, Claude W , Jr & Petynia, William W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Date: November 1, 1956
Creator: Mitcham, Grady L; Stevens, Joseph E & Norris, Harry P
Description: A flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach numbers of 1.61 and 2.01 of various tip controls on the wing panel of a 0.05-scale model of a Martin XASM-N-7 (Bullpup) missile : TED No. NACA AD 3106

Aerodynamic characteristics at Mach numbers of 1.61 and 2.01 of various tip controls on the wing panel of a 0.05-scale model of a Martin XASM-N-7 (Bullpup) missile : TED No. NACA AD 3106

Date: February 1, 1956
Creator: Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390

Date: May 23, 1956
Creator: Driver, Cornelius
Description: Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined. The results indicate that for a horizontal-tail incidence of -10 deg the trim lift coefficient varied from 0.29 at a Mach number of 1.61 to 0.23 at a Mach number of 2.01 with a corresponding decrease in lift-drag trim from 3.72 to 3.15. Stick-position instability was indicated in the low-supersonic-speed range. A photographic-type nose modification resulted in slightly higher values of minimum drag coefficient but did not significantly affect the static stability or lift-curve slope. The minimum drag coefficient for the complete model with the production nose remained essentially constant at 0.047 throughout the Mach number range investigated.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102B airplane at Mach numbers of 1.41, 1.61, and 2.01 : COORD No. AF-231

Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102B airplane at Mach numbers of 1.41, 1.61, and 2.01 : COORD No. AF-231

Date: February 27, 1956
Creator: Driver, Cornelius & Robinson, Ross B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 6-percent-thick symmetrical circular-arc airfoil having a 30-percent-chord trailing-edge flap at a Mach number of 6.9

Aerodynamic characteristics of a 6-percent-thick symmetrical circular-arc airfoil having a 30-percent-chord trailing-edge flap at a Mach number of 6.9

Date: May 5, 1956
Creator: Ridyard, Herbert W & Fetterman, David E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic control of supersonic inlets for optimum performance

Aerodynamic control of supersonic inlets for optimum performance

Date: February 20, 1956
Creator: Wilcox, Fred A & Perchonok, Eugene
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic damping at Mach numbers of 1.3 and 1.6 of a control surface on a two-dimensional wing by a free-oscillation method

Aerodynamic damping at Mach numbers of 1.3 and 1.6 of a control surface on a two-dimensional wing by a free-oscillation method

Date: May 1, 1956
Creator: Tuovila, W J & Hess, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic design of axial-flow compressors Volume 1

Aerodynamic design of axial-flow compressors Volume 1

Date: August 1, 1956
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Design of Axial-Flow Compressors, Volume 2

Aerodynamic Design of Axial-Flow Compressors, Volume 2

Date: August 1, 1956
Creator: unknown
Description: Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of the magnitude of the reference total-pressure loss and the reference deviation and incidence angles for conventional blade profiles. These relations are developed in simplified forms readily applicable to compressor design procedures.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic design of axial-flow compressors. Volume III

Aerodynamic design of axial-flow compressors. Volume III

Date: August 1, 1956
Creator: Johnson, Irving A; Bullock, Robert O; Graham, Robert W; Costilow, Eleanor L; Huppert, Merle C; Benser, William A et al.
Description: Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0

Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0

Date: September 26, 1956
Creator: Hoffman, Sherwood & Chauvin, Leo T
Description: None
Contributing 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

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

Date: September 11, 1956
Creator: Swanson, Andrew G & Rumsey, Charles B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating of aircraft components

Aerodynamic heating of aircraft components

Date: February 14, 1956
Creator: Chauvin, Leo T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic investigation of a parabolic body of revolution at mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Aerodynamic investigation of a parabolic body of revolution at mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Date: September 1, 1956
Creator: Love, Eugene S
Description: An aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base. Measurements with the jet inoperative were made of lift, drag, pitching moment, base pressures, and radial and axial pressures. With the jet in operation, pressure measurements were made over the rear of the body with the primary variables being angle of attack, ratio of jet velocity to stream velocity, and ratio of pressure at jet exit to stream pressure.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loadings associated with swept and unswept spoilers on a flat-plate at Mach numbers of 1.61 and 2.01

Aerodynamic loadings associated with swept and unswept spoilers on a flat-plate at Mach numbers of 1.61 and 2.01

Date: March 12, 1956
Creator: Lord, Douglas R & Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loads on an external store adjacent to a 60 deg delta wing at mach numbers from 0.75 to 1.96

Aerodynamic loads on an external store adjacent to a 60 deg delta wing at mach numbers from 0.75 to 1.96

Date: April 24, 1956
Creator: Hadaway, W. M.
Description: Aerodynamic loads on external store adjacent to 60 deg delta wing at Mach numbers 0.75 to 1.96.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Date: February 17, 1956
Creator: Hadaway, W. M.
Description: Aerodynamic loads on high-speed aircraft external store adjacent to an unswept wing at mach 0.75 to 1.96.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic loads on an external store adjacent to an unswept wing at Mach numbers between 0.75 and 1.96

Aerodynamic loads on an external store adjacent to an unswept wing at Mach numbers between 0.75 and 1.96

Date: February 17, 1956
Creator: Hadaway, William M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic mixing downstream from line source of heat in high-intensity sound field

Aerodynamic mixing downstream from line source of heat in high-intensity sound field

Date: August 1, 1956
Creator: Mickelson, William R & Baldwin, Lionel V
Description: Theory and measurement showed that the heat wake downstream from a line source is displaced by a transverse standing sound wave in a manner similar to a flag waving in a harmonic mode. With a 147 db, 104 cps standing wave, time-mean temperatures were reduced by an order of magnitude except near the displacement-pattern nodal points. The theory showed that a 161 db, 520 cps standing wave considerably increased the mixing in both the time-mean and instantaneous senses.
Contributing Partner: UNT Libraries Government Documents Department
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