You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Year: 1949
8 steps in grading soybeans : under revised standards, effective September 1, 1949.

8 steps in grading soybeans : under revised standards, effective September 1, 1949.

Date: June 1949
Creator: United States. Extension Service.
Description: An explanation of the process used by U.S. federal grain inspectors to grade soybeans. Factors include odor, weevil or garlic infestation, moisture, weight per bushel, foreign material, mixed colors, splits, and damage.
Contributing Partner: UNT Libraries Government Documents Department
234-5 Remote mechanical line design bases and schedules

234-5 Remote mechanical line design bases and schedules

Date: August 22, 1949
Creator: Gross, C.N.
Description: Short communication.
Contributing Partner: UNT Libraries Government Documents Department
Adobe or sun-dried brick for farm buildings.

Adobe or sun-dried brick for farm buildings.

Date: August 1949
Creator: Miller, T. A. H. (Thomas Arrington Huntington), 1885- & Molander, Edward G.
Description: Describes an efficient method of making and using adobe in the form of sun-dried bricks; describes how adobe bricks can be used in different parts of a building, such as: the roof, the boundary walls, the foundation, etc.
Contributing Partner: UNT Libraries Government Documents Department
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 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Date: October 1949
Creator: Loftin, Laurence K , Jr & Smith, Hamilton A
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
Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6).

Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6).

Date: December 1949
Creator: Schaefer, Raymond F & Smith, Hamilton A
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 Properties of Cruciform-Wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Aerodynamic Properties of Cruciform-Wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Date: June 1949
Creator: Spreiter, John R
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
FIRST PREV 1 2 3 4 5 NEXT LAST