Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.

Report presenting an investigation of the performance of a pair of tubular turbojet combustors interconnected by a 3-inch-inside-diameter ceramic-lined pilot chamber to determine the utility of the pilot chamber for improvement of high-altitude combustion efficiency, lean limits, and minimum engine speed. Results regarding the combustion efficiency and lean-limit blow-out, ignition limits, and altitude operating limits are provided.

Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.

Report presenting an investigation of the transonic flutter characteristics at zero lift of a model of a wing for a new fighter airplane. The characteristics were found to be similar to those of a comparable systematic plan-form series of models described in previous reports. Results regarding visual observations, damping, flutter-speed ratio, and ratio of experimental sustained flutter speeds to reference flutter speeds are provided.

Report presenting a brief study utilizing pilots to fly a simulator of some longitudinal stability and control problems of an assumed aircraft capable of flights to altitudes essentially out of the atmosphere. The results show that more than the inherent longitudinal damping of the aircraft is necessary to affect a safe flight, particularly during entry into the atmosphere. Results regarding some preliminary considerations, entry, and control in ascent and the ballistics trajectory are provided.

Memorandum presenting a single J33 combustor and an experimental tubular combustor incorporating a fuel vaporizer as operated with gaseous hydrogen at temperatures slightly above the boiling point of the fuel. Data were obtained to explore possible effects of the fuel temperature on combustor performance and on the control and measurement of fuel flow.

The performance and operational characteristics of the J71-A2 turbojet-engine afterburner were investigated for a range of altitudes from 23,000 to 60,000 feet at a flight Mach number of 0,9 and at flight Mach numbers of 0.6, 0.9, and 1.0 at an altitude of 45,000 feet. The combustion performance and altitude operational limits, as well as the altitude starting characteristics have been determined.