Numerical Simulation of Steady Supersonic Viscous Flow

Schiff, Lewis B.; Steger, J. L.

doi:10.2514/3.50902

Cited by 104 publications

(37 citation statements)

References 19 publications

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“…The thin-layer equations are solved using the PNS technique of Schiff and Steger [1]. Following the approach of Schiff and Steger, the governing equations are solved using a conservative, approximately factored, implicit finite-difference numerical algorithm as formulated by Beam and Warming [7].…”

Section: A$ An Ac Re Asmentioning

confidence: 99%

“…Computation of the viscous flow field about the various projectile configurations was accomplished by solving the thin-layer Navier-Stokes equations using the parabolized Navier-Stokes (PNS) technique of Schiff and Steger [1], Using the PNS technique, computational results were obtained by marching through the grid from the projectile nose to the trailing edge of the fins. This technique is applicable in the supersonic flow regime and requires that the flow field contain no regions of flow separation in the axial direction.…”

Section: Computational Approachmentioning

confidence: 99%

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Effect of Body Cross Section on Projectile Aerodynamic Performance With Application to Electromagnetic (EM) Guns

Weinacht¹

2001

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The most effective bore cross-section geometry for electromagnetic (EM) guns may differ significantly from the circular cross section of conventional guns. The geometry of the bore cross section will influence the shape of the armature/subprojectile launch package. For certain applications, a noncircular cross section may provide payload packaging benefits which have not been considered previously for conventional circular cross-section guns. Whether these benefits can be fully realized depends, in part, on the aerodynamic performance of these geometries in free flight. The current study considers the aerodynamics of chemical energy (CE)-type munitions to determine whether there are potential aerodynamic benefits for noncircular cross-section geometries compared with conventional circular cross-section bodies. The study compares the aerodynamic drag and static stability of both circular and noncircular geometries using sophisticated computational aerodynamic predictive tools to determine the potential aerodynamic benefits.

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Section: A$ An Ac Re Asmentioning

confidence: 99%

Section: Computational Approachmentioning

confidence: 99%

Effect of Body Cross Section on Projectile Aerodynamic Performance With Application to Electromagnetic (EM) Guns

Weinacht¹

2001

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“…The thin-layer equations are solved using the PNS technique of Schiff and Steger (14). Following the approach of Schiff and Steger, the governing equations, which have been modified here to include the Coriolis and centrifugal force terms, are solved using a conservative, approximately factored, implicit finite-difference numerical algorithm as formulated by Beam and Warming (15).…”

Section: Looping Motionmentioning

confidence: 99%

Navier-Stokes predictions of the individual components of the pitch-damping coefficient sum

Weinacht¹

1995

20th Atmospheric Flight Mechanics Conference

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) April 2004 REPORT TYPE ARL-TR-3169 SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTAn approach for predicting the two individual aerodynamic damping coefficients that form the pitch-damping coefficient sum is presented. The coefficients are obtained using prescribed or forced motions that independently excite the two different angular rates that are associated with the two damping coefficients. A key feature of the approach is that steady flow fields are produced by the selected motions. Steady flow computational fluid dynamics approaches can be applied, allowing results to be obtained in a computationally efficient manner. Application of the technique is made to an axisymmetric projectile configuration. The predicted pitch-damping coefficient sum obtained by adding the individually determined coefficients is in excellent agreement with previous predictions of the pitch-damping coefficient sum and with experimental data. Additional validation of the approach is obtained through comparisons with prior results from numerical solutions of the nonlinear unsteady potential equation. The individual coefficients are also compared with slender body theory, and the results show similar trends though the slender body theory appears to underpredict the various coefficients. iii SUBJECT TERMS

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“…11 Using the parabolized Navier-Stokes technique, computational results are obtained by marching through the grid from the projectile nose to the base. This technique is applicable in the supersonic flow regime and requires that the flow field contain no regions of flow separation in the axial direction.…”

Section: Computational Approachmentioning

confidence: 99%

Navier-Stokes predictions of pitch damping for a family of flared projectiles

Weinacht

1991

9th Applied Aerodynamics Conference

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Numerical Simulation of Steady Supersonic Viscous Flow

Cited by 104 publications

References 19 publications

Effect of Body Cross Section on Projectile Aerodynamic Performance With Application to Electromagnetic (EM) Guns

Effect of Body Cross Section on Projectile Aerodynamic Performance With Application to Electromagnetic (EM) Guns

Navier-Stokes predictions of the individual components of the pitch-damping coefficient sum

Navier-Stokes predictions of pitch damping for a family of flared projectiles

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