A Flight Investigation at Transonic Speeds of a Model Having a Triangular Wing of Aspect Ratio 3

Report presenting free-falling recoverable-model tests at transonic speeds on a model with a triangular wing of aspect ratio 3 and a 45 degree swept tail located in the chord plane of the wing. Static and dynamic longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at a range of angles of attack. results regarding lift, drag, static longitudinal stability, dynamic longitudinal stability, horizontal-tail effectiveness, loading distributions over fuselage, and buffet boundary are provided.