Experimental investigation of corner flows in rectangular supersonic inlets with 3d shockboundary layer effects w. Supin assumes that the engine face dimensions are specified. Wellperforming supersonic inlets on gas turbine engines must provide uniform, stable, and subsonic flow before the engine face for compression and combustion. 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 cone shape of the spike also incrementally reduces the speed of the incoming supersonic air without producing a drastic loss of pressure. 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. Mixed compression engine inlets are designed to improve the efficiency of supersonic flight vehicles. Textbased ascii input data file with blocks and lines of input. Roundedlip inlets are found to give satisfactory performance to a mach number. The propulsion systems of jet aircraft are composed of three mayor parts. The phenomenon occurs when mass flow rate changes significantly within a duct. The overall aim of this study is to determine to what extent vortex generators vgs can mitigate flow separations within supersonic inlets. 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.
Glenn recently completed testing on an advanced highspeed inlet for propulsion systems to power air transport vehicles at supersonic speeds. For a supersonic inlet, a common engine is the turbofan for which the engine face is circular and a spinner exists about the. The supersonic performance of high bypass ratio spencer. An advanced highspeed inlet for propulsion systems to power air transport vehicles at supersonic speeds has completed testing at nasas glenn research center, cleveland. 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. A well designed subsonic a 1 inlet will produce a stagnation pressure recovery. Variable geometry inlets can be used over a relatively wide range of mach numbers than the. Preliminary design of a 2d supersonic inlet to maximize. The inlet tools effort includes aspects of creating an electronic database of inlet design information, a document describing inlet design and analysis methods, a.
Inlet tools effort includes aspects of creating an electronic database of inlet design information, a document describing inlet design and analysis methods, a. Us2772620a air inlet for supersonic airplane or missile. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high. The farther back over the cone the air moves, the more speed it bleeds off. In a rectangular supersonic inlet the first oblique shock wave will interact with both the sidewall boundary layers and with the corner flows. The supersonic performance of high bypass ratio turbofan. A ramp of external compression of this inlet is the vshaped body forming an initial plane oblique shock wave and a.
Avoiding unstarts is a key objective in design of the engine air intakes inlets u. 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. In order to improve the performance of the flow field, counterflow is applied to control the shock reflection configuration in the hypersonic inlets. Investigation of flow control for the hypersonic inlets. Database contains pdf files of publicdomain papers, reports, and other literature. Supersonic engine inlets for airbreathing engines on supersonic vehicles, usually want to slow flow down to subsonic speeds inside engine need diffuser m1m file.
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. Geometry control is needed so that the inlet compression surfaces can be varied with supersonic flight conditions in order to obtain efficient inlet compression. Numerical study on performance of supersonic inlets with various. Steady analysis of naca flush inlet at high subsonic and. 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.
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. Modern concepts of operation of supersonic inlets of highvelocity airbreathing engines are analyzed. Comparing the simple diagrams of subsonic and supersonic inlets, we can appreciate that the subsonic inlet has the simpler task. Reducedorder modeling of twodimensional supersonic. 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. Supersonic wind tunnel 8x6 swt to validate the configurations sonic boom signature. Design and analysis tools for supersonic inlets computational tools are being developed for the design and analysis of. Externalcompression supersonic inlet design code ntrs nasa. 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. Currently capable of design and analysis of externalcompression, supersonic inlets mach1. 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. Driscollz university of michigan, ann arbor, mi, 48109. The design and operation of supersonic inlets is discussed as fully as the extent of this report will allow.
The baseline set of inlets include axisymmetric pitot, twodimensional singleduct, axisymmetric outwardturning, and twodimensional bifurcatedduct inlets. This can create large, complex 3d separation zones that reduce the effective flow area and can lead to the. Air force research laboratory, wrightpatterson air force base, oh, 45433 abstract in a rectangular supersonic inlet the first. The performance of the engine inlet is largely affected by the shockboundary layer interactions sblis. The objective is to update existing tools and provide design and loworder aerodynamic analysis capability for advanced inlet concepts. 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. Driscoll2 university of michigan, ann arbor, mi, 48109 john a. Aerodynamic design of a supersonic threedimensional inlet. 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.
The results of designing and numerical gasdynamic modeling a supersonic threedimensional inlet of a new type are considered. Gasdynamic problems in offdesign operation of supersonic. An experimental investigation of flow control for supersonic inlets. Unlike typical inlets for supersonic cruise that rely on a mix of external and internal compression, this inlet accomplishes all of the supersonic. In order to evaluate performance of the topmounted inlets, the starboard flowthrough nacelle on the aerodynamic model was replaced by a 2. At supersonic flight speeds the pressure and temperature rise in the inlet can. As the slowed, but still supersonic, air continues to move farther into the inlet, the normal shock wave springs up between the. The current numerical simulations showed that a bumptype inlet can provide an improvement in the total pressure recovery downstream of the shock wave. Subsonic and supersonic air intakes linkedin slideshare. Media in category diverterless supersonic inlets the following 6 files are in this category, out of 6 total.
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 total. Pdf the present paper deals with concept design of supersonic inlet based on compressible flow theory and flow control of bleeding in order to. At the inlets exit i hav given pressure outlet as boundary. 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. 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. Externalcompression supersonic inlet design code a computer code named supin has been developed to perform aerodynamic design and analysis of externalcompression, supersonic inlets. The supersonic air is decelerated by the inlet through a system of shocks.
Performance of supersonic scoop inlets unt digital library. Subsonic and supersonic air intakes jet propulsion sanjay singh asst. When i went thru the help files,it says that the fluent ignores the pressure outlet boundary condition if the flow is locally supersonic. Location to store data, source code, input and output files.
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. In supersonic aerodynamics, unstart refers to a generally violent breakdown of the supersonic airflow. Members must be invited by the eroom coordinator john slater. The role of the inlet is more complex at supersonic speeds due to the phenomenon known as shock wave boundary layer interaction swbli. The term inlet unstart is considered in the present paper as a synonym of the absence. 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. Pdf study on concept design of supersonic inlet and flow. Dsis seem like such an absolutely elegant solution to a problem that has, so far, been solved in a truly overly complicated way. 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.
1452 446 443 1044 1204 1392 429 525 270 617 36 869 1367 931 813 1387 378 505 1332 1063 1029 1310 892 732 1317 1213 1251 151 1414 422 880 986 1420 346 671 1215 151 1219 406 666 1268 636 33