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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
A theoretical investigation of the dynamic lateral oscillatory stability of an airplane having a 60 degree triangular wing

A theoretical investigation of the dynamic lateral oscillatory stability of an airplane having a 60 degree triangular wing

Date: March 8, 1950
Creator: Johnson, Joseph L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the dynamic lateral stability characteristics of Douglas design No. 39C, an early version of the X-3 research airplane

Theoretical investigation of the dynamic lateral stability characteristics of Douglas design No. 39C, an early version of the X-3 research airplane

Date: January 18, 1949
Creator: Bennett, Charles V
Description: Contains results of calculations made to determine the neutral oscillatory stability boundaries, period and time to damp of the oscillatory mode, and motions following disturbances. The calculations were made for Mach numbers of 0.75 and 2.3 at an attitude of 35,000 feet and for the landing condition at sea level.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the dynamic lateral stability characteristics of the Douglas X-3 research airplane : study 41-B

Theoretical investigation of the dynamic lateral stability characteristics of the Douglas X-3 research airplane : study 41-B

Date: April 27, 1950
Creator: Bennett, Charles V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the MX-838 (XB-51) Airplane

A Theoretical Investigation of the Dynamic Lateral Stability Characteristics of the MX-838 (XB-51) Airplane

Date: January 1, 1948
Creator: Paulson, Jon W.
Description: At the request of the Air Material Command, U. S. Air Force, a theoretical study has been made of the dynamic lateral stability characteristics of the MX-838 (XB-51) airplane. The calculations included the determination of the neutral-oscillatory-stability boundary (R = 0), the period and time to damp to one-half amplitude of the lateral oscillation, end the time to damp to one-half amplitude for the spiral mode. Factors varied in the investigation were lift coefficient, wing incidence, wing loading, and altitude. The results of the investigation showed that the lateral oscillation of the airplane is unstable below a lift coefficient of 1.2 with flaps . deflected 40deg but is stable over the entire speed range with flaps deflected 20deg or 0deg. The results showed that satisfactory oscillatory stability can probably be obtained for all lift coefficients with the proper variation of flap deflection and wing incidence with airspeed. Reducing the positive wing incidence improved the oscillatory stability characteristics. The airplane is spirally unstable for most conditions but the instability is mild and the Air Force requirements are easily met.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the effect of a target seeker sensitive to pitch attitude on the dynamic stability and response characteristics of a supersonic canard missile configuration

A theoretical investigation of the effect of a target seeker sensitive to pitch attitude on the dynamic stability and response characteristics of a supersonic canard missile configuration

Date: August 26, 1952
Creator: Gates, Ordway B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the effect of auxiliary damping on the longitudinal response of a transonic bomber configuration in flight through continuous turbulence

A theoretical investigation of the effect of auxiliary damping on the longitudinal response of a transonic bomber configuration in flight through continuous turbulence

Date: March 1, 1955
Creator: Bridgland, T F , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the effect of partial wing lift of hydrodynamic landing characteristics of V-bottom seaplanes in step impacts

A theoretical investigation of the effect of partial wing lift of hydrodynamic landing characteristics of V-bottom seaplanes in step impacts

Date: November 1, 1952
Creator: Sims, Joseph L
Description: A theoretical investigation is made of the loads and motions in water-landing impacts of wide prismatic V-bottom seaplanes for constant partial wing-lift conditions where the resultant velocity of the seaplane is normal to the keel. An approximate method is given for applying the results of this investigation to the more general case of oblique impact. The increase in vertical hydrodynamic load factor due to wing-lift reduction is shown to be approximately 133 percent of the decrease in air load.
Contributing Partner: UNT Libraries Government Documents Department
:Theoretical investigation of the effect of the ailerons on the wing of an airplane

:Theoretical investigation of the effect of the ailerons on the wing of an airplane

Date: April 1, 1929
Creator: Wieselsberger, C
Description: The present work investigates, on the basis of Prandtl's wing theory, the form of the lift distribution when the ailerons are deflected in opposite directions. An ideal fluid and a wing with a rectangular form are assumed. The moments must not cause any rotation of the wing or any deviation from the rectilinear motion.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the effect of yawing moment due to rolling on lateral oscillatory stability

A theoretical investigation of the effect of yawing moment due to rolling on lateral oscillatory stability

Date: October 1, 1948
Creator: Johnson, Joseph L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the effect on the lateral oscillations of an airplane of an automatic control sensitive to yawing accelerations

A theoretical investigation of the effect on the lateral oscillations of an airplane of an automatic control sensitive to yawing accelerations

Date: January 1, 1950
Creator: Beckhardt, Arnold R
Description: None
Contributing Partner: UNT Libraries Government Documents Department