"In naval architecture, it is customary to determine the wetted surface of a ship by means of some formula which involves the principal dimensions of the design and suitable constants. These formulas of naval architecture may be extended and applied to the calculation of the surface area of airship envelopes by the use of new values of the constants determined for this purpose. Surface area coefficients were calculated from the actual dimensions, surfaces, and volumes of 52 streamline bodies, which form a series covering the entire range of shapes used in the present aeronautical practice" (p. 1).

"The various speeds of an airplane can only be measured in horizontal flight, since there are no means for measuring the angle of ascent or descent. The measurements must be corrected for the density of the air. This is obtained by simultaneous pressure and temperature measurements during flight" (p. 1).

This paper constitutes a general theoretical discussion of the damping factor in roll, together with the results of wind tunnel tests on the continuous rolling of U.S.A. 30 airfoil.

Report presenting testing of rectangular Clark-Y biplane cellules with zero and -0.25 stagger, the gap equal to the chord, and 0 degrees decalage were tested on the NACA spinning balance in the 5-foot vertical tunnel.

Three rectangular monoplane wings having rounded tips were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The airfoil sections used were the N.A.C.A. 0009, 23018, and 6718. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. There is included an estimate of the yawing moment that must be furnished by parts of the airplane to balance the inertia couples and wing yawing moments for spinning equilibrium. The predicted angles of sideslip and yawing moments required for spinning equilibrium for a Clark Y wing with the same form are included for comparison.

Note presenting a consideration of dynamic maneuvers consisting of periodic rudder and aileron control deflections with respect to the maximum sideslip angles developed and the position of the rudder at the time of maximum sideslip. A method is also given for computing the maximum sideslip angles when the forces and moments are nonlinear functions of the sideslip.

Report presenting an extension of a finite-difference method to include the computation of disk stresses when plastic flow and creep are considered. The results of numerical examples indicate qualitatively that plastic flow markedly alters the elastic-stress distribution and that, if the amount of creep is small, the effect on stress distribution is also small.

Report presenting a partly linearized solution of plastic deformation of a rotating disk based on the deformation theory of plasticity and considering finite strains. The method can be used to investigate the general plastic behavior of a rotating disk.

Note presenting an investigation carried out to study the elastic behavior after buckling of a rectangular plate reinforced with longitudinal stiffeners and subjected to compressive loads in a direction parallel to the stiffeners. Two possible buckling modes were investigated.

Report presenting an investigation of steady flow about curved airfoils at high supersonic speeds. Testing demonstrated that within the limitation of the assumption of ideal gas flow, the shock-expansion method may be used with good accuracy to predict pressure distributions on curved airfoils at arbitrarily high Mach numbers.

Report presenting an investigation of nickel-aluminum alloys which were from 14 to 34 percent aluminum by weight as part of a study of the properties of intermetallics. Results regarding the quality of castings, physical evaluation of cast alloys, hot formability of alloys, physical properties of 17.5-percent-aluminum alloy, microstructure of 17.5-percent-aluminum alloy, the casting method, and other properties of the intermetallics are provided.

Report presenting the results of an analytical and experimental investigation of the steady-state and dynamic characteristics of three types of throttle-controlled fuel systems. The three systems tested are a throttle with regulated upstream pressure, a throttle plus bypass differential-pressure regulator, and a throttle plus reducing-valve differential-pressure regulator with regulated supply pressure. Results regarding the effect of output pressure on the controlled flow, response of output flow to step changes in throttle area, and response of output flow to a sinusoidal variation in throttle area are provided.

Note presenting information on the average pressure indicated by a total-pressure probe subjected to a stagnation pressure that alternates periodically between two constant values. Calculated and experimental data are in good agreement and errors are reduced when the probe design is such as to ensure laminar-flow pulsations in the probe at all times.

Structural efficiency curves are presented for high-strength, stainless-steel, cellular-core sandwich plates of various proportions subjected to compressive end loads for temperatures of 80 F and 600 F. Optimum proportions of sandwich plates for any value of the compressive loading intensity can be determined from the curves. The efficiency of steel sandwich plates of optimum proportions is compared with the efficiency of solid plates of high-strength steel and aluminum and titanium alloys at the two temperatures.

Report presenting six-percent-thick NACA 63-series compressor-blade sections with a loaded-leading-edge mean line investigated systematically in a two-dimensional porous-wall cascade over a range of Reynolds numbers. Blades cambered to have four different isolated-airfoil lift coefficients were tested over the usable angle-of-attack range at four different inlet-air angles and two different solidities.

"The amount of water in cloud droplet form ingested by a full-scale supersonic nose inlet with conical centerbody was measured in the NACA Lewis icing tunnel. Local and total water impingement rates on the cowl and centerbody surfaces were also obtained. All measurements were made with a dye-tracer technique" (p. 1).