Leaflet showing a floor plan, an illustration, and examples of drawings to be used in constructing an expansible farmhouse. Complete plans were distributed through agricultural extension services.

Provides composition tables for a variety of foods, and a table of daily dietary allowances for adults and children.

From Summary: "Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per square inch was required for marginal ice protection on the airfoil leading edge at an air temperature of 00 F and an airspeed of 300 miles per hour."

"Wind-tunnel tests were performed at Mach numbers of 1.5 and 2.0 to investigate the influence of tail surfaces on the base drag of a body of revolution without boattailing and having a turbulent boundary layer. The tail surfaces were of rectangular plan form of aspect ratio 2.33 and has symmetrical, circular-arc airfoil section. The results of the investigation showed that the addition of these tail surfaces with the trailing edges at or near the body base incurred a large increase in the base-drag coefficient. For a cruciform tail having a 10-percent-thick airfoil section, this increase was about 70 percent at a Mach number of 1.5 and 35 percent at a Mach number of 2.0" (p. 1).

Report presenting two closely related methods which employ operations tables that have been developed and used in the calculation of buckling load of a monocoque cylinder subjected to pure bending. The buckling loads of three cylinders with very different characteristics were calculated using the methods.

Report presenting charts that enable convenient determination of the pressure drop sustained by monatomic gases flowing at high subsonic speeds in a constant-area passage under the simultaneous influence of friction and heat addition. Pressure drops are determinable with good accuracy for other modes of heat addition using an effective wall temperature in conjunction with the charts. The effective wall temperature is given in terms of the passage dimensions, gas-flow conditions, and gas-temperature rise across the flow passage.

Report presenting an investigation of the spray resulting from the impingement of two jets of water in order to determine the characteristics of the instability associated with that method of spray formation. A ruffled sheet of liquid was found to form perpendicular to the plane of the two jets. The ruffling of the sheet was found to persist until the sheet disintegrated and established the frequency of wave formation.

From Summary: "Solutions of the first- and second-order Prandtl-Busemann iteration equations are obtained for the flow past thin, sharp-nose, symmetric, two-dimensional bodies in closed channels. With the use of these solutions an expression is derived from the tunnel-wall interference. The tunnel-wall correction for a parabolic-arc airfoil is calculated to indicate the effects of compressibility, ratio of the tunnel height to the airfoil chord, and airfoil thickness coefficient."

Report presenting wind-tunnel testing to investigate the effect of surface heating on boundary-layer transition on a flat plate. The identification of the onset and end of transition was made by inspection of the curves of surface-tube Mach number reading as a function of length Reynolds number obtained through the transition region.

"A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than the drag coefficient for the type of inlet with supersonic compression entirely inside, but the pressure recovery is larger for all flight conditions" (p. 1).

Report presenting an investigation of the possibility of designing a fixed total-pressure tube which will remain insensitive to inclination of the air stream over a wide range of angle of attack through subsonic and supersonic speed ranges.

Note presenting measurements of the reflection characteristics of shock waves from a flat surface with a laminar and turbulent boundary layer. The difference in the shock-wave interaction with laminar and turbulent boundary layers, first found in transonic flow, is confirmed and investigated in detail for supersonic flow.

From Summary: "On the basis of approximate expressions for the lift-curve slope and the coefficient of damping in roll of swept wings at subsonic speeds, the finite-span effects on these aerodynamic characteristics are shown to be functions primarily of a plan-form parameter, which is the aspect ratio divided by the cosine of the sweep angle and by the ratio of the section lift-curve slope to 2pi. The use of this parameter is presenting concisely and in correlating certain aerodynamic characteristics and the limitations attendant upon such use are discussed."

Note presenting numerical solutions of quantities appearing in the Karman momentum equation for the development of a turbulent boundary layer in plane and in radial compressible flows along thermally insulted surfaces in tabular form for a rnage of Mach numbers from 0.100 to 10. Through use of the tables, approximate calculation of boundary-layer growth is reduced to routine arithmetic computation.

Report presenting testing of a model with heavy beam loadings and an angle of dead rise of 0 degrees subjected to smooth-water impacts at a range of fixed trims and flight-path angles. Results regarding the time histories of horizontal and vertical displacements, vertical velocity, vertical acceleration, and pitching moment are provided.

Report presenting an investigation of the localized region of laminar separation behind the position of minimum pressure on an NACA 663-018 airfoil at zero angle of attack. A description of the behavior of the boundary layer and the resulting turbulence occurring from transition are provided.

Note presenting a discussion of various methods of reducing to stability parameter form the response to sinusoidal and transient disturbances, using the simplified longitudinal motion of an idealized airplane as an illustrative example. Most of this report is concerned with methods of determining transfer-function coefficients rather than stability derivatives. Examples are provided for a simplified case of longitudinal motion, but the methods presented are applicable to other, more complicated types of motion.

Note presenting an analysis performed to determine the effects on the rates of convective heat transfer produced by variations of the surface temperature with distance along a flat plate. The analysis is confined to the case of a low-speed turbulent boundary layer on a flat plate oriented parallel to the free-stream velocity.

Report presenting an investigation in the full-scale tunnel to determine the low-speed longitudinal, lateral, and hinge-moment control characteristics of a basic 60 degree delta wing of aspect ratio 2.31 with 10-percent-thick biconvex symmetrical airfoil sections. The wing was tested with a nose glove using NACA 65-010 section ordinates and a constant-chord plain semispan ailavator with two segments.

Report presenting a preliminary analytical evaluation of the air and fuel specific-impulse characteristics of octene-1, aluminum, and aluminum-octene-1 slurries. The adiabatic combustion flame temperature, combustion equilibrium-gas composition, air specific impulse, and fuel-weight specific impulse are presented for each fuel. Aluminum-octene-1 slurries were found to offer a means of increasing the limited air specific impulse values available with octene-1 or hydrocarbon-type fuels.

Report presenting an investigation into the effect of end plates and end-mounted struts on the lift-drag ratios of a hydrofoil at several speeds and Reynolds numbers that were all above the limiting speed of wave propagation. Information about the lift-drag ratio, effective aspect ratio, and comparison of the results versus theoretical calculations is included.

Fuels having Reid vapor pressures of 6.3 and 1.0 pounds per square inch were investigated in a tail-pipe burner on an axial-flow-type turbojet engine at a simulated flight Mach number of 0.6 and altitudes from 20,000 to 45,000 feet. With the burner configuration used in this investigation, having a mixing length of only 8 inches between the fuel manifold and the flame holder, the low-vapor-pressure fuel gave lower combustion efficiency at a given tail-pipe fuel-air ratio. Because the exhaust-nozzle area was fixed, the lower efficiency resulted in lower thrust and higher specific fuel consumption. The maximum altitude at which the burner would operate was practically unaffected by the change in fuel volatility.

Report presenting an investigation of an axial-discharge impeller in combination with a 16-vaned supersonic diffuser cascade over a range of flow conditions at equivalent tip speeds varying from 800 to 1600 feet per second. Results regarding the overall performance of the combination, starting of diffuser cascade, use of flow bleedoff to aid starting, radial distribution of flow angle, flow characteristics within diffuser, and efficiency of diffuser cascade are provided.

Report presenting the effect of Mach number on the characteristics of the downwash and wake behind an unswept, tapered wing of aspect ratio 2.67 with full-span, 25-percent-chord, leading- and trailing-edge flaps has been determined from wind-tunnel tests. Results regarding downwash characteristics and wake characteristics are provided.