Effect of exit area variation on the performance of an auxiliary inlet ejector nozzle at Mach numbers from 0 to 1.27
Auxiliary inlet ejector nozzle designed for supersonic cruise aircraft
Blaha, B. J.↗
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Comparison of predicted and experimental wall temperatures for a cylindrical ejector exhaust nozzle operated with a turbojet gas generator
Comparison of predicted and experimental wall temperature for cylindrical ejector exhaust nozzle operated with turbojet gas generator
Lieberman, A.↗
High entrainment ejector design
High entrainment constant area multiple nozzle ejectors with two mixing tube lengths for boundary layer control, estimating performance with analytical model
Carey, J. H.↗
Ejector nozzle with massive blowing
Jet-flap, wing-blowing system for use in short takeoff and landing aircraft is described. System depends on ejector nozzle with large blowing capacity to direct ducted air against deflected flap. Operation of equipment during takeoff and cruise conditions is discussed. Diagrams of equipment are provided.
True, H. C.↗
Performance and noise generation studies of supersonic air ejectors
Experimental investigations were conducted to determine the aerodynamic performance and noise generation characteristics of five ejectors having subsonic secondary flow. Primary nozzles with equal exit area for Mach numbers 1, 1.5, 2, 2.5, and 3 produced a variety of noise and pumping effects. The pumping capacity, specific power, and noise generation of the Mach 1 nozzle was the highest and its mass augmentation was the lowest among the nozzles tested. The Mach 3 nozzle was found superior in mass augmentation and it also produced the lowest noise, however its pumping capacity and specific power was the lowest.
Barna, P. S.↗
Flight velocity influence on jet noise of conical ejector, annular plug and segmented suppressor nozzles
An F106 aircraft with a J85-13 engine was used for static and flight acoustic and aerodynamic tests of a conical ejector, an unsuppressed annular plug, and three segmented suppressor nozzles. Static 100 ft. arc data, corrected for influences other than jet noise, were extrapolated to a 300 ft. sideline for comparison to 300 ft. altitude flyover data at M = 0.4. Data at engine speeds of 80 to 100% (max dry) static and 88 to 100% flight are presented. Flight velocity influence on noise is shown on peak OASPL and PNL, PNL directivity, EPNL and chosen spectra. Peak OASPL and PNL plus EPNL suppression levels are included showing slightly lower flight than static peak PNL suppression but greater EPNL than peak PNL suppression. Aerodynamic performance was as anticipated and closely matched model work for the 32-spoke nozzle.
Brausch, J. F.↗
Computer program for calculating the flow field of supersonic ejector nozzles
An analytical procedure for computing the performance of supersonic ejector nozzles is presented. This procedure includes real sonic line effects and an interaction analysis for the mixing process between the two streams. The procedure is programmed in FORTRAN 4 and has operated successfully on IBM 7094, IBM 360, CDC 6600, and Univac 1108.
Anderson, B. H.↗
Vector thrust induced lift effects for several ejector exhaust locations on a V/STOL wind tunnel model at forward speed
The results and analysis of aerodynamic force data obtained from a small scale model of a V/STOL research vehicle in a low speed wind tunnel are presented. The analysis of the data includes the evaluation of aerodynamic-propulsive lift performance when operating twin ejector nozzles with thrust deflected. Three different types of thrust deflector systems were examined: 90 deg downward deflected nozzle, 90 deg slotted nozzle with boundary layer control, and an externally blown flap configuration. Several nozzle locations were tested, including over and underwing positions. The interference lift of the nacelle and model due to jet exhaust thrust is compared and results show that 90 deg turned nozzles located over the wing (near the trailing edge) produce the largest interference lift increment for an untrimmed aircraft, and that the slotted nozzle located under the wing near the trailing edge (in conjunction with a BLC flap) gives a comparable interference lift in the trimmed condition. The externally blown flap nozzle produced the least interference lift and significantly less total lift due to jet thrust effects.
Sharon, A. D.↗
Thrust performance of isolated, two-dimensional suppressed plug nozzles with and without ejectors at Mach numbers from 0 to 0.45
A series of two-dimensional plug nozzles was tested with and without ejector shrouds at free stream Mach numbers from 0 to 0.45 and over a range of nozzle pressure ratios from 2 to 4. These nozzles were also tested with and without chute noise suppressors. A two-dimensional plug nozzle has an efficiency of 96.1 percent at an assumed takeoff pressure ratio of 3.0 and Mach 0.36. A 12-chute suppressed nozzle with sidewalls has an efficiency of 81.0 percent (15.1 percent below the unsuppressed nozzle).
Harrington, D. E.↗
Integration of ejectors into high-speed aircraft
The integration of ejectors into forebodies is considered for transonic and supersonic flight. Topics discussed include mixing flow in ducts, prediction of flow fields and external aerodynamics.
Duvvuri, T.↗
A simple apparatus for the experimental study of non-steady flow thrust-augmenter ejector configurations
A flexible, and easily modified, test rig is described which allows a one dimensional nonsteady flow stream to be generated, economically from a steady flow source of compressed air. This nonsteady flow is used as the primary stream in a nonsteady flow ejector constituting part of the test equipment. Standard piezo-electric pressure transducers etc. allow local pressures to be studied, as functions of time, in both the primary and secondary (mixed) flow portions of the apparatus. Provision is also made for measuring the primary and secondary mass flows and the thrust generated. Sample results obtained with the equipment are presented.
Khare, J. M.↗
Considerations of some critical ejector problems
Some aspects of ejector design and application, including, three dimensional effects and cross flow effects are presented.
Alperin, M.↗
The effect of inflow velocity profiles on the performance of supersonic ejector nozzles
The effect of initial velocity profile on the performance of axisymmetric supersonic ejector nozzles is discussed. Two different initial profiles in each of two different geometries are analyzed, and the importance of using realistic starting conditions to predict supersonic nozzle performance is demonstrated.
Bishop, A. R.↗
The effect of inflow velocity profiles on the performance of supersonic ejector nozzles
The design of supersonic nozzles is becoming increasingly complex as conflicting requirements for low noise, higher efficiency, and wider operating range are driving the designer toward more variable geometry and multiple stream flows. Analysis techniques must be modified and expanded to take into account these additional complexities and still retain the rapid computational rate necessary for optimization and design studies. A nozzle analysis must handle more flow streams, more complex geometries, and more highly distorted initial profiles. This paper discusses some modifications to a method for calculating the performance characteristics of supersonic ejector nozzles and demonstrates the improvement in results the modifications provide.
Bishop, A. R.↗
Capture-ejector satellites
A satellite in the form of a large rotating rim is described which can be used to boost spacecraft from low-Earth orbit to higher orbits. The rim rotates in the plane of its orbit such that the lower portion of the rim is travelling at suborbital velocity, while the upper portion is travelling at greater than orbital velocity. Ascending spacecraft or payloads arrive at the lowest portion of the rim at suborbital velocities, attach to the perimeter, and remain until they reach the highest point, where the payloads are released on a trajectory for higher orbits; descending payloads employ the reverse procedure. Electric thrusters placed on the rim maintain rim rotational speed and altitude. From the standpoint of currently known materials, the capture-ejector concept may be useful for relatively small velocity increments.
Macconochie, I. O.↗
Entrainment and mixing in thrust augmenting ejectors
An experimental investigation of two-dimensional thrust augmenting ejector flows has been conducted. Measurements of the shroud surface pressure distribution, mean velocity, turbulent intensities and Reynolds stresses were made in two shroud geometries at various primary nozzle pressure ratios. The effects of shroud geometry and primary nozzle pressure ratio on the shroud surface pressure distribution, mean flow field and turbulent field were determined. From these measurements the evolution of mixing within the shroud of the primary flow and entrained fluid was obtained. The relationship between the mean flow field, the turbulent field and the shroud surface pressure distribution is discussed.
Bernal, L.↗
Ejector nozzle test results at simulated flight conditions for an advanced supersonic transport propulsion system
Results are presented of wind tunnel tests conducted to verify the performance improvements of a refined ejector nozzle design for advanced supersonic transport propulsion systems. The analysis of results obtained at simulated engine operating conditions is emphasized. Tests were conducted with models of approximately 1/10th scale which were configured to simulate nozzle operation at takeoff, subsonic cruise, transonic cruise, and supersonic cruise. Transonic cruise operation was not a consideration during the nozzle design phase, although an evaluation at this condition was later conducted. Test results, characterized by thrust and flow coefficients, are given for a range of nozzle pressure ratios, emphasizing the thrust performance at the engine operating conditions predicted for each flight Mach number. The results indicate that nozzle performance goals were met or closely approximated at takeoff and supersonic cruise, while subsonic cruise performance was within 2.3 percent of the goal with further improvement possible.
Nelson, D. P.↗
Capture-ejector satellites
A satellite in the form of a large rotating rim which can be used to boost spacecraft from low-Earth orbit to higher orbits is described. The rim rotates in the plane of its orbit such that the lower portion of the rim is traveling at suborbital velocity, while the upper portion is travelling at greater than orbital velocity. Ascending spacecraft or payloads arrive at the lowest portion of the rim at suborbital velocities, where the payloads are released on a trajectory for higher orbits; descending payloads employ the reverse procedure. Electric thrusters placed on the rim maintain rim rotational speed and altitude. From the standpoint of currently known materials, the capture-ejector concept may be useful for relatively small velocity increments.
Macconochie, I. O.↗