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6 Matching Results
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Response of a Rotating Propeller to Aerodynamic Excitation
"The flexural vibration of a rotating propeller blade with clamped shank is analyzed with the object of presenting, in matrix form, equations for the elastic bending moments in forced vibration resulting from aerodynamic forces applied at a fixed multiple of rotational speed. Matrix equations are also derived which define the critical speeds end mode shapes for any excitation order and the relation between critical speed and blade angle. Reference is given to standard works on the numerical solution of matrix equations of the forms derived" (p. 1).
Date:
January 21, 1949
Creator:
Arnoldi, Walter E.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section
From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date:
October 21, 1949
Creator:
Goodson, Kenneth W. & Morrison, William D., Jr.
System:
The UNT Digital Library
Performance of 24-inch supersonic axial-flow compressor in air 2: performance of compressor rotor at equivalent tip speeds from 800 to 1765 feet per second
Report presenting an investigation of a 24-inch-diameter rotor for a supersonic axial-flow compressor in air up to an actual tip speed of 1654 feet per second and a maximum equivalent tip speed of 1765 feet per second. Results regarding overall performance, rotor-inlet characteristics, rotor-passage flow characteristics, and rotor-outlet characteristics are provided.
Date:
January 21, 1949
Creator:
Johnsen, Irving A.; Wright, Linwood C. & Hartmann, Melvin J.
System:
The UNT Digital Library
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation of a large-scale model at low speed
From Introduction: "This report presents the aerodynamic characteristics at low speed end high Reynolds number as determined in the Ames 40- by 80 foot wind tunnel."
Date:
January 21, 1949
Creator:
McCormack, Gerald M. & Walling, Walter C.
System:
The UNT Digital Library
The Effect of Span and Deflection of Split Flaps and Leading-Edge Roughness on the Longitudinal Stability and Gliding Characteristics of a 42 Degree Sweptback Wing Equipped With Leading-Edge Flaps
Report discussing the effect of half-span and full-span split flaps through a deflection range on the low-speed, longitudinal characteristics of a sweptback wing with a round-nose, extensible leading-edge flap. Information about the effect of split-flap deflection on lift and stalling characteristics, effect of split flaps on gliding characteristics, and effect of leading-edge roughness on longitudinal stability is presented.
Date:
June 21, 1949
Creator:
Pratt, George L. & Bollech, Thomas V.
System:
The UNT Digital Library
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-bump method
From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."
Date:
April 21, 1949
Creator:
Sleeman, William C., Jr. & Becht, Robert E.
System:
The UNT Digital Library