You limited your search to:

 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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
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
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
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon

Date: October 11, 1948
Creator: Reynolds, Robert M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Aeronautical characteristics of a three-blade propeller having NACA 10-(3)(08)-03 blades

Date: October 29, 1948
Creator: Davidson, Robert E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Air-flow behavior over the wing of an XP-51 airplane as indicated by wing-surface tufts at subcritical and supercritical speeds

Date: April 24, 1947
Creator: Beeler, De E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane

Date: April 8, 1947
Creator: Foster, Gerald V.
Description: The XF-12 airplane was designed by Republic Aviation Corporation to provide the Army Air Forces with a high performance, photo reconnaissance aircraft. A series of air-stream surveys were made n the vicinity of the empennage of a 1/8.33-scale powered model of the XF-12 airplane in the Langley 19-foot pressure tunnel. Surveys of the vortical-tail region were made through a range of yaw angles of plus or minus 20 degrees at a high and low angle of attack. The horizontal-tail surveys were made over a fairly wide range of angles of attack at zero degrees yaw. Several power and flap conditions were investigated. The results are presented in the form a dynamic pressure ratios, sidewash angles, and downwash angles plotted against vertical distance from the fuselage center line. The results of the investigation indicate that a vertical tail located in a conventional position would be in a field of flow where the dynamic pressure ratios at the horizontal tail to be increased; for equal lift coefficients, the effect of power or flap deflection on the direction of flow at any particular point in the region of the horizontal tail is small.
Contributing Partner: UNT Libraries Government Documents Department