High Mach propulsion system installation and exhaust system design considerations

Dusa, D.

doi:10.2514/6.1987-2941

Cited by 1 publication

(1 citation statement)

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“…./nozzle Jnozzle Jramp exit__________________exit__________________________________ Vs y\ dmi (2) where Vs = f(P T8 /P 0 ,T T8 , y).…”

Section: Single Expansion Ramp Nozzle Studymentioning

confidence: 99%

Preliminary assessment of exhaust systems for high-Mach (4-6) fighter aircraft

Kuchar¹,

Wolf²

1993

Journal of Propulsion and Power

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Exhaust systems designed for high-Mach fighter aircraft will operate at nozzle pressure ratios near 100 for a Mach 4 aircraft to possibly over 600, depending on inlet recovery, for a Mach 6 aircraft. Also, the nozzle pressure loading will be two to four times higher than current Mach 1.5-2.2 exhaust systems, and the exhaust gas temperatures will be significantly higher. These new operating conditions for high Mach nozzles will result in substantial increases in both nozzle size and weight relative to current exhaust systems. Analytical studies have been conducted to assess the internal performance of the conventional axisymmetric nozzle, the twodimensional, convergent-divergent (2DCD) nozzle, and the single expansion ramp nozzle (SERN) operating at high Mach conditions. Weight estimates have also been completed for the 2DCD nozzle matrix. As expected, results of the studies show that the 2DCD and SERN concepts can achieve desired levels of performance at the expense of size and weight. In general, the exhaust systems for Mach 4-6 aircraft will have to be three to four times as large and four to five times as heavy as those currently employed on Mach 1.5-2.2 aircraft. The axisymmetric nozzle has geometric constraints that limit its performance capability.

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“…./nozzle Jnozzle Jramp exit__________________exit__________________________________ Vs y\ dmi (2) where Vs = f(P T8 /P 0 ,T T8 , y).…”

Section: Single Expansion Ramp Nozzle Studymentioning

confidence: 99%