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Missile Aerodynamics Prediction: MISL3

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.

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For software licensing information contact: softwaresales@ama-inc.com

Aerodynamic Database Generation

4590 Cases, Mach numbers, Angles of Attack, Fin Deflection Sets

  • Intel Core i7-6920HQ CPU @ 2.90 GHz (2016)

  • 173 secs = 0.038 sec/case

Specifications

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, 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

Examples

Sample Fin Configurations

M3_Configs.png

MISL3 Database Generation 

3FINSETgeo.gif
3FINSET.gif

Tandem Control

M = 1.75 Φ = 0°

TANDEM1.gif

Tandem Control

M = 2.50 Φ = 0°

TANDEM3.gif

Canard Pitch Control

M = 1.75 Φ = 45°

TANDEM2.gif
TANDEM_VelField.png

Pitch-Plane and Rolling Moment Characteristics

freetail1.png

Free-to-Rotate Tail Section Characteristics

FREETAIL4.gif

Velocity Fields at Tail Leading Edge

FREETAIL3.jpg

MISL3 High AR Wing - Tail Results

HIGHARgeo.gif
HIGHAR.gif

MISL3 - Additional Results

freetail1.png
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.

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