Aerodynamic characteristics of missile control fins in nonlinear flow fieldsRecent experimental results show that the control effectiveness of a missile fin in supersonic flow at moderate-to-high angles of attack is a strong nonlinear function of free-stream Mach number, body incidence angle, fin bank angle and fin deflection angle. Analysis of the experimental results using an Euler finite-difference computer code with flow separation together with the equivalent angle-of-attack concept indicates that the observed nonlinearities are due to the variation of local dynamic pressure and local Mach number around the missile body alone. The nonlinearities are shown to be a strong source of control cross-coupling for high Mach number, high angle-of-attack combinations. The analysis suggests a relatively simple yet comprehensive approach for accurately accounting for these nonlinear effects.
Document ID
19830060699
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hemsch, M. J. (Nielsen Engineering and Research, Inc. Mountain View, CA, United States)
Nielsen, J. N. (Nielsen Engineering and Research, Inc. Mountain View, CA, United States)