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Detailed Missile Loads: MISDL

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 NEAR 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. Delivery to foreign contries requires U.S. State Department export license. NEAR recommends a two-day training course which includes interpretation of the output and "hands-on" code running.

MISDL Database Generation Example
Canard-Tail Missile with body and fin vortex shedding and wake tracking
  • 2400 flow conditions, M, αc, φ, and δ
  • Intel Core2 2.33 GHz processor
  • 64 CPU minutes, 1.60 seconds/case

  • Applicable Configurations
    Up To 3 Fin Sections
    Up to 8 fins per 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

    1. Lesieutre, D. J. and Quijano, O. E. "Studies of Vortex Interference Associated with Missile Configurations," AIAA-2014-0213, Jan. 2014.
    2. Lesieutre, D. J. "Nonlinear Aerodynamic Predictions of Aircraft and Missiles Employing Trailing-Edge Flaps," AIAA-2014-0055, Jan. 2014.
    3. 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.
    4. 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.
    5. Lesieutre, D. J., Dillenius, M. F. E., and Gjestvang, J., "Store Separation Simulation of Penguin Missile from Helicopters," AIAA 2002-0278, Jan. 2002.
    6. Lesieutre, D. J., Dillenius, M. F. E., and Gjestvang, J., "Application of MISDL/KDA Aerodynamics Prediction Method to Penguin Missile," AIAA 2002-0277, Jan. 2002.
    7. Dillenius, M. F. E., Lesieutre, D. J., Hegedus, M. C., Perkins, S. C., Jr., Love, J. F., and Lesieutre, T. O., "Engineering-, Intermediate-, and High-Level Aerodynamic Prediction Methods and Applications," Journal of Spacecraft and Rockets, Vol. 36, No. 5, Sep.-Oct. 1999, pp. 609-620.
    8. Lesieutre, D. J., Dillenius, M. F. E., and Lesieutre, T. O., "Missile Fin Planform Optimization for Improved Performance," RTO-MP-5, Missile Aerodynamics, Nov. 1998.
    9. Dillenius, M. F. E., Lesieutre, D. J., Perkins, S. C., Jr., and Love, J. F., "Prediction of Nonlinear Missile Aerodynamics with Applications Including Store Separation," RTO-MP-5, Missile Aerodynamics, Nov. 1998.
    10. Lesieutre, D. J., Dillenius, M. F. E., and Lesieutre, T. O., "Multidisciplinary Design Optimization of Missile Configurations and Fin Planforms for Improved Performance," 7th Symposium on Multidisciplinary Analysis and Optimization, St. Louis, MO, AIAA-1998-4890, Sep. 1998.
    11. Lesieutre, D. J., Dillenius, M. F. E., Love, J. F., and Perkins, S. C., Jr., "Control of Hinge Moment by Tailoring Fin Structure and Planform," NEAR TR 530, Nielsen Engineering & Research, Mountain View, CA, Dec. 1997.
    12. Lesieutre, D. J., Lesieutre, T. O., and Dillenius, M. F. E., "Optimal Aerodynamic Design of Advanced Missile Configurations with Geometric and Structural Constraints," NEAR TR 520, Nielsen Engineering & Research, Mountain View, CA, Apr. 1997.
    13. Lesieutre, D. J., Lesieutre, T. O., and Dillenius, M. F. E., "Planform/Configuration Optimization Program OPTMIS for Arbitrary Cross Section Configurations With Up To Two Fin Sets - Software User's Manual and Software Programmer's Manual," NEAR TR 519, Nielsen Engineering & Research, Mountain View, CA, Apr. 1997.

    Aero Software Licensing and Training

    Missile Aerodynamics Prediction:  MISL3
    Detailed Missile Loads:  MISDL
    Euler Solver: NEARZEUSIN (with Inlets) /ZEUSBL
    Aircraft Store Separation and Carriage Loads Analysis: STRLNCH
    Aircraft Unsteady Maneuvering: SHAMAN
    Unsteady Hydrodynamic Analysis: SUBFLO_2
    User’s Training for all NEAR Software
    State Department Export License and TAA Preparation as Required


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