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An investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback vertical tail in sideslip with and without a 45 degree sweptback horizontal tail located on the fuselage center line
Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distribution at six spanwise stations on a 45 degree sweptback, untapered vertical tail in sideslip. The presence of the horizontal tail slightly increased the value of section normal-force coefficients on the vertical tail but did not materially alter the nature of the load distribution.
Date:
November 2, 1954
Creator:
Wiley, Harleth G. & Moseley, William C., Jr.
System:
The UNT Digital Library
Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique
Memorandum presenting the carpet-plotting technique as a more useful and concise method of summarizing the 65-series compressor-blade cascade data. Four different carpet plots are presented. A sample use of the carpet plots is also provided.
Date:
November 2, 1954
Creator:
Felix, A. Richard
System:
The UNT Digital Library
Methods of predicting helicopter stability
From Summary: "Some of the methods of predicting rotor stability derivatives have been reviewed. The methods by which these rotor derivatives are employed to estimate helicopter stability characteristics have been summarized. It is concluded that, although these methods are not always feasible for predicting absolute values of the stability of the helicopter, the effects on stability of changes in individual derivatives can generlaly be estimated satisfactorily."
Date:
November 2, 1954
Creator:
Tapscott, Robert J. & Gustafson, F. B.
System:
The UNT Digital Library
Effects of Fuselage Modifications on the Drag Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds
From Summary: "An investigation has been conducted in the Langley 8-foot transonic tunnel to determine the effects of several fuselage modifications on the transonic drag-rise characteristics of a 1/20-scale model of the Convair F-102 airplane. Tests covered an angle-of-attack range from 0 degrees to about 10 degrees and a Mach number range from 0.60 to 1.14."
Date:
November 2, 1954
Creator:
Kelly, Thomas C. & Osborne, Robert S.
System:
The UNT Digital Library