"A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).

"Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in level flight at Mach numbers from 0.79 to 1.00 and in a pull-up to an airplane normal-force coefficient of 0.91 at a Mach number of approximately 0.96" (p. 1).

Report presenting testing of the zero-lift drag of two wings, one with 45 degree sweepforward of the inboard panel and 45 degree sweepback of the outboard panel ("M" wing) and the other with a reverse sweep ("W" wing) at a range of Mach numbers. Both wings were found to have greater drag than a sweptback wing and less drag than a rectangular wing at transonic speeds. The differences were reduced at Mach numbers above 1.25.

Report presenting an investigation in the high speed 7- by 10-foot tunnel to determine the effects of a spanwise variation in thickness ratio on the aerodynamic characteristics of a wing with a plan form identical to that of a constant-percent thickness-ratio wing program. The wing with thickness variation had 35 degrees of sweepback, aspect ratio 4, and taper ratio of 0.60 with airfoil section tapered from an NACA 65A006 section at the root chord to an NACA 65A002 section at the tip chord. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.

Report presenting a method based on geometric factors of the coolant passage was evolved for the rapid selection and evaluation of coolant passage configurations for air-cooled turbine rotor blades. The most promising coolant passage configurations are analyzed to obtain absolute values of the required cooling-air weight flow, pressure loss, and strength characteristics.

Report presenting the longitudinal frequency-response characteristics and the stability derivatives of the Douglas D-558-II airplane at a range of Mach numbers and altitudes. Results of experimentation were compared to computed values.

Memorandum presenting a preliminary investigation of flame-stability and flame-extinction characteristics of a propane-air mixture in an annular combustion chamber conducted with both straight and rotational flow. The rotating mixture burned at higher axial-inlet stream velocities and with more stable flames than could be obtained with straight-flow burning.

Report presenting a series of survey tests of a transonic axial-flow compressor inlet stage to permit a detailed analysis of the flow across individual blade rows.