Air force research laboratory, wrightpatterson air force base, oh, 45433 abstract in a rectangular supersonic inlet the first. Location to store data, source code, input and output files. Driscollz university of michigan, ann arbor, mi, 48109. The supersonic air is decelerated by the inlet through a system of shocks. Reducedorder modeling of twodimensional supersonic. Glenn recently completed testing on an advanced highspeed inlet for propulsion systems to power air transport vehicles at supersonic speeds. So, if im not missing out on some important small speck of knowledge that complicates dsis way, way more than being a bump to subsonicize air of course a slight bit more than that, but you get the idea, then i feel like it is justified for me to get the well. A supersonic inlet has to provide homogeneous, low speed and high pressure air flow to the compres sor face of an engine over a wide range of speeds, altitudes. Driscoll2 university of michigan, ann arbor, mi, 48109 john a. The phenomenon occurs when mass flow rate changes significantly within a duct. Steady analysis of naca flush inlet at high subsonic and supersonic speeds taimur a. At the inlets exit i hav given pressure outlet as boundary. The term inlet unstart is considered in the present paper as a synonym of the absence. Supin assumes that the engine face dimensions are specified.
Supersonic engine inlets for airbreathing engines on supersonic vehicles, usually want to slow flow down to subsonic speeds inside engine need diffuser m1m file. A brief summary is made of the performance of a series of variablegeometry type scoop inlets investigated at the lewis laboratory on a model of the x3 airplane fuselage. The overall aim of this study is to determine to what extent vortex generators vgs can mitigate flow separations within supersonic inlets. Inlet tools effort includes aspects of creating an electronic database of inlet design information, a document describing inlet design and analysis methods, a. Numerical study on performance of supersonic inlets with various. Avoiding unstarts is a key objective in design of the engine air intakes inlets u.
The supersonic performance of high bypass ratio turbofan. The role of the inlet is more complex at supersonic speeds due to the phenomenon known as shock wave boundary layer interaction swbli. Pdf study on concept design of supersonic inlet and flow. Experimental results show that there exist two flow fields in the hypersonic inlets when the forebody waves interact with the lip boundary, which is similar to the shock reflection ion hysteresis phenomenon.
Comparing the simple diagrams of subsonic and supersonic inlets, we can appreciate that the subsonic inlet has the simpler task. When i went thru the help files,it says that the fluent ignores the pressure outlet boundary condition if the flow is locally supersonic. Experimental investigation of corner flows in rectangular. A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity based on the combination of inlet gas velocity and tangential speed of the ramp which forms a supersonic shockwave axially, between adjacent strakes. Textbased ascii input data file with blocks and lines of input. The baseline set of inlets include axisymmetric pitot, twodimensional singleduct, axisymmetric outwardturning, and twodimensional bifurcatedduct inlets. Currently capable of design and analysis of externalcompression, supersonic inlets mach1. In order to evaluate performance of the topmounted inlets, the starboard flowthrough nacelle on the aerodynamic model was replaced by a 2. The inlet tools effort includes aspects of creating an electronic database of inlet design information, a document describing inlet design and analysis methods, a. An experimental investigation of flow control for supersonic inlets. Roundedlip inlets are found to give satisfactory performance to a mach number. The current numerical simulations showed that a bumptype inlet can provide an improvement in the total pressure recovery downstream of the shock wave.
A well designed subsonic a 1 inlet will produce a stagnation pressure recovery. Members must be invited by the eroom coordinator john slater. To achieve this, an experimental investigation was undertaken in a smallscale wind tunnel, because smallscale wind tunnels are much more amenable to numerous measurement techniques than real inlets. Dsis seem like such an absolutely elegant solution to a problem that has, so far, been solved in a truly overly complicated way. In order to improve the performance of the flow field, counterflow is applied to control the shock reflection configuration in the hypersonic inlets. The results of designing and numerical gasdynamic modeling a supersonic threedimensional inlet of a new type are considered. Preliminary design of a 2d supersonic inlet to maximize total. Mixed compression engine inlets are designed to improve the efficiency of supersonic flight vehicles. Design and analysis tools for supersonic inlets computational tools are being developed for the design and analysis of. Supersonic engine inlets for airbreathing engines on supersonic vehicles, usually want to slow flow down to subsonic speeds inside engine need diffuser m1m inlet exception.
The inlet achieves better pressure recovery in compressing the air and reducing it to subsonic speeds through the use of multiple oblique shock waves, which are weaker than normal shock waves. At supersonic flight speeds the pressure and temperature rise in the inlet can. Shams1, masud j2 abstract essence of this research is to report computational analysis of naca flush inlets at high subsonic and supersonic free stream mach numbers at sea. Supin supersonic inlet design code incorporates the supersonic inlet geometry model and design and analysis methods.
Preliminary design of a 2d supersonic inlet to maximize. Compared to typical inlets in this operating range, tests showed high pressure recovery, low cowl drag, reduced complexity, increased safety, significant manufacturing cost reduction and weight, as well as increased efficiency, said david lam. Externalcompression supersonic inlet design code a computer code named supin has been developed to perform aerodynamic design and analysis of externalcompression, supersonic inlets. Performance of supersonic scoop inlets unt digital library. In the former case, an oblique shock system forms upstream of the cowl leading edge, followed by a terminal normal shock located at the cowl. The propulsion systems of jet aircraft are composed of three mayor parts. Media in category diverterless supersonic inlets the following 6 files are in this category, out of 6 total. Variable geometry inlets can be used over a relatively wide range of mach numbers than the. A ramp of external compression of this inlet is the vshaped body forming an initial plane oblique shock wave and a. Pdf the present paper deals with concept design of supersonic inlet based on compressible flow theory and flow control of bleeding in order to.
Externalcompression supersonic inlet design code ntrs nasa. The objective of this study is to understand how to integrate conical spike external compression inlets with high bypass turbofan engines for application on future supersonic airliners. Subsonic and supersonic air intakes linkedin slideshare. For efficient stable operation of the inlet, two control systems are needed, one to control the inlet geometry and one to control the bypass flow. Wellperforming supersonic inlets on gas turbine engines must provide uniform, stable, and subsonic flow before the engine face for compression and combustion. For a supersonic inlet, a common engine is the turbofan for which the engine face is circular and a spinner exists about the. In supersonic aerodynamics, unstart refers to a generally violent breakdown of the supersonic airflow. The objective is to update existing tools and provide design and loworder aerodynamic analysis capability for advanced inlet concepts. Data are presented for a range of inlet massflow ratios over a mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. The performance of the engine inlet is largely affected by the shockboundary layer interactions sblis. Several engines of efficient fuel consumption and differing bypass ratios were developed through the engine trade studies and used with the aerodynamic data of the concorde to test the aircraft performance of a supersonic airliner using these engines. Supersonic wind tunnel 8x6 swt to validate the configurations sonic boom signature. As the slowed, but still supersonic, air continues to move farther into the inlet, the normal shock wave springs up between the.
An advanced highspeed inlet for propulsion systems to power air transport vehicles at supersonic speeds has completed testing at nasas glenn research center, cleveland. Aerodynamic design of a supersonic threedimensional inlet. The design and operation of supersonic inlets is discussed as fully as the extent of this report will allow. Geometry control is needed so that the inlet compression surfaces can be varied with supersonic flight conditions in order to obtain efficient inlet compression. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high. Modern concepts of operation of supersonic inlets of highvelocity airbreathing engines are analyzed. Subsonic and supersonic air intakes jet propulsion sanjay singh asst. Diverterless supersonic inlet dsi the diverterless supersonic inlet dsi is a novel air inlet design principle, used most famously on the lockheed martin f35 lightning ii. Database contains pdf files of publicdomain papers, reports, and other literature. Experimental investigation of corner flows in rectangular supersonic inlets with 3d shockboundary layer effects w.
The supersonic performance of high bypass ratio spencer. Unlike typical inlets for supersonic cruise that rely on a mix of external and internal compression, this inlet accomplishes all of the supersonic. Us2772620a us297194a us29719452a us2772620a us 2772620 a us2772620 a us 2772620a us 297194 a us297194 a us 297194a us 29719452 a us29719452 a us 29719452a us 2772620 a us2772620 a us 2772620a authority us united states prior art keywords inlet supersonic air air inlet missile prior art date 19520703 legal status the legal status is an assumption and is not a legal. This can create large, complex 3d separation zones that reduce the effective flow area and can lead to the. The farther back over the cone the air moves, the more speed it bleeds off. Gasdynamic problems in offdesign operation of supersonic.
The cone shape of the spike also incrementally reduces the speed of the incoming supersonic air without producing a drastic loss of pressure. Results of this inlet performance testing are reported herein. Investigation of flow control for the hypersonic inlets. It is demonstrated that the flow in the engine duct becomes extremely complicated in offdesign modes of inlet operation, which can lead to unpredictable consequences, in particular, to inlet unstart. In a rectangular supersonic inlet the first oblique shock wave will interact with both the sidewall boundary layers and with the corner flows. Us2772620a air inlet for supersonic airplane or missile. Steady analysis of naca flush inlet at high subsonic and. Many performance problems arise when inlets are matched with engines as inlets come with a plethora of limitations and losses that greatly affect an engines.
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