From Introduction: "A 12-percent-chord-thick wedge section and a reversed NACA 0012 section were chosen for these tests as they are representative of sections having no boat tailing and appreciable boat tailing (i.e., blunt and rounded trailing edges, respectively), and the results of this investigation are compared with those obtained from a previous investigation of the NACA 0012 section. Conclusions are drawn regarding the relative merits of the two unconventional sections and the conventional section in transonic speed range."

Report presenting foredrag measurements made at zero angle of attack for a series of fineness ratio 3 nose shapes. The types of noses investigated included theoretically derived minimum drag shapes, hemispherically blunted cones, and other more common profiles. Results regarding hemispherically blunted cones, theoretical minimum drag nose shapes, and comparison of foredrag of all the force models are provided.

Report discussing the results of an investigation to determine the stability and control characteristics of a flying model of an unswept-wing vertically rising airplane. Information about stabilization, maneuverability, rolling motions, and landings is provided.

Altitude-test-chamber investigation of effects of flame-holder blocked area and gutter width on performance of 28-inch diameter ram jet at simulated flight Mach number of 2.0 for altitudes from 40,000 to 55,000 feet was conducted at NACA Lewis laboratory. Ten flame holders investigated covered gutter widths from 1.00 to 2.50 inches and blocked areas from 40.5 to 62.0 percent of combustion-chamber area. Gutter width did not appreciably affect combustion efficiency.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the static longitudinal stability and control characteristics of a 1/16-scale model of the Douglas D-558-II research airplane. The results indicated a high degree of longitudinal stability that decreased slightly with increasing Mach number and lift coefficient.

Memorandum presenting flight tests on a swept-wing fighter airplane at a range of Mach numbers, which indicate the critical flight regions for balancing, maneuvering, and buffeting horizontal-tail loads. The critical balancing tail loads were found to occur at the highest test Mach number of about 1.03 at the highest airplane load factor. Results regarding balancing tail loads, maneuvering tail loads in elevator-pulse maneuvers, maneuvering tail loads in pitch-up maneuvers, buffet tail loads, and tail-load distributions are provided.

Report presenting pressure-distribution measurements on the fuselage of the Bell X-1 research airplane. A variety of angles of attack and Mach numbers were tested. Results regarding pressure distribution and normal load are provided.

From Summary: "Tests have been made in Langley tank no. I of a dynamic model of the Consolidated Vultee PB2Y-3 airplane. These tests were made using an alternate hull form, the purpose of which was to reduce the bow spray and eliminate the landing instability which are objectionable features of the production design. The major differences from the PB2Y-3 hull included a deeper step to improve the landing stability , and a lengthened forebody and increased beam to reduce the sway in the propellers and on the flaps. The tests showed that the spray characteristics of the revised hull form were much better than that to the production design. In addition the take-off and landing stability of the model with the alternate hull were satisfactory."