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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees

A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees

Date: October 30, 1952
Creator: Gapcynski, John P; Hasel, Lowell E & Cooper, Morton
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Date: July 10, 1953
Creator: Kuhn, Richard E; Fournier, Paul G & Wiggins, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26

Rocket-model investigation to determine the hinge-moment and normal-force properties of a full-span, constant-chord, partially balanced trailing-edge control on a 60 degree clipped delta wing between Mach numbers of 0.50 and 1.26

Date: October 30, 1953
Creator: Martz, C William & Goslee, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Date: January 21, 1953
Creator: Johnson, Joseph L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigations toward simplification of missile control systems

Investigations toward simplification of missile control systems

Date: November 12, 1953
Creator: Strass, H Kurt; Crane, Harold L & Curfman, Howard J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Date: June 17, 1954
Creator: Burrows, Dale L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An experimental study of five annular air inlet configurations at subsonic and transonic speeds

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

Date: August 19, 1953
Creator: Pendley, Robert E; Bryan, Carroll R; Fleming, Frank F & Milillo, Joseph R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow

The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow

Date: November 12, 1952
Creator: Love, Eugene S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: December 19, 1952
Creator: Coletti, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Date: October 7, 1953
Creator: Radin, Edward J & Carpenter, Paul J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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