Nonaxisymmetric Body, Supersonic, Inviscid Dynamic Derivative Prediction
Abstract
A supersonic, aerodynamic computational model, which is the basis of the NANC code, has been extended to compute dynamic derivatives. The extension is to the inviscid contribution of constant angular rates and axial accelerations. The body geometry limitations are the same as for the steady- state model. Here, a pointed body or equivalent pointed body is assumed for low Mach numbers; at higher Mach numbers, the effect of axial acceleration is neglected and the body may be blunt. The body may be noncircular with planar discontinuities, including inlets, with fins (up to six per fin set), which lie on a cylindrical coordinate ray. For the low Mach number range, the original second-order potential model has been extended for angular rate derivative prediction. For the acceleration rate derivatives, a 'hybrid' first- and second- order model has been developed. For the high Mach number range, an equivalent angle-of-attack vector is defined and combined with local solution models. Computational comparisons are made with experimental data, primarily for pitch and roll damping derivatives. Keywords: Aerodynamic loading; Supersonic characteristics; Mathematical prediction; Projectile models; Dynamic derivatives; Supersonic/aerodynamic computational model; First and second order model; Roll/pitch damping; Fin magnus.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1989
- Accession Number
- ADA220839
Entities
People
- Leroy Devan
Organizations
- Naval Surface Warfare Center