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Missile Aerodynamics Prediction: MISL3



Click for 3 fin set MISL3 Missile Aerodynamics Prediction Software
  • High Angle of Attack
  • Angular Rates
  • Nonuniform Flow Fields
  • Body Flares and Boattails
  • Arbitrary Interdigitation between Fin Sets

  • 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 diameterr: 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 NEAR 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. 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.

    MISL3 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
  • 330 CPU seconds, 0.1375 seconds/case


  • Applicable Configurations
    Up to 3 fin sections
    1,2,3,4 or 8 fins per fin section
    0.25 < fin aspect ratio, AR < 10
    0 < fin taper ratio < 1
    Fins with aspect ratio 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, transonic, 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


    Examples of applicable configurations


    Click on images to view example results

    Click for Additional Results
    References below contain additional results

    References
    1. Lesieutre, D. J. "Prediction of Sparrow Missile Aerodynamic Characteristics with a Non-Linear Engineering-Level Missile Prediction Method," AIAA 2017-3399, June 2017.
    2. Lesieutre, D. J. and Quijano, O. E. "Studies of Vortex Interference Associated with Missile Configurations," AIAA-2014-0213, 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., Love, J. F., and Dillenius, M. F. E., "Recent Applications and Improvements to the Engineering-Level Aerodynamic Prediction Software MISL3," AIAA 2002-0275, Jan. 2002.
    6. 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.
    7. 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.
    8. Lesieutre, D. J., Love, J. F., and Dillenius, M. F. E., "High Angle-of-Attack Missile Aerodynamics Including Rotational Rates - Program M3HAX," AIAA 1996-3392, Jul. 1996.
    9. Dillenius, M. F. E., Lesieutre, D. J., Whittaker, C. H., and Lesieutre, T. O., "New Application of Engineering Level Missile Aerodynamics and Store Separation Prediction Methods," AIAA 94-0028, Jan. 1994.
    10. Lesieutre, D. J., Mendenhall, M. R., and Dillenius, M. F. E., "Prediction of Induced Roll on Conventional Missiles with Cruciform Fin Sections," AIAA 1988-0529, Jan. 1988.
    11. Lesieutre, D. J., Mendenhall, M. R., Hemsch, M. F., and Nazario, S. M., "Aerodynamic Characteristics of Cruciform Missiles at High Angles of Attack," AIAA 87-0212, Jan. 1987.


    12. 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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