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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response

Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response

Date: August 13, 1952
Creator: Abramovitz, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response

Date: August 13, 1952
Creator: Abramovitz, M.
Description: Proportional navigation guidance systems - radar antenna positioning effects on speed of response.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response

Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response

Date: January 19, 1953
Creator: Abramovitz, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Theoretical Investigation of the Rolling Oscillations of an Airplane with Ailerons Free

A Theoretical Investigation of the Rolling Oscillations of an Airplane with Ailerons Free

Date: January 1, 1944
Creator: Cohen, Doris
Description: An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Report No. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions. If the ailerons tend to float against the wind and have a high degree of aerodynamic balance, rolling oscillations, in addition to the normal lateral oscillations, are likely to occur. On the basis of the equations including only the rolling motion and the aileron deflection, formulas are derived for the stability and damping of the rolling oscillations in terms of the hinge moment derivatives and other characteristics of the ailerons and airplane. Charts are also presented showing the oscillatory regions and stability boundaries for a fictitious airplane of conventional proportions. The effects of friction in the control system are investigated and discussed. If the ailerons tend to trail with the wind, the condition for stable variation of stick force with aileron deflection is found to ...
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the rolling oscillations of an airplane with ailerons free

A theoretical investigation of the rolling oscillations of an airplane with ailerons free

Date: January 1, 1944
Creator: Cohen, Doris
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the rolling oscillations of an airplane with ailerons free

A theoretical investigation of the rolling oscillations of an airplane with ailerons free

Date: January 1, 1944
Creator: Cohen, Doris
Description: An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Technical Report no. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions. If the ailerons tend to float against the wind and have a high degree of aerodynamic balance, rolling oscillations, in addition to the normal lateral oscillations, are likely to occur. On the basis of the equations including only the rolling motion and the aileron deflection, formulas derived for the stability and damping of the rolling oscillations in terms of the hinge-moment derivatives are also presented showing the oscillatory regions and stability boundaries for a fictitious airplane of conventional proportion. The effects of friction in the control system are investigated and discussed.
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the short-period dynamic longitudinal stability of airplane configurations having elastic wings of 0 degree to 60 degrees sweepback

A theoretical investigation of the short-period dynamic longitudinal stability of airplane configurations having elastic wings of 0 degree to 60 degrees sweepback

Date: December 1, 1954
Creator: Mclaughlin, Milton D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the stability at negative static margins of a supersonic missile with an autopilot sensitive to pitch angle and pitching velocity

Theoretical investigation of the stability at negative static margins of a supersonic missile with an autopilot sensitive to pitch angle and pitching velocity

Date: March 17, 1952
Creator: Cole, Henry, A , jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the supersonic lift and drag of thin, sweptback wings with increased sweep near the root

Theoretical investigation of the supersonic lift and drag of thin, sweptback wings with increased sweep near the root

Date: June 1, 1953
Creator: Cohen, Doris
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of thrust augmentation of turbojet engines by tail-pipe burning

Theoretical investigation of thrust augmentation of turbojet engines by tail-pipe burning

Date: January 28, 1947
Creator: Bohanon, H R
Description: None
Contributing Partner: UNT Libraries Government Documents Department