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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15271 - 15294 of 19,794
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Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

Date: March 4, 1958
Creator: Sherman, Windsor L; Faber, Stanley & Whitten, James B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of surface roughness and extreme cooling on boundary-layer transition for 15 deg cone-cylinder in free flight at Mach numbers to 7.6

Effects of surface roughness and extreme cooling on boundary-layer transition for 15 deg cone-cylinder in free flight at Mach numbers to 7.6

Date: March 5, 1958
Creator: Rabb, L. & Krasnican, M. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of the effect of circumferential inlet flow distortion on the performance of a five-stage axial-flow research compressor with transonic rotors in all stages

Experimental investigation of the effect of circumferential inlet flow distortion on the performance of a five-stage axial-flow research compressor with transonic rotors in all stages

Date: March 5, 1958
Creator: Robbins, William H & Glaser, Frederick
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of a two-dimensional cascade inlet at a free-stream Mach number of 3.05 and at angles of attack of -3 degrees, 0 degrees, 3 degrees, and 6 degrees

Performance of a two-dimensional cascade inlet at a free-stream Mach number of 3.05 and at angles of attack of -3 degrees, 0 degrees, 3 degrees, and 6 degrees

Date: March 5, 1958
Creator: Woolett, Richard R & Ferguson, Harold M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of canard surface size on stability and control characteristics of two canard airplane configuration at Mach numbers of 1.41 and 2.01

Effects of canard surface size on stability and control characteristics of two canard airplane configuration at Mach numbers of 1.41 and 2.01

Date: March 6, 1958
Creator: Spearman, M Leroy & Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of a high-flow transonic-compressor inlet stage having a hub-tip radius of 0.35

Investigation of a high-flow transonic-compressor inlet stage having a hub-tip radius of 0.35

Date: March 6, 1958
Creator: Felix, A Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the longitudinal aerodynamic characteristics of a trapezoidal-wing airplane model with various vertical positions of wing and horizontal tail at Mach numbers of 1.41 and 2.01

Investigation of the longitudinal aerodynamic characteristics of a trapezoidal-wing airplane model with various vertical positions of wing and horizontal tail at Mach numbers of 1.41 and 2.01

Date: March 6, 1958
Creator: Foster, Gerald V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Supersonic Wave Interference Affecting Stability

Supersonic Wave Interference Affecting Stability

Date: March 8, 1958
Creator: Love, Eugene S.
Description: Some of the significant interference fields that may affect stability of aircraft at supersonic speeds are briefly summarized. Illustrations and calculations are presented to indicate the importance of interference fields created by wings, bodies, wing-body combinations, jets, and nacelles.
Contributing Partner: UNT Libraries Government Documents Department
Effect of distributed granular-type roughness on boundary-layer transition at supersonic speeds with and without surface cooling

Effect of distributed granular-type roughness on boundary-layer transition at supersonic speeds with and without surface cooling

Date: March 10, 1958
Creator: Braslow, Albert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental lift-drag ratios for two families of wing-body combinations at supersonic speeds

Experimental lift-drag ratios for two families of wing-body combinations at supersonic speeds

Date: March 10, 1958
Creator: Jorgensen, Leland H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Longitudinal and lateral stability and control characteristics at Mach number 2.01 of a 60 degree delta-wing airplane configuration equipped with a canard control and with wing trailing-edge flap controls

Longitudinal and lateral stability and control characteristics at Mach number 2.01 of a 60 degree delta-wing airplane configuration equipped with a canard control and with wing trailing-edge flap controls

Date: March 10, 1958
Creator: Spearman, M Leroy & Driver, Cornelius
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30 Deg Blunted Nose Cone

Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30 Deg Blunted Nose Cone

Date: March 10, 1958
Creator: Hopko, R. N. & Strass, H. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Date: March 10, 1958
Creator: Robinson, R. B.
Description: An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested were a body alone which had a ratio of length to diameter of 10, the body with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose. Various canard surfaces for pitch control only were tested on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
External Environmental Radiation Measurements in the United States

External Environmental Radiation Measurements in the United States

Date: March 11, 1958
Creator: Solon, Leonard R.; Lowder, Wayne M.; Zila, Albert; LeVine, H. D.; Blatz, Hanson & Eisenbud, Merril
Description: Report regarding ion chamber measurements made of the external environmental radiation in various location in the United States during the summer of 1957.
Contributing Partner: UNT Libraries Government Documents Department
Portable Mercury Vapor Detector

Portable Mercury Vapor Detector

Date: March 14, 1958
Creator: McMurray, C. S. & Redmond, J. W.
Description: From abstract: "This report describes a functional mercury vapor detector which is a portable, self-contained, survey instrument, and had a minimum range from zero to two-tenths milligram of mercury per cubic meter of air."
Contributing Partner: UNT Libraries Government Documents Department
An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

Date: March 17, 1958
Creator: Neel, C. B.
Description: Aerodynamic heating of sweptback wing leading edge.
Contributing Partner: UNT Libraries Government Documents Department
Section thrust coefficients for a full-scale, three-blade, supersonic-type propeller operating at low and negative blade angles

Section thrust coefficients for a full-scale, three-blade, supersonic-type propeller operating at low and negative blade angles

Date: March 17, 1958
Creator: Salters, Leland B & Lewis, Martha C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional cascade investigation at Mach numbers up to 1.0 of NACA 65-series blade sections at conditions typical of compressor tips

Two-dimensional cascade investigation at Mach numbers up to 1.0 of NACA 65-series blade sections at conditions typical of compressor tips

Date: March 17, 1958
Creator: Dunavant, James C & Emery, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Date: March 18, 1958
Creator: Dryer, Murray & Luidens, Roger W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of two-stage counterrotating turbine efficiencies in terms of work and speed requirements

Analysis of two-stage counterrotating turbine efficiencies in terms of work and speed requirements

Date: March 18, 1958
Creator: Wintucky, William T & Stewart, Warner L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of flutter characteristics for finite-span swept or unswept wings at subsonic and supersonic speeds by a modified strip analysis

Calculation of flutter characteristics for finite-span swept or unswept wings at subsonic and supersonic speeds by a modified strip analysis

Date: March 18, 1958
Creator: Yates, E Carson, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of two bluff shapes in axial free flight over a Mach number range from 0.35 and 2.15

Investigation of two bluff shapes in axial free flight over a Mach number range from 0.35 and 2.15

Date: March 18, 1958
Creator: Coltrane, Lucille C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of two bluff shapes in axial free flight over a Mach number range from 0.35 to 2.15

Investigation of two bluff shapes in axial free flight over a Mach number range from 0.35 to 2.15

Date: March 18, 1958
Creator: Coltrane, L. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary investigation of land-water operation with a 1/10-scale model of a jet airplane equipped with hydro-skis

Preliminary investigation of land-water operation with a 1/10-scale model of a jet airplane equipped with hydro-skis

Date: March 18, 1958
Creator: Thompson, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department