Report presenting an investigation of the aerodynamic characteristics of several plate- and bell-type outlets discharging air into a transonic stream. The variation in discharge coefficient of the outlets is presented as a function of the rate of discharge. The discharge coefficient, jet wake, and surface pressure distribution are also provided.

Report presenting an investigation in the transonic tunnel of the aerodynamic characteristics of a scale model of an X-1 airplane in order to correlate wing pressure-distribution results obtained in a slotted wind tunnel with flight test data on the full-scale airplane. Results regarding basic pressure measurements, and correlation of pressure measurements are provided.

Comparisons of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution with the same axial distributions of cross-sectional area normal to the air stream. An investigation was also presented of representative wing-body combinations with the body so indented that the axial distributions of cross-sectional areas for the combinations were the same as that for the original body. Results regarding unswept wing and cylindrical body, delta wing and cylindrical body, swept wing and cylindrical body, swept wing and curved body, and applications of the transonic drag-rise concept are provided.