The Effects of Heat Shielding in Jet Engine Exhaust Systems on Aircraft Survivability

Yi, Kyung Joo; Baek, Seung Wook; Kim, Man Young; Lee, Sung Nam; Kim, Won Cheol

doi:10.1080/10407782.2013.869441

Cited by 6 publications

(2 citation statements)

References 20 publications

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“…Estimating surface temperature distribution for an aircraft in flight requires solving heat-balance equations for the entire airframe which is a complicated task because of the complex flowfield around the aircraft, particularly at transonic and supersonic flight speeds. Researchers have frequently resorted to CFD [12] [13] [30] [31] to generate solutions for the aircraft heat balance problem, however, as a result of the computational intensity of the calculations involved, the data presented correspond to a limited number of operating conditions and/or do not cover the entire airframe.…”

Section: Skin Temperature Estimationmentioning

confidence: 99%

Effects of Propulsion System Operation on Military Aircraft Survivability

Antonakis

Nikolaidis

Pilidis

2019

Journal of Aircraft

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The recent advances in Infra-Red (IR) weapon technology have dramatically altered the rules of air combat leading to a consistent departure from 'traditional' Energy-Maneuverability philosophy in aircraft design, prioritizing stealth and sophisticated armament instead. In this modern aerial warfare environment, it is obvious that new techniques need to be applied to properly assess aircraft survivability and produce successful designs for aircraft propulsion systems. The present study focuses on the development of such a methodology, which contrary to related work in the field includes considerations for both aircraft IR signature and missile/aircraft kinematic performance. An aircraft IR signature model is constructed using a collection of methods for area & temperature estimation and exhaust plume modelling; the latter is combined with missile-vs-aircraft and aircraft-vsaircraft simulations to quantify aircraft survivability in the form of missile & aircraft lethal zones. The proposed methodology is applied to a study on propulsion system effects on aircraft survivability, in which a comparison between different engine configurations is performed: In the scenarios examined, IR signature at cruise conditions and maximum-power thrust performance are identified as key parameters for aircraft combat performance. Nomenclature (Nomenclature entries should have the units identified) A = Area AB = Afterburner

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Section: Skin Temperature Estimationmentioning

confidence: 99%

Effects of Propulsion System Operation on Military Aircraft Survivability

Antonakis

Nikolaidis

Pilidis

2019

Journal of Aircraft

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“…(i) thermal insulation around engine to reduce heat transfer to outer casing; 22,23 (ii) surface emissivity (ε) reduction/optimization, depending on band and role of Earthshine and skyshine.…”

Section: Introduction To Aircraft Infrared Signatures From Frontal As...mentioning

confidence: 99%

Long-wave infrared signature of aircraft nose and its emissivity for low observability

Vinayak

Mahulikar

2023

J. Appl. Rem. Sens.

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High speeds have been an advantage for aircraft to fly out of the adversary's airspace fast, to escape earlier generations of infrared (IR) guided missiles that could lock-on only from the rear aspect. Advancements in IR seekers in long-wave IR (LWIR, 8 to 12 μm) band with imaging sensors in focal plane arrays made them capable of tracking aircraft also from the frontal aspect, which is a tactical advantage. Aerodynamically heated airframe surfaces are LWIR signature hot spots that increase aircraft susceptibility from front and bottom views. The conventional belief is that IR signatures of aircraft nose is only due to temperature-based emission acquired by aerodynamic heating at high Mach number (M amb ). Our study reports the LWIR contrast of aircraft nose (with nose replaced skyshine as background) by considering: (i) aerodynamic heating (important for high ε nose , M amb ) and (ii) reflected skyshine and Earthshine (important at low ε nose , M amb ), where skyshine is more important relative to Earthshine. Earthshine irradiance is obtained using atmospheric transmittance and view factor between visible circular Earth-disc and nose surface. The role of a transition Mach number (M trans ) in emissivity selection is identified as follows: for M amb < M trans , LWIR contrast decreases with ε nose and for M amb > M trans , LW-IR contrast increases with ε nose .

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Analysis of the IR Signature and Radiative Base Heating from a Supersonic Solid Rocket Exhaust Plume

Kim

Baek

2019

Int. J. Aeronaut. Space Sci.

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The Effects of Heat Shielding in Jet Engine Exhaust Systems on Aircraft Survivability

Cited by 6 publications

References 20 publications

Effects of Propulsion System Operation on Military Aircraft Survivability

Effects of Propulsion System Operation on Military Aircraft Survivability

Long-wave infrared signature of aircraft nose and its emissivity for low observability

Analysis of the IR Signature and Radiative Base Heating from a Supersonic Solid Rocket Exhaust Plume

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