Prediction of Sparrow Missile Aerodynamic Characteristics with a Nonlinear Engineering Level Missile Prediction Method

An engineering-level aerodynamic prediction code was applied to the analysis of the Sparrow wingand tail-control missile configurations. The equivalent angle of attack methodology employed by the MISL3 prediction method is reviewed, and nonlinear effects of Mach number, high angles of attack, coupled fin deflections, and body-shed and fin vorticity are accounted for in the analysis and investigated. The method is used to generate an aerodynamic database over the flight Mach number range of 0.8 to 4.6, angles of attack from 0° to 48°, and fin deflection angles from -20° to +20°. These results are compared to the published database. The prediction method is compared to experimental data for several interesting nonlinear cases. The loss of roll control authority with combined pitch and roll deflections is investigated for the wing-control Sparrow at transonic speeds.

[1]  Jerry M. Allen,et al.  Analysis of selected data from the triservice missile data base , 1989 .

[2]  Stanley C. Perkins,et al.  ENGINEERING, INTERMEDIATE, AND HIGH LEVEL AERODYNAMIC PREDICTION METHODS AND APPLICATIONS , 1999 .

[3]  John F. Love,et al.  Recent Applications and Improvements to the Engineering-Level Aerodynamic Prediction Software MISL3 , 2002 .

[4]  D. Lesieutre,et al.  AIAA 2002-4511 Prediction of the Nonlinear Aerodynamic Characteristics of Tandem-control and Rolling-tail Missiles , 2002 .

[5]  M. J. Hemsch,et al.  Equivalent angle-of-attack method for estimating nonlinear aerodynamics of missile fins , 1983 .

[6]  Charles A. Smith,et al.  A Preliminary Method for Calculating the Aerodynamic Characteristics of Cruciform Missiles to High Angles of Attack Including Effects of Roll Angle and Control Deflections , 1977 .

[7]  Daniel J. Lesieutre,et al.  Studies of Vortex Interference Associated with Missile Configurations , 2014 .

[9]  Daniel J. Lesieutre,et al.  High angle of attack missile aerodynamics including rotational rates - Program M3HAX , 1996 .

[10]  W. J. Monta.  Supersonic aerodynamic characteristics of a Sparrow 3 type missile model with wing controls and comparison with existing tail-control results , 1977 .

[11]  Melissa A. McDaniel,et al.  The Effect of Tail Fin Parameters on the Induced Roll of a Canard-Controlled Missile , 2010 .

[12]  M. J. Hemsch,et al.  Extension of equivalent angle-of-attack method for nonlinear flowfields , 1985 .