Report discussing an investigation of the McDonnell XF3H-1 with models to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Information about the flutter, static longitudinal stability, dynamic longitudinal stability, static directional stability, trim, drag, and effect of rocket racks on aerodynamic characteristics of the model is provided.

Report presenting a wind-tunnel investigation on a 42 degree sweptback-wing model to determine the lateral control characteristics of a plug-aileron configuration. The configuration consisted of six segments extending from the wing 20-percent-span to the wing 80-percent-span stations and with the center of each plug on the wing 70-percent-chord line. Results regarding wing aerodynamic characteristics and lateral control characteristics are provided.

Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.

Report presenting an investigation to determine the predictability of using ceramals with comparatively low strategic material content for the blades of aircraft turbines, including testing with four different blade root configurations. The most favorable results were obtained for ceramal turbine blades with single serration interlock and dovetail root configurations. Results are also provided for fir-tree blade runs and 4-pin blade runs.

Memorandum presenting an investigation of the phenomenon of the starting of aerodynamic instability or buzz in supersonic inlets with external compression. The starting of the buzz has been related to the existence in the flow field of a velocity discontinuity across a vortex sheet which originates at a shock intersection. Results regarding the inlets without separation on the central body, inlets with separation on the central body, the regulation of entering volume flow at angles of attack, experimental performance of various inlets, and an application of the results are provided.

"Due to the scattered nature of existing information on the losses involved in the internal flow of gases through axial compressors and turbines, a brief survey of the available information on such losses is made. The present state of knowledge and the direction of future research toward the reduction of these losses are indicated" (p. 1).

Report presenting a review of the literature pertaining to the use of orthotoluidine and triethylamine in rocket propellant combinations and a summary with particular emphasis on ignition delay investigations and fuel mixture applications. The survey indicated that orthotoluidine is about as good a rocket fuel as aniline with respect to cost, performance, and ignition characteristics, but it has a wider temperature application because of its lower freezing point.

Report presenting a flight investigation using two rocket-boosted scale models of the McDonnell XF3H-1 airplane to determine the aerodynamic effects of operating internally stowed extensible rocket racks during transonic flight. Operation of the racks generally had only a small effect on the aerodynamic characteristics with the exception of drag.

Report presenting a brief investigation conducted to determine the effects of a 60-40 air flow distribution to the twin inlet ducts of an axial-flow turbojet engine. Data were obtained over a range of exhaust gas temperatures at several altitudes at Mach number 0.64. Results regarding the effect on pressure and temperature patterns, compressor performance, effect on combustor and turbine performance, engine pumping characteristics, and operational characteristics are provided.