Preliminary Results of an Investigation at Transonic Speeds to Determine the Effects of a Heated Propulsive Jet on the Drag Characteristics of a Related Series of Afterbodies

Preliminary results are presented from an investigation to determine the influence of afterbody geometry on the effects of a sonic propulsive jet at transonic speeds. The results presented are base pressure coefficient and afterbody pressure-drag coefficient as a function of jet pressure ratio for different values of Mach number and jet temperature. Geometric parameters investigated include boattail angle, jet-to-model diameter ratio, and jet-to-base diameter ratio

NACA Research Memorandums

Report presenting an investigation in the transonic pressure tunnel to determine the afterbody pressure distribution and fin loading characteristics of two configurations of the TX-21 special weapon. The only different in the two configurations was the nose contour, with one having a hemispherical-flat shape and one with a double-radius ogive-flat shape. Results regarding the pressure port, fin loads, and force measurements are provided

NACA Research Memorandums

Report presenting an investigation to determine the aerodynamic characteristics of a wing-fuselage configuration with a wing with quarter-chord line swept back 35 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Lift, drag, and pitching-moment characteristics, downwash angles, and wake characteristics for various angles of attack and Mach numbers are provided

NACA Research Memorandums

Report discussing an investigation of two sweptback wings of different plan form in order to determine the effects of adding a triangular area to the inboard section of a conventional sweptback wing as a way to create a wing with two stages of sweepback. Lift, drag, and pitching-moment characteristics are provided for a range of Mach numbers

NACA Research Memorandums

Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers

NACA Research Memorandums

Report presenting an investigation to determine the longitudinal stability and afterbody pressure characteristics of the TX-14 and TX-16 special weapons at transonic and supersonic speeds. Results regarding dynamic testing and pressure testing are provided

NACA Research Memorandums

From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design.