Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on altitude operational limits are provided.

Data are presented showing compliance of C-54D with Army and Navy lateral and directional stability and control specifications. The airplane met requirements except for the rolling effectiveness pb/2V, the aileron forces in rolling, and the rudder forces in the asymmetric power conditions which were marginal. Also, the results of special tests concerning asymmetric power, asymmetric loading, and pitch due to yaw requested by the Airplane Handling Qualities Subcommittee of the Air Transport Association are presented.

Report presenting an investigation of the effect of hull length-beam ratio on the hydrodynamic characteristics of flying boats that extend to a length-beam ratio of 20. The results are compared with flying boats having a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, take-off performance, taxiing and take-off behavior in waves, landing behavior in waves, and a summary chart are provided.

Report presenting an investigation of the pressure distribution on an asymmetrical nonconical body at a Mach number of 1.90 over a wide range of angles of attack and yaw. Pressure distributions occurred at anticipated trends. Results regarding the pressure coefficients, Schileren photographs, boundary layers, and pressure distributions are provided.

Report discussing a particular wing-body combination that is part of a larger investigation to determine the lift, drag, pitching moment, and root bending moments for various configurations. Information about the aerodynamic characteristics at the tail plane is also provided.

Report presenting a wind-tunnel investigation to determine the respective variations with Mach number of the static longitudinal stability, the drag, and the effectiveness of a constant-chord control surface for a tailless fighter aircraft with a triangular wing of aspect ratio 2.31.

From Summary: "An apparatus for varying effective dihedral in flight by means of servo actuation of the ailerons in response to sideslip angle is described. The results of brief flight tests of the apparatus on a conventional fighter airplane are presented and discussed. The results of an investigation employing the apparatus to determine the tolerable (safe for normal fighter operation) range of effective dihedral on the test airplane are presented."

A spin-recovery investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 20-scale model modified to represent the McDonnell XF2H-1 airplane. The project included tests both with tip tanks installed and with the tanks removed. The results indicated that the recovery characteristics of the airplane would be satisfactory for all loadings by normal recovery technique (full reversal of the rudder, followed 1/2 turn later by movement of the elevator down). The rudder pedal and the elevator stick forces likely to be encountered in a spin should be within the capabilities of the pilot.