Improved supersonic performance for the F-16 inlet modified for the J79 engine

Hunter, L.; Cawthon, J.

doi:10.2514/3.22758

Cited by 5 publications

(3 citation statements)

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“…Also, at Mach 0.6 a bypass valve was activated to direct air into the compressor face. The development of a practical variable-geometry inlet design also facilitates the development for the F-16 through a long term program that began at the outset of the YF-16 prototype (Hunter and Cawthon, 1984). This concept entailed the conformal shaping combined with a conventional external compression inlet design technique to enhance airplane integration and performance.…”

Section: Introductionmentioning

confidence: 99%

“…The Modular Common Inlet Concept Design intake would allow flexibility in the selection of future engines for the F-16 by efficiently providing performance over the large range of airflows (Hagseth, 1987). Other improvements of the F-16 intake aerodynamics included the implementation of a fixed double-ramp inlet with a throat slot bleed system implemented on the F-16/J79, a derivative of the F-16 A/B (Hunter and Cawthon, 1984). The improvements were seen in the supersonic region (Mach 2.0); with spill drag decrease over 60% and performance increase of about 20%.…”

Section: Introductionmentioning

confidence: 99%

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Flight Maneuverability Characteristics of the F-16 CFD and Correlation with its Intake Total Pressure Recovery and Distortion

Ibrahim

Wong³

2011

Engineering Applications of Computational Fluid Mechanics

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An investigation of the intake pressure recovery and distortion effects observed by varying maneuverability conditions of the F-16 was conducted. Simulations were conducted by using the Partial Differential Equation (PDE) calculator COMSOL. Results were validated with the classical s-duct, showing reasonable qualitative agreement. The maneuverability of the F-16 was defined using three factors: Mach number, angle of attack and angle of sideslip. The values of pressure recovery and distortion were measured at the Aerodynamic Interface Plane (AIP). Two sets of simulations were conducted: one to compare the sea level and 10 km altitude flight condition and another to correlate the required air intake and engine performance with pressure recovery and distortion at the AIP. Results of the flight level comparisons showed a slightly higher pressure recovery at 10 km of 0.985 compared to sea level condition value of 0.983. Distortion coefficient values for both conditions were however similar at 0.120. The difference in recovery values is attributed to the less viscous characteristic of air at higher altitude. This resulted in lower secondary flow formations in the intake. With increasing altitude, temperature plots showed a linear decreasing profile throughout the intake. The study provides a platform to a future model which couples the results obtained from the intake as inlet conditions to turbine flow simulations. This would provide a more holistic understanding of the propulsion system in the F-16.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Flight Maneuverability Characteristics of the F-16 CFD and Correlation with its Intake Total Pressure Recovery and Distortion

Ibrahim

Wong³

2011

Engineering Applications of Computational Fluid Mechanics

View full text Add to dashboard Cite

show abstract

“…A Mach 2.0 fixed geometry intake with an additional compression ramp intake (additional shocks) was also considered, but discarded for similar reasons (12% acceleration time penalty, 7% decrease in turn rate at Mach 1.2 and 250 lb of additional dry weight). Incidentally, such an intake was later designed for the F-16/79, powered by the GE J79 engine, but, although it had a 20% higher total pressure recovery and 68% lower spillage drag at Mach 2.0 [12], the resulting weight penalty turned out to be one of the main reasons why the F-16/79 never went into service.…”

Section: A Pressure Recovery and Dragmentioning

confidence: 99%

Tradeoffs in Jet Inlet Design: A Historical Perspective

Sóbester

2007

Journal of Aircraft

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The design of the inlet(s) is one of the most demanding tasks of the development process of any gas turbine-powered aircraft. This is mainly due to the multi-objective and multidisciplinary nature of the exercise. The solution is generally a compromise between a number of conflicting goals and these conflicts are the subject of the present paper. We look into how these design tradeoffs have been reflected in the actual inlet designs over the years and how the emphasis has shifted from one driver to another. We also review some of the relevant developments of the jet age in aerodynamics and design and manufacturing technology and we examine how they have influenced and informed inlet design decisions.

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Effect of the angle of attack on the YF-16 inlet

Ibrahim

Wong³

2010

IJAD

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Improved supersonic performance for the F-16 inlet modified for the J79 engine

Cited by 5 publications

References 0 publications

Flight Maneuverability Characteristics of the F-16 CFD and Correlation with its Intake Total Pressure Recovery and Distortion

Flight Maneuverability Characteristics of the F-16 CFD and Correlation with its Intake Total Pressure Recovery and Distortion

Tradeoffs in Jet Inlet Design: A Historical Perspective

Effect of the angle of attack on the YF-16 inlet

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