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"25" Critically Consultation with J. W. Morfitt : April 3, 1950
Summary: "Criticality was considered impossible in any contingency encountered in practice under either of the following conditions which include no safety factor: (a) In any isolated cylinder not more than 5 in. in disruptor, if the total amount of U235 present does not exceed 7.5 Eg. (b) In an isolated vessel of any shape and size, if the total amount of U235 present does not exceed 880 g. An "isolated" vessel is one which does not "see" more than 0.1 [...] other vessels containing fissionable material."
Date:
April 3, 1950
Creator:
Merrill, E. T. & Sege, G.
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.40
Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic tunnel to determine the longitudinal stability and control characteristics of a model of a supersonic airplane configuration at Mach number 1.40. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results indicated a high degree of longitudinal stability that was fairly constant throughout the trim-lift-coefficient range.
Date:
April 3, 1950
Creator:
Spearman, M. Leroy
System:
The UNT Digital Library
Wing-flow measurements of longitudinal stability and control characteristics of a supersonic airplane configuration having a 42.8 degree sweptback circular arc wing with aspect ratio 4.0, taper ratio 0.50, and sweptback tail surfaces
Report presenting the results of an investigation at transonic speeds by the wing-flow method of the longitudinal stability characteristics of a 42.8 degree sweptback supersonic airplane configuration. Lift, pitching-moment, and rolling-moment characteristics of the semispan model as well as stabilizer hinge moments and effective downwash at the tail were measured over a range of Mach numbers. The wing-flow data is compared to data for the same configuration from other research facilities.
Date:
April 3, 1950
Creator:
Crane, Harold L. & Adams, James J.
System:
The UNT Digital Library
The Use of Laboratory High Frequency Induction Furnaces
Equations are derived for the rates of heating of objects in induction furnaces and for the maximum temperatures attainable. The equations are primarily useful in designing conducting crucibles, shells, and cylinders so as to increase the power input and decrease heat losses. A very brief treatment is given of the factors which influence the current in the induction coil. The performances of various induction furnaces are compared.
Date:
April 3, 1950
Creator:
Brewer, Leo, 1919-2005
System:
The UNT Digital Library