Collection
Serial/Series Title
8 Matching Results
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8
Letter with Attachment, Apparent Carburization and Sensitization of APPR-1 Feul Plates
None
Date:
June 19, 1956
Creator:
Beaver, R. J.
System:
The UNT Digital Library
VIBRATION EFFECTS ON THE TAYLOR 206R PRESSURE TRANSMITTER. PART II
None
Date:
June 19, 1956
Creator:
Job, G.H. & Owen, J.A.
System:
The UNT Digital Library
Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model
Memorandum presenting an investigation to determine the roll effectiveness of a differentially deflected horizontal tail of a 42 degree swept-wing model. The model was tested through an angle-of-attack range of 0 degrees through the stall in the clean and landing configurations with the horizontal tail in a low position. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date:
June 19, 1956
Creator:
Boisseau, Peter C.
System:
The UNT Digital Library
Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1 to 1.8
Report discussing testing of a cruciform missile with a low-aspect-ratio wing and flap-type controls to determine the stability and control characteristics while rolling. Longitudinal stability and control effectiveness for this particular configuration were examined. The data obtained was compared to results from a similar model that was rolling significantly less.
Date:
June 19, 1956
Creator:
Lundstrom, Reginald R. & Baber, Hal T., Jr.
System:
The UNT Digital Library
Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1. To 1.8
Report presenting flight testing of a model of a cruciform missile configuration with a low-aspect-ratio wing equipped with flap-type controls in order to determine the stability and control characteristics while rolling at about 5 radians per second. Results indicated that if the ratio of roll rate to natural circular frequency in pitch is not greater than about 0.3, the motion following a step disturbance in pitch essentially remains in a plane in space. Results regarding time histories, normal force due to angle of attack, pitching moment due to angle of attack, damping, and control effectiveness are provided.
Date:
June 19, 1956
Creator:
Lundstrom, Reginald R. & Baber, Hal T., Jr.
System:
The UNT Digital Library
The effect of fluid injection on the compressible turbulent boundary layer : the effect of skin friction of air injected into the boundary layer of a cone at M = 2.7
Report presenting data from which the effects of transpiration air flow on average skin-friction coefficients and pressure drag of a conical model were evaluated. The model consisted of a truncated porous nose cone with a solid ogival nose section. Results regarding the pressure distribution, base pressure drag, average skin-friction coefficients, effects of transpiration air, and comparison with theory.
Date:
June 19, 1956
Creator:
Tendeland, Thorval & Okuno, Arthur F.
System:
The UNT Digital Library
Static lateral stability and control characteristics of a model of a 45 degree swept-wing fighter airplane with various vertical tails at Mach numbers of 1.41, 1.61, and 2.01
Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of a model of a 45 degree swept-wing fighter airplane. Results regarding the static stability characteristics and lateral and directional control are provided.
Date:
June 19, 1956
Creator:
Spearman, M. Leroy & Robinson, Ross B.
System:
The UNT Digital Library
Ditching Investigation of a 1/12-Scale Model of the Douglas F4D-1 Airplane, TED No. NACA DE 384
"A ditching investigation was made of a l/l2-scale dynamically similar model of the Douglas F4D-1 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tables, sequence photographs, time-history acceleration curves, and attitude curves" (p. 1).
Date:
June 19, 1956
Creator:
Windham, John O.
System:
The UNT Digital Library