For software licensing information contact: softwaresales@ama-inc.com
MISDL: Detailed Missile Loads
Fast-running program MISDL employs elements of classical aerodynamic theory, including vortical theory
The software package predicts overall aerodynamic performance coefficients and detailed aerodynamic loading distributions on the body and lifting surfaces of flight vehicles, including: missiles, munitions, mortars, aircraft, UAVs, etc.
MISDL can model configurations with circular and noncircular bodies, including those with chines. The finned sections can have planar, triform, cruciform, and low profile fin layouts. Fin planform can be arbitrary. Effects of rotational rates (damping) and of nonuniform flow are included. The overall and detailed aerodynamics predicted by these programs are useful to aerodynamic, structural, and control system engineers.
As an option, MISDL can be linked with the store separation program STRLNCH for detailed aerodynamic analysis of store carriage loads and trajectories.
MISDL is available for Windows and Linux computers subject to license fees and a software license agreement. We recommend a two-day training course which includes interpretation of the output and "hands-on" code running. Delivery to foreign countries requires U.S. State Department export license.
Capabilities
Applicable Configurations
Up To 3 Fin Sections
Up to 8 fins/fin section
Arbitrary fin planform shape
Arbitrary attachment and dihedral angles
Folded and wrap-around fins
Aerodynamic Quantities Computed
Overall 6-DOF forces and moments: axial, side, and normal forces, rolling, pitching, and yawing moments
Fin forces and moments: fin axial and normal forces, fin hinge and bending moments
Body pressure distribution
Fin load distributions
Detailed axial force breakdown
Range of Flow Parameters
Subsonic - supersonic Mach number (fin loads valid to Mach 6.0)
Angles of attack up to 30 deg
Roll angle arbitrary
Fin control deflection angles to 20 deg
Important Modeling Features
Nonlinear effects of body and fin vortices
Damping effects due to rotational rates (p,q,r)
Effects of user-specified nonuniform flow
Output Options
Detailed output file
TECPLOT ® compatible files
Spreadsheet compatible files
For software licensing information contact: softwaresales@ama-inc.com
References
Lesieutre, D. J. and Quijano, O. E. "Studies of Vortex Interference Associated with Missile Configurations," AIAA-2014-0213, Jan. 2014.
Lesieutre, D. J. "Nonlinear Aerodynamic Predictions of Aircraft and Missiles Employing Trailing-Edge Flaps," AIAA-2014-0055, Jan. 2014.
McDaniel, M. A., Evans, C. and Lesieutre, D. J., "The Effect of Tail Fin Parameters on the Induced Roll of a Canard-Controlled Missile," AIAA 2010-4226, Jun. 2010.
Lesieutre, D. J., Love, J. F., and Dillenius, M. F. E., "Prediction of the Nonlinear Aerodynamic Characteristics of Tandem-Control and Rolling-Tail Missiles," AIAA-2002-4511, Aug. 2002.