If an approximate similarity principle could be established, properly chosen performance parameters should be similar for both hot and cold flow tests if the initial Mach number and total pressures of the flow field are held constant. Existing ejector data is used to explore the utility of one particular similarity principle; the Munk and Prim similarity principle for isentropic flows. Static performance test data for a full- scale thrustaugmenting ejector are analyzed for primary flow temperatures up to 1. R. At different primary temperatures, exit pressure contours are compared for similarity. GG7, CCG2) A-121 this was an old astrogation plotter. The basic training program.A nondimensional flow parameter is then used to eliminate primary nozzle temperature dependence and verify similarity between the hot and cold flow experiments. An investigation of corner separation within a thrustaugmenter having Coanda jets. NASA Technical Reports Server (NTRS)Seiler, M. R. 1. 97. 9- 0. 1- 0. The development of separation in corners of thrust augmentor wings having Coanda jets was investigated using hot film surface sensors and pressure transducers. Separation on the test augmentor began at a corner very close to the augmentor exit and then rapidly proceeded upstream. Plotter (device) -- besayek Plural (n.) -- wehu Plus -- eh, heh. Program -- tumau, tumaya; tumak (computer) Programmed, to be -- putumau Project (n.) -- ar'tu (anc.). Long Live Songun Politics! Well, he’d program a worm to go through the computer and delete all references. Measurements of the pressure fields in the corner region indicated that a modified form of the Stratford criterion could be used to predict the onset of separation. Testing was conducted over a range of nozzle pressure ratios, aspect ratios, diffuser angles, and designs of the boundary layer and Coanda nozzles. Performance Charts for a Turbojet System. NASA Technical Reports Server (NTRS)Karp, Irving M. Convenient charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet system. These charts take into account the effects of ram pressure, compressor pressure ratio, ratio of combustion- chamber- outlet temperature to atmospheric temperature, compressor efficiency, turbine efficiency, combustion efficiency, discharge- nozzle coefficient, losses in total pressure in the inlet to the jet- propulsion unit and in the combustion chamber, and variation in specific heats with temperature. The principal performance charts show clearly the effects of the primary variables and correction charts provide the effects of the secondary variables. The performance of illustrative cases of turbojet systems is given. It is shown that maximum thrust per unit mass rate of air flow occurs at a lower compressor pressure ratio than minimum specific fuel consumption. The thrust per unit mass rate of air flow increases as the combustion- chamber discharge temperature increases. For minimum specific fuel consumption, however, an optimum combustion- chamber discharge temperature exists, which in some cases may be less than the limiting temperature imposed by the strength temperature characteristics of present materials. Performance Charts for the Turbojet Engine. NASA Technical Reports Server (NTRS)Pinkel, Benjamin; Karp, Irving M. Charts are presented for computing the thrust, fuel consumption, and other performance values of a turbojet engine for any given set of operating conditions and component efficiencies. The effects of the pressure losses in the inlet duct and combustion chamber, the variation in the physical properties of the gas as it passes through the cycle, and the change in mass flow by the addition of fuel are included. The principle performance charts show the effects of the primary variables and correction charts provide the effects of the secondary variables. Extended Operation of Turbojet Engine with Pentaborane. NASA Technical Reports Server (NTRS)Useller, James W; Jones, William L1. A full- scale turbojet engine was operated with pentaborane fuel continuously for 2. Mach number of 0. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1. JP- 4 fuel to 0. 9. A portion of this thrust loss is potentially recoverable with proper design of the engine components. The boron oxide deposition and erosion processes within the engine approached an equilibrium condition after approximately 2. Uncertainty of in- flight thrust determination. NASA Technical Reports Server (NTRS)Abernethy, Robert B.; Adams, Gary R.; Steurer, John W.; Ascough, John C.; Baer- Riedhart, Jennifer L.; Balkcom, George H.; Biesiadny, Thomas. Methods for estimating the measurement error or uncertainty of in- flight thrust determination in aircraft employing conventional turbofan/turbojet engines are reviewed. While the term 'in- flight thrust determination' is used synonymously with 'in- flight thrust measurement', in- flight thrust is not directly measured but is determined or calculated using mathematical modeling relationships between in- flight thrust and various direct measurements of physical quantities. The in- flight thrust determination process incorporates both ground testing and flight testing. The present text is divided into the following categories: measurement uncertainty methodoogy and in- flight thrust measurent processes. Annular MHD Physics for Turbojet Energy Bypass. NASA Technical Reports Server (NTRS)Schneider, Steven J. The use of annular Hall type MHD generator/accelerator ducts for turbojet energy bypass is evaluated assuming weakly ionized flows obtained from pulsed nanosecond discharges. The equations for a 1- D, axisymmetric MHD generator/accelerator are derived and numerically integrated to determine the generator/accelerator performance characteristics. The concept offers a shockless means of interacting with high speed inlet flows and potentially offers variable inlet geometry performance without the complexity of moving parts simply by varying the generator loading parameter. The cycle analysis conducted iteratively with a spike inlet and turbojet flying at M = 7 at 3. N- s/kg. The turbojet allowable combustor temperature is set at an aggressive 2. K. The annular MHD Hall generator/accelerator is L = 3 m in length with a B(sub r) = 5 Tesla magnetic field and a conductivity of sigma = 5 mho/m for the generator and sigma= 1. The calculated isentropic efficiency for the generator is eta(sub sg) = 8. Ng) = 0. 6. 3. The calculated isentropic efficiency for the accelerator is eta(sub sa) = 8. Na) = 0. 6. 2. An assessment of the ionization fraction necessary to achieve a conductivity of sigma = 1. X 1. 0(exp - 6), and for sigma = 5. X 1. 0(exp - 6). Optimum flight paths of turbojet aircraft. NASA Technical Reports Server (NTRS)Miele, Angelo. The climb of turbojet aircraft is analyzed and discussed including the accelerations. Three particular flight performances are examined: minimum time of climb, climb with minimum fuel consumption, and steepest climb. The theoretical results obtained from a previous study are put in a form that is suitable for application on the following simplifying assumptions: the Mach number is considered an independent variable instead of the velocity; the variations of the airplane mass due to fuel consumption are disregarded; the airplane polar is assumed to be parabolic; the path curvatures and the squares of the path angles are disregarded in the projection of the equation of motion on the normal to the path; lastly, an ideal turbojet with performance independent of the velocity is involved. The optimum Mach number for each flight condition is obtained from the solution of a sixth order equation in which the coefficients are functions of two fundamental parameters: the ratio of minimum drag in level flight to the thrust and the Mach number which represents the flight at constant altitude and maximum lift- drag ratio. Combustion Limits and Efficiency of Turbojet Engines. NASA Technical Reports Server (NTRS)Barnett, H. R. 1. 95. 6- 0. 1- 0. Combustion must be maintained in the turbojet- engine combustor over a wide range of operating conditions resulting from variations in required engine thrust, flight altitude, and flight speed. Furthermore, combustion must be efficient in order to provide the maximum aircraft range. Thus, two major performance criteria of the turbojet- engine combustor are (1) operatable range, or combustion limits, and (2) combustion efficiency. Several fundamental requirements for efficient, high- speed combustion are evident from the discussions presented in chapters III to V. The fuel- air ratio and pressure in the burning zone must lie within specific limits of flammability (fig. Increases in mixture temperature will favor the flammability characteristics (ch. A second requirement in maintaining a stable flame - is that low local flow velocities exist in the combustion zone (ch. Finally, even with these requirements satisfied, a flame needs a certain minimum space in which to release a desired amount of heat, the necessary space increasing with a decrease in pressure (ref. It is apparent, then, that combustor design and operation must provide for (1) proper control of vapor fuel- air ratios in the combustion zone at or near stoichiometric, (2) mixture pressures above the minimum flammability pressures, (3) low flow velocities in the combustion zone, and (4) adequate space for the flame. Development study of a precooled turbojet engine. NASA Astrophysics Data System (ADS)Sato, Tetsuya; Taguchi, Hideyuki; Kobayashi, Hiroaki; Kojima, Takayuki; Fukiba, Katsuyoshi; Okai, Daisaku Masaki, Keiichi; Fujita, Kazuhisa; Hongo, Motoyuki; Sawai, Shujiro. A precooled turbojet engine has been developed by JAXA used for the hypersonic airplane and spaceplane. The subscale engine named . The components and the system firing tests under the sea- level- static condition were successfully conducted. In the next phase, a flight test of the S- engine is planned using a stratospheric balloon in 2. BOV). The vehicle is dropped from an altitude of 4. After 4. 0 s free- fall, the vehicle is pulled up and the S- engine operates for 3. D2. 0 - Star Wars - The Completely Unofficial Star Wars Encyclopedia. BFBoba Fett (comic series)BFEEwoks: The Battle for Endor (motion picture)BGSBattle for the Golden Sun (WEG adventure module)BHASThe Bounty Hunters: Aurra Sing (comic)BIBlack Ice (WEG adventure module)BPBalance Point (novel)BTMStar Wars : Behind the Magic (computer software)BTSBefore the Storm (novel)BSSBlack Sands of Socorro (WEG supplement)BWX- Wing Rogue Squadron: The Bacta War (novel)CStar Wars: Chewbacca (comic series)CCCCrisis on Cloud City (WEG adventure)CCGStar Wars: Customizable Card Game - Premiere Edition. CCG2. Star Wars: Customizable Card Game - A New Hope. CCG3. 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