Memorandum presenting a method for varying the mass flow of supersonic inlets with a circular cross section and a central body. The method consists of changing the size of the entering stream tube by means of an inflatable boot on the surface of the central body.

Report presenting results during demonstration flight tests of the Northrop X-4 No. 1 and No. 2 airplanes. Results regarding the static and dynamic longitudinal- and lateral-stability characteristics, the stalling characteristics, and the buffet boundary.

Report presenting aerodynamic characteristics of an unswept wing with an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent chord, plain, trailing-edge flaps using wind-tunnel testing of a semispan model. The trailing-edge flap was generally effective in changing the lift coefficient at each angle of attack and Mach number of the investigation. Results regarding lift characteristics, hinge-moment characteristics, drag characteristics, and pitching-moment characteristics are provided.

"Surface temperatures and heat transfer to the air stream have been measured for turbulent flow over a flat plate at a Mach number of 1.5 and at a Reynolds number, based on the momentum thickness of the boundary layer, of approximately 5000. Preliminary data are presented and the surface heat-transfer coefficients calculated from these data are considered to be accurate to plus or minus 2.6 percent at a temperature potential of 50 degrees Fahrenheit. These data are in good agreement with the results produced by applying modifications obtained from published information to existing subsonic theories" (p. 1).

Report presenting tests of NACA 65-series compressor blades cambered to an isolated airfoil lift coefficient of 1.2 at several maximum section thicknesses to obtain the effect of maximum section thickness on section operating characteristics. Information about surface pressure trends, design angle-of-attack selection, drag, operating range, and critical Mach number is also provided. Changing the section thickness was not found to significantly affect the design angle of attack selected.

From Summary: "Thrust augmentation of an axial-flow type turbojet engine by burning fuel in the tail pipe has been investigated in the NACA Cleveland altitude wind tunnel. The performance was determined over a range of simulated flight conditions and tail-pipe fuel flows. The engine tail pipe was modified for the investigation to reduce the gas velocity at the inlet of the tail-pipe combustion chamber and to provide an adequate seat for the flame; four such modifications were investigated."

Report presenting tests of four 7.5 degree boattail bodies of revolution with secondary air scoops in free flight to find the change in drag coefficient when a simulated turbojet exhaust issued from conical short-length ejectors. Results indicated that the jet-on total drag coefficients were lower throughout the test Mach number range than corresponding jet-off values of the forebody drag coefficient. Results regarding drag and ejector-shroud characteristics are provided.

Memorandum presenting a limited investigation in the supersonic pressure tunnel to determine the effectiveness of differential horizontal-tail deflection for producing lateral control for two swept-wing airplane models in the Mach number range from 1.4 to 2.0. The tests were limited to small tail deflections but included combined angles of attack and sideslip up to about 20 degrees. The tests showed the rolling-moment effectiveness to be essentially constant with sideslip angle but to decrease with increasing angle of attack.

Report presenting an analysis of the longitudinal stability characteristics of the cambered-wing version of the Convair YF-102 airplane at a range of Mach numbers and altitudes. Results regarding longitudinal trim, stall maneuvers, dynamic longitudinal stability, maneuvering stability, stability and control effectiveness parameters, and artificial-feel system are provided.

Report presenting some exploratory materials and nose-shape tests in a small supersonic air jet with a stagnation temperature of approximately 4000 degrees Fahrenheit. Materials considered included graphite, copper, carbon steel, and stainless steel, and the nose shapes included 90 degree total-angle cones, hemispherical-face cylinders, and flat-face cylinders. The aerodynamic heat transfer to flat-face cylinders is appreciably less than to hemispherical-face cylinders.

"This report presents a discussion of longitudinal stability in gliding flight together with a series of charts with which the stability characteristics of any airplane may be readily estimated. The relationships governing stability characteristics are derived from equations of equilibrium referred to moving axes that are tangent and perpendicular to the instantaneous flight path. It is shown that instability of the motion can arise only through an increase of linear and angular momentum in the system during one complete cycle" (p. 289).

"Test data and analysis show that the rate of fuel leakage between a lapped plunger and sleeve varies directly with the density of the fuel, the diameter of the plunger, the pressure producing the leakage, and the cube of the mean clearance between the plunger and sleeve. The rate varies inversely as the length of the lapped fit and the viscosity of the fuel. With a mean clearance between the plunger and sleeve of 0.0001 inch the leakage amounts to approximately 0.2 percent of the fuel injected with gasoline and as low as 0.01 percent with diesel fuel oils" (p. 63).

"This report presents the results of wind tunnel tests on a Mcdonnell Douglas airplane to determine the wing-fuselage interference of a low-wing monoplane. The tests included a study of tail buffeting and the air flow in the region of the tail. The airplane was tested with and without the propeller slipstream, both in the original condition and with several devices designed to reduce or eliminate tail buffeting. The devices used were wing-fuselage fillets, a NACA cowling, reflexed trailing edge of the wing, and stub auxiliary airfoils" (p. 143).

"A summary of methods for making dynamic lateral stability and response calculations and for estimating the aerodynamic stability derivatives required for use in these calculations is presented. The processes of performing calculations of the time histories of lateral motions, of the period and damping of these motions, and of the lateral stability boundaries are presented as a series of simple straightforward steps. Existing methods for estimating the stability derivatives are summarized and, in some cases, simple new empirical formulas are presented. Detailed estimation methods are presented for low-subsonic-speed conditions but only a brief discussion and a list of references are given for transonic and supersonic speed conditions" (p. 1).

"Results are presented for a wind-tunnel investigation of an airplane model with a 3.4-percent-thick unswept wing of aspect ratio 2.45 at Mach numbers from 0.8 to 1.4 at a Reynolds number of 1.5 million. Longitudinal characteristics are presented for the basic model and for configuration variations involving two types of wing camber, an area-rule fuselage modification, various external-store arrangements, several conventional missile installations and one designed according to the moment-of-area concept, and two fuselage dive-flap arrangements. Lateral-directional characteristics of the basic model with and without the empennage are also included" (p. 1).