Report presenting an investigation in the transonic pressure tunnel to determine the afterbody pressure distribution and fin loading characteristics of two configurations of the TX-21 special weapon. The only different in the two configurations was the nose contour, with one having a hemispherical-flat shape and one with a double-radius ogive-flat shape. Results regarding the pressure port, fin loads, and force measurements are provided.

Report discussing an evaluation of a series of half-conical side inlets mounted on the fuselage of a supersonic aircraft at various Mach numbers. Information about the maximum total-pressure recovery, asymmetrical operation of the twin-duct system, potential reduction in stable mass-flow range, boundary-layer diverter height, and engine mass flow is described.

Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.

Report presenting an investigation of the aerodynamic characteristics of a swept-wing supersonic bomber configuration conducted in the 8-foot transonic tunnel. The wing had an aspect ratio of 3.5, taper ratio of 0.2, 47 degrees of sweepback of the 0.25-chord line, and airfoil sections which were 5.5 percent thick parallel to the plane of symmetry. Results regarding the longitudinal force characteristics, effects of wing incidence, a modified wing, various auxiliary wing devices, and horizontal-tail height are provided.

Report presenting an investigation of a swept-wing supersonic bomber configuration in the 4- by 4-foot supersonic pressure tunnel. Testing occurred at Mach numbers of 1.41 and 2.01 and a designated Reynolds number based on the wing mean aerodynamic chord. The model had a tapered wing with an aspect ratio of 3.5, a taper ratio of 0.2, a thickness ratio of 5.5 percent and 47 degrees sweep of the quarter-chord line. The investigation included the longitudinal and lateral force characteristics and various combinations of its components, including several jet nacelle installations.

Report presenting an investigation made to determine experimentally the effects of two types of trailing-edge controls on the aerodynamic characteristics of a wing-body combination consisting of a 4-percent-thick wing of rectangular plan form and a slender body of revolution. The variations of lift coefficient with angle of attack of the flap-wing-body combination and spoiler-wing-body combination were generally nonlinear. Results regarding the trailing-edge flap control and trailing-edge spoiler controls are provided.

Report presenting an investigation of the static longitudinal-stability characteristics of a 45 degree sweptback wing-fuselage configuration with and without a sweptback horizontal tail for a range of angles of attack and Mach numbers. Special focus is given to the pitching-moment characteristics, location of the aerodynamic center, and slope of the lift-coefficient curve.

Report presenting an investigation in the transonic blowdown tunnel to determine the effects of variations in inlet lip swagger from 0 to 60 degrees on the internal-flow characteristics of an unswept semielliptical scoop-type air-inlet model without boundary-layer control. Tests were made for a range of Mach numbers and mass-flow ratios. Results regarding the flow over the fuselage nose, total-pressure recovery at inlet, flow distortions at inlet, and inlet-design considerations are presented.

"Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss" (p. 1).

Memorandum presenting tests at two supersonic speeds to obtain experimentally the aerodynamic damping characteristics of a control surface on a two-dimensional wing. The control surface had a chord of 1.67 inches and a span of 7.25 inches and was supplied in three materials with different mass, inertia, and stiffness properties. Results regarding the presentation of data and comparison with theory and comparison with control-surface data for a triangular wing are provided.

Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.

Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.