"Tabulated pressure coefficients and aerodynamic characteristics are presented unanalyzed for six spanwise stations on the right wing of the Douglas D-558-I research airplane (BuAero No. 37972). The data were obtained in a 1 g stall at subcritical Mach numbers, in a speed run to a Mach number of 0.90 and in a wind-up turn at a Mach number of 0.86" (p. 1).

Report presenting an investigation to determine the spin, recovery, and longitudinal-trim characteristics of a 60 degree delta-wing model through an extensive range of mass loadings. Variations in the relative density, center-of-gravity position, and inertia parameters were included in testing. Results regarding the single-vertical-tail and multiple-vertical-tail configurations are provided.

Report presenting an investigation in the high speed tunnel to determine the effects of several wing-mounted external-store configurations on the aerodynamic characteristics of a model of a swept wing-fuselage combination for a range of Mach numbers. Some of the configurations explored included inboard underwing installations and wing-tip installations. Results regarding lift-drag ratios, drag characteristics, lift-curve slope, and pitching-moment characteristics are provided.

From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."

Report discussing tests of an unshrouded axial-flow supersonic compressor rotor. Information about the pressure ratio, efficiency, and flow rate with and without inlet guide vanes is provided. The results are also compared to testing on the original shrouded rotor.

Report presenting an investigation to determine the aerodynamic characteristics of a wing-fuselage configuration with a wing with quarter-chord line swept back 35 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Lift, drag, and pitching-moment characteristics, downwash angles, and wake characteristics for various angles of attack and Mach numbers are provided.

Report presenting the results of static tests conducted for the purpose of determining the lift forces and hinge moments associated with a flat-plate paddle vane, externally hinged near a rocket-nozzle exit and operating on the jet for vane deflection angles ranging from -4 degrees to 25 degrees. Results regarding vane aerodynamic characteristics, performance of rocket motor, and vane erosion

An experimental investigation was made at Mach number 1.90 of the performance of a series of perforated convergent-divergent supersonic diffusers operating with initial boundary layer, which was induced and controlled by lengths of cylindrical inlets affixed to the diffusers. Supercritical mass-flow and peak total-pressure recoveries were decreased slightly by use of the longest inlets (4 inlet diameters in length). Combinations of cylindrical inlets, perforated diffusers, and subsonic diffuser were evaluated as simulated wind tunnels having second throats. Comparisons with noncontracted configurations of similar scale indicated conservatively computed power reductions of 25 percent.

Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.

Memorandum presenting wind tunnel tests to determine the aerodynamic characteristics of a semispan wing with a modified NACA 0012-64 section and a 26.6-percent-chord, plain, trailing-edge aileron. Results are shown for the wing with the 0.229-chord line unswept and swept back 45 degrees and for a Mach number range from 0.40 to 0.925.

From Summary: "A flight investigation was made of a supersonic twin-ram-jet test vehicle using short-flame-length burners. The test demonstrated a maximum acceleration of 3.6g and a maximum flight Mach number of 3.02. Data were obtained over a Mach number range from about 1.9 to 3.0, an altitude range from 1,800 to 40,900 feet, and a fuel-air-ratio range from 0.012 to 0.065."