For software licensing information contact: softwaresales@ama-inc.com
MISL3: Missile Aerodynamics Prediction
Fast-running, engineering-level missile aerodynamics predictions for analysis and design
MISL3 efficiently predicts longitudinal and lateral aerodynamic characteristics including damping derivatives and is essential for generating aerodynamic data bases for flight simulations.
Models axisymmetric bodies with up to three fin sections with fully deflectable fins. Bodies may have conical changes in body diameter: flares and boattails. Based on high resolution, high angle-of-attack, experimental data bases and advanced equivalent angle-of-attack concept. Detailed body and fin vortex modeling for induced nonlinear effects between fin sets.
As an option, MISL3 can be linked with the store separation program STRLNCH for detailed aerodynamic analysis of store carriage loads and trajectories.
MISL3 is available for Windows and Linux computers subject to license fees and a software license agreement. AMA recommends 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
1,2,3,4 or 8 fins/fin section
0.25 < fin aspect ration, AR < 10
0 < fin taper rations < 1
Fins with aspect ration between 1.0 and 4.0 can be deflected (control fins)
Aerodynamic Quantities Computed
Overall 6-DOF forces and moments: axial, side, and normal forces, rolling, pitching, and yawing moments
Aerodynamic Damping Coefficients due to Rotational Rates
Fin forces and moments: fin axial and normal forces, fin hinge and bending moments, body load distribution, fin load distributions, detailed axial force breakdown
Range of Flow Parameters
Subsonic, trans-sonic, supersonic Mach numbers
Angles of attack up to 90 deg
Roll angle is arbitrary
Fin deflection angles up to 40 deg
Interdigitation angles between fin sets arbitrary
Important Modeling Features
Nonlinear compressibility effects at high angles of attack
Nonlinear effects of body and fin vortices
Nonlinear fin/body gap effects
Damping effects due to rotational rates (p,q,r)
Effects of user-specified nonuniform flow
Output Options
Detailed output file
TECPLOT® compatible graphics and spreadsheet files
Spreadsheet compatible files
For software licensing information contact: softwaresales@ama-inc.com
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References
Lesieutre, D. J. and Hall, J.B. "Forebody Vortex Modeling Methods for Non-Linear Engineering-Level Missile Prediction Methods MISL3 and MISDL," AIAA 2024-443, June 2024.
Lesieutre, D. J. "Prediction of Sparrow Missile Aerodynamic Characteristics with a Non-Linear Engineering-Level Missile Prediction Method," AIAA 2017-3399, June 2017.
Lesieutre, D. J. and Quijano, O. E. "Studies of Vortex Interference Associated with Missile Configurations," AIAA-2014-0213, 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.