Coefficient of Friction, Oil Flow and Heat Balance of a Full-Journal Bearing

Coefficient of Friction, Oil Flow and Heat Balance of a Full-Journal Bearing

Date: October 1, 1947
Creator: Orloff, P. I.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Relation of turbojet propulsion system development to the strategic bomber mission

Relation of turbojet propulsion system development to the strategic bomber mission

Date: August 15, 1956
Creator: Rothrock, A. M.; Cesaro, R. S. & Walker, C. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Relation of currently estimated ANP performance to required ANP performance

Relation of currently estimated ANP performance to required ANP performance

Date: May 16, 1957
Creator: Cesaro, R. S. & Rothrock, A. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Theory of the Pitot and Venturi Tubes, Part 2

The Theory of the Pitot and Venturi Tubes, Part 2

Date: January 1, 1989
Creator: Buckingham, E.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigations of Pressure Distribution on Fast Flying Bodies

Investigations of Pressure Distribution on Fast Flying Bodies

Date: September 1, 1946
Creator: Stamm, G.
Description: The question to be treated is: how high is the pressure in the bow wave caused by a body flying at supersonic speed, and how far reaching are the destructive effects of that wave? The pressure distribution on an s.S. and an S. projectile of normal speed has been ascertained already by the methods of measurement used at the Ballistic Institute of the Technical Academy of the German Air Forces. Now similar investigations of the conditions on especially fast-flying bodies were carried out.
Contributing Partner: UNT Libraries Government Documents Department
Suggestions for Popularizing Civil Aviation

Suggestions for Popularizing Civil Aviation

Date: January 1, 1926
Creator: unknown
Description: The public generally is taking very little interest in the progress of Civil Aviation, and the time has come to educate the public in aeronautics and to make them realize the far-reaching importance of air transport. Briefly, the whole problem resolves itself into discovering and applying means for bringing some of the many aspects and effects of civil aviation into the everyday lives of the public. The report suggests three principal groups of methods: (1) Bring aviation into daily contact with the public. (2) Bring the public into daily contact with aviation. (3) General publicity.
Contributing Partner: UNT Libraries Government Documents Department
The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

The Lagrangian Multiplier Method of Finding Upper and Lower Limits to Critical Stresses of Clamped Plates

Date: January 1, 1946
Creator: Hu, Pai C. & Budiansky, Bernard
Description: The theory of Lagrangian multipliers is applied to the problem of finding both upper and lower limits to the true compressive buckling stress of a clamped rectangular plate. The upper and lower limits thus bracket the truss, which cannot be exactly found by the differential-equation approach. The procedure for obtaining the upper limit, which is believed to be new, presents certain advantages over the classical Raleigh-Rite method of finding upper limits. The theory of the lower-limit procedure has been given by Trefftz but, in the present application, the method differs from that of Trefftz in a way that makes it inherently more quickly convergent. It is expected that in other buckling problems and in some vibration problems problems the Lagrangian multiplier method finding upper and lower limits may be advantageously applied to the calculation of buckling stresses and natural frequencies.
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
Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane

Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane

Date: June 1, 1964
Creator: Lee, Henry A.
Description: An investigation has been made in the Langley spin tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried.
Contributing Partner: UNT Libraries Government Documents Department
Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane

Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane

Date: July 1, 1964
Creator: Lee, Henry A. & Healy, Frederick M.
Description: An investigation has been made of a 1/28-scale model of the Grumman A-6A airplane in the Langley spin tunnel. The erect spin and recovery characteristics of the model were determined for the flight design gross weight loading and for a loading with full internal fuel and empty external wing fuel tanks. The effects of extending slats and deflecting flaps were investigated. Inverted-spin and recovery characteristics of the model were determined for the flight design gross weight loading. The size of the spin-recovery tail parachute necessary to insure satisfactory spin-recovery was determined, and the effect of firing wing-mounded rockets during spins was investigated.
Contributing Partner: UNT Libraries Government Documents Department
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