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The aerodynamic loading on a number of rocket body-control surface combinations has been calculated using methods developed at the University of Tennessee Space Institute over the past five years. Variations in control surface planform, roll angle, control surface deflection or incorporation of elevons, are included. Compressibility is accounted for. Details of the digital computer program are included.
This report documents some techniques used in deriving the equations of motion of a missile for a six-degree-of-freedom (6-DOF) simulation. Several forms of the equations are developed, and their implementation is discussed. Specific emphasis is placed on showing the interrelation of the equation forms currently in use by showing their development from the basic laws. This report is meant to serve as a primer for new engineers and as a reference for all engineers involved in missile flight simulation.
A cooperative experimental investigation has been performed to obtain a systematic fin-body and fin-plate database for series of 12 missile fins. These data are intended to complement and extend the information contained in the Triservice missile project and to provide a systematic set of experimental data from which fin-body interference factors can be derived. Data were obtained with the fins mounted on both an axisymmetric body and on a flat plate that was used to simulate fin-alone measurements. The experiments were conducted at Mach numbers from 0.60 to 3.95; fin deflection angles of 0°, 10° , and -10° ; and angles of attack up to 30° on the body and up to 95° on the flat plate. The data were obtained from three-component balances attached to the fins and a six-component balance located in the axisymmetric body. The data obtained in this project are documented in tabular form in this report. In addition, selected data are presented in graphical form to illustrate the effects of the test variables.
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.