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 Decade: 1940-1949
 Year: 1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Aerodynamic characteristics at subsonic and transonic speeds of a 42.7 degree sweptback wing model having an aileron with finite trailing-edge thickness

Date: January 12, 1949
Creator: Lockwood, Vernard E; Vogler, Raymond D & Turner, Thomas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Description: An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale moue1 of the Fairchild Lark missile, The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses. The wind-tunnel-test data indicate that rolling the missile 22.5 deg. had no serious effect on the static longitudinal stability. The desired maneuvering acceleration could not be attained with any of the horizontal wings tested, even with the horizontal wing flaps deflected 50 deg. The flaps on the 64A-209 wing (with small trailing-edge angles and flat sides) were effective at all flap deflections, while the flaps on the 16-series wings (with large trailing-edge angles) lost effectiveness at small flap deflections. The data showed that rolling moment existed when the vertical wing flaps were deflected with the model at other than zero angle of attack. A similar rolling moment probably would be found . with the horizontal wing flaps deflected and the model yawed.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method

Date: March 4, 1949
Creator: Lina, Lindsay J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Date: February 11, 1949
Creator: Macleod, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bumb method

Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bumb method

Date: April 21, 1949
Creator: Sleeman, William C , Jr & Becht, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Date: February 24, 1949
Creator: Goodson, Kenneth W & Weil, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section

Date: November 1, 1949
Creator: Goodson, Kenneth W & Few, Albert G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Date: September 6, 1949
Creator: King, Thomas J , Jr & Myers, Boyd C , II
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Date: October 21, 1949
Creator: Goodson, Kenneth W & Morrison, William D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of an 0.08-scale model of the Martin XB-51 Airplane at high subsonic speeds

Aerodynamic characteristics of an 0.08-scale model of the Martin XB-51 Airplane at high subsonic speeds

Date: October 7, 1949
Creator: Barnes, Robert H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Aerodynamic characteristics of an airfoil-forebody swept flying-boat hull with a wing and tail swept back 51.3 degrees at the leading edge

Date: September 9, 1949
Creator: Naeseth, Rodger L & Macleod, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

The aerodynamic characteristics throughout the subsonic speed range of a thin, sharp-edged horizontal tail of aspect ratio 4 equipped with a constant-chord elevator

Date: June 30, 1949
Creator: Bandettini, Angelo & Reed, Verlin D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Date: October 7, 1949
Creator: Mccormack, Gerald M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Date: January 26, 1949
Creator: Madden, Robert T
Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Date: July 7, 1949
Creator: Mas, Newton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics throughout the subsonic speed range with the wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics throughout the subsonic speed range with the wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Date: August 15, 1949
Creator: Jones, J Lloyd & Demele, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects at subsonic speeds of a constant-chord elevon on a wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects at subsonic speeds of a constant-chord elevon on a wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Date: December 5, 1949
Creator: Jones, J Lloyd & Demele, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed

Date: May 19, 1949
Creator: Hopkins, Edward J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation at a Mach number of 1.53 to determine the effects of cambering and twisting the wing for uniform load at a lift coefficient of 0.25

Date: May 6, 1949
Creator: Madden, Robert T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation of a large-scale model at low speed

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : investigation of a large-scale model at low speed

Date: January 21, 1949
Creator: Mccormack, Gerald M & Walling, Walter C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-chamber performance of British Rolls-Royce Nene II engine I : standard 18.75-inch-diameter jet nozzle

Altitude-chamber performance of British Rolls-Royce Nene II engine I : standard 18.75-inch-diameter jet nozzle

Date: September 23, 1949
Creator: Barson, Zelmar & Wilsted, H D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-chamber performance of British Rolls-Royce Nene II engine II : 18.41-inch-diameter jet nozzle

Altitude-chamber performance of British Rolls-Royce Nene II engine II : 18.41-inch-diameter jet nozzle

Date: October 26, 1949
Creator: Wilsted, H D; Armstrong, J C & Vincent, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Date: November 8, 1949
Creator: Conrad, E William & Prince, William R
Description: An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel. Several fuel systems and flame holders were investigated in a 29-inch-diameter tail-pipe burner to determine the effect of fuel distribution and flame-holder design on tail-pipe-burner performance and operational characteristics over a range of simulated flight conditions. At an altitude of 5000 feet, the type of flame holder used had only a slight effect on the combustion efficiency. As the altitude was increased, the decrease in peak combustion efficiency became more rapid as the blocking area of the flame holder was reduced. At all altitudes investigated, an improvement in the uniformity of the radial distribution of fuel and air slightly increased the peak combustion efficiencies and shifted the peak combustion efficiency to higher tail-pipe fuel-air ratios. The use of an internal cooling liner extending the full length of the tail-pipe combustion chamber provided adequate shell cooling at all flight conditions investigated.
Contributing Partner: UNT Libraries Government Documents Department
Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Description: An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6. Similar information was obtained for AN-F-32 fuel at a flight Mach number of 0.0.
Contributing Partner: UNT Libraries Government Documents Department
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