Prediction of rocket plume flowfields for infrared signature studies

Dash, S. M.; Pearce, B.; Pergament, H. S.; Fishburne, E. S.

doi:10.2514/6.1979-95

Cited by 6 publications

(10 citation statements)

References 3 publications

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“…However, the Case D results are significantly lower for each altitude compared with Case A. This variation of radiation emissions with respect to turbulent mixing rate has been recognized by Dash et al (1980) in the context of turbulence model assessment for plume flows. The increased mixing rate in Case D also increases the drop-off rate of the total intensity over Case A.…”

Section: Resultsmentioning

confidence: 71%

“…The features evident in this solution are typical «all cases. A curved "barrel" shock is evident in Figure 4 1(b) and is characteristic of highly underexpanded American Institute of Aeronautics and Astronautics AIAA 98-3618 plume flows (Dash et al, 1980). This shock reflects off the axis of symmetry and interacts with the surrounding shear layer between the exhaust gases and the external flow.…”

Section: Resultsmentioning

confidence: 97%

“…These interactions not only affect species production and temperature distributions but may also impact the radiation predictions (Pearce and Varma, 1981). In addition, a complex shock wave pattern (Dash et al, 1980) exists in the plume to equilibrate the exhaust flow pressure with the atmosphere. Reflected shocks may excite vortical roll up of the shear layer (e.g., Norris and Edwards, 1997) enhancing mixing and may also provide a temperature rise to stabilize afterburning.…”

Section: Introductionmentioning

confidence: 99%

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Evaluation of Afterburning Cessation Mechanisms in Fuel Rich Rocket Exhaust Plumes

Calhoon¹,

.²

1998

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Publicfeporting 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 this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this 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)2. REPORT TYPE A computational study was conducted to identify fundamental physical processes governing the cessation or shutdown of the afterburning of fuel rich rocket exhaust with the atmosphere. Several mechanisms that have been proposed were examined which are: 1) a relaminarization phenomenon, 2) a Damköhler number effect and 3) a classical flame extinction mechanism. Analysis of the simulation results revealed the relammanzation mechanism to be implausible while the Damköhler number effect and the flame extinction mechanisms were found to be valid. The extinction mechanism was also found to dramatically alter the emissions characteristics • and enhance the shutdown behavior which has important implications with respect to radiative heat transfer to the body and missile intercept systems. This is a significant finding because strain rate induced extinction is a previously unrecognized phenomena occurring in rocket exhaust plumes during afterburning cessation. Technical Papers

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Section: Resultsmentioning

confidence: 71%

Section: Resultsmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

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Evaluation of Afterburning Cessation Mechanisms in Fuel Rich Rocket Exhaust Plumes

Calhoon¹,

.²

1998

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“…In addition, a complex shock wave pattern 4 exists in the plume to equilibrate the exhaust flow pressure with the atmosphere. Reflected shocks may excite vortical roll up of the shear layer (e.g., Ref.…”

Section: Introductionmentioning

confidence: 99%

Computational Assessment of Afterburning Cessation Mechanisms in Fuel-Rich Rocket Exhaust Plumes

Calhoon

2001

Journal of Propulsion and Power

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A computational study was conducted to identify fundamental physical processes governing the cessation or shutdown of the afterburning of fuel rich rocket exhaust with the atmosphere. Several mechanisms were examined which are: 1) a relaminarization phenomenon, 2) a Damköhler number effect and 3) a classical flame extinction mechanism. Analysis of the simulation results revealed the relaminarization mechanism to be implausible while the Damköhler number effect and the flame extinction mechanisms were found to be valid. The extinction mechanism was also found to dramatically alter the emission characteristics and enhance the shutdown behavior which has important implications with respect to radiative heat transfer to the body and missile defense systems. This is a significant finding because strain rate induced extinction is a previously unrecognized phenomena occurring in rocket Approved for public release; distribution unlimited exhaust plumes during afterburning cessation.

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“…The prediction of afterburning shutdown using engineering level modeling techniques 3 has been relatively successful for systems that exhibit the gradual drop-off type of shutdown event. However, these techniques have been less successful in predicting shutdown for systems that exhibit the rapid drop-off b ehavior.…”

mentioning

confidence: 99%

Assessment of Turbulence-Chemistry Interactions in Missile Exhaust Plume Signature Analysis

Calhoon

Kenzakowski

2003

Journal of Spacecraft and Rockets

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Prediction of rocket plume flowfields for infrared signature studies

Cited by 6 publications

References 3 publications

Evaluation of Afterburning Cessation Mechanisms in Fuel Rich Rocket Exhaust Plumes

Evaluation of Afterburning Cessation Mechanisms in Fuel Rich Rocket Exhaust Plumes

Computational Assessment of Afterburning Cessation Mechanisms in Fuel-Rich Rocket Exhaust Plumes

Assessment of Turbulence-Chemistry Interactions in Missile Exhaust Plume Signature Analysis

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