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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees

Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees

Date: June 7, 1949
Creator: Schneiter, Leslie E & Hagerman, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle

Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle

Date: November 29, 1949
Creator: Johnson, Harold S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body

Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body

Date: February 2, 1950
Creator: Stivers, Louis S & Malick, Alexander W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wire cloth as porous material for transpiration-cooled walls

Wire cloth as porous material for transpiration-cooled walls

Date: November 13, 1951
Creator: Eckert, E R G; Kinsler, Martin R & Cochran, Reeves B
Description: The permeability characteristics and tensile strength of a porous material developed from stainless-steel corduroy wire cloth for use in transpiration-cooled walls where the primary stresses are in one direction were investigated. The results of this investigation are presented and compared with similar results obtained with porous sintered metal compacts. A much wider range of permeabilities is obtainable with the wire cloth than with the porous metal compacts considered and the ultimate tensile strength in the direction of the primary stresses for porous materials produced from three mesh sizes of wire cloth are from two to three times the ultimate tensile strengths of the porous metal compacts.
Contributing Partner: UNT Libraries Government Documents Department
Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Yaw characteristics and sidewash angles of a 42 degree sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000

Date: December 10, 1947
Creator: Salmi, Reino J & Fitzpatrick, James E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Yaw characteristics of a 52 degree sweptback wing of NACA 64(sub 1)-112 section with a fuselage and with leading-edge and split flaps at Reynolds numbers from 1.93 x 10(exp 6) to 6.00 x 10(exp 6)

Date: November 8, 1948
Creator: Salmi, Reino J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

Yawed-Landing Investigation of a Model of the Convair Y2-2 Airplane, TED No. NACA DE 363

Date: January 1, 1950
Creator: Hoffman, Edward L. & Fisher, Lloyd J.
Description: A model of the Convair Y2-2 airplane was tested in Langley tank no. 2 to determine whether satisfactory stability in yawed landings was possible with a certain ventral fin. Free-body landings were made in smooth and rough water at two speeds and two rates of descent with the model yawed 15deg. The behavior of the model was determined by visual observations and from motion-picture re.cords. It was concluded that satisfactory stability was possible with the ventral fin as tested but that the characteristics of the model shock absorbers and the settings of the elevon control surfaces had an appreciable influence on behavior.
Contributing Partner: UNT Libraries Government Documents Department
Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

Zero-angle-of-attack performance of two-dimensional inlets near Mach number 3

Date: February 29, 1956
Creator: Woollett, Richard R & Connors, James F
Description: An extensive program was undertaken to investigate the effect of several geometric variables on the performance of two-dimensional inlets. This investigation included inlets having single-wedge, double-wedge, and isentropic compression ramps with various side-plate configurations and subsonic diffusers. The tests were conducted over a range of Reynolds number based on inlet height from 0.50 to 2.67(sup x)10(sup 6). Generally, the performance levels of the two-dimensional inlets were somewhat below those obtained previously with comparable axisymmetric models. At Mach number 3.05 the optimum total-pressure recovery was obtained with an isentropic inlet which compressed the external flow to a Mach number of 1.88. Rectangular side plates and a long high-exit-Mach-number subsonic diffuser with filleted corners were used with this inlet. A critical total-pressure recovery of 0.71 was realized with a corresponding mass-flow ratio of 0.965. Subcritical stability to a mass-flow ratio of 0.60 was obtained.
Contributing Partner: UNT Libraries Government Documents Department
Zero-lift drag of a large fuselage cavity and a partially submerged store on a 52.5 degree sweptback-wing-body configuration as determined from free-flight tests at Mach numbers of 0.7 to 1.53

Zero-lift drag of a large fuselage cavity and a partially submerged store on a 52.5 degree sweptback-wing-body configuration as determined from free-flight tests at Mach numbers of 0.7 to 1.53

Date: February 26, 1957
Creator: Hoffman, Sherwood
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Zero-lift drag of a series of bomb shapes at Mach numbers from 0.60 to 1.10

Zero-lift drag of a series of bomb shapes at Mach numbers from 0.60 to 1.10

Date: July 26, 1956
Creator: Stoney, William E, Jr & Royall, John F
Description: None
Contributing Partner: UNT Libraries Government Documents Department