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  • Other Sources  (39)
  • Spacecraft Propulsion and Power  (18)
  • PROPELLANTS  (11)
  • Temperatur
  • 2005-2009
  • 2000-2004
  • 1955-1959  (39)
  • 1959  (26)
  • 1958  (13)
Collection
  • Maps
  • Other Sources  (39)
Years
  • 2005-2009
  • 2000-2004
  • 1955-1959  (39)
Year
  • 1
    facet.materialart.
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    In:  32. Deutsche Pflanzenschutztagung der Biologischen Bundesanstalt für Land- und Forstwirtschaft in Hannover, 6.-10. Oktober 1958; Mitt. Biol. Bundesanst. Land-Forstwirtsch. Berlin-Dahlem 97, p. 181-188
    Publication Date: 1959
    Description: Untersuchungen zu den Bedingungen für das Verlassen des Bodens und somit den Beginn des Zufluges um eine optimale Bekämpfung zu ermöglichen KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf die Aktivität von Gallmücken KATASTER-DETAIL: T (Boden, 2cm) 〉 20°C, dann Verlassen des Bodens; Tmax (Luft) 〉 16°C, dann Gallmücken flugaktiv
    Keywords: Aschersleben und Seggerde ; 1955-1958 ; Boden ; Pflanzenschädling ; Temperatur ; Weizen ; Witterung
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  • 2
    Publication Date: 1959
    Description: Beschreibung der Schwankungen des Beginns, des Endes sowie die Gesamtschwankung der Vegetationsperiode unter Verwendung langjähriger Reihen, phänologische Ereignisse wie Schneeglöckchenblüte, Blüte, Ernte und Länge der Reifezeit von Roggen, Erfassung des Zusammenhangs zwischen Niederschlägen, Wärmeanspruch und der Phänologie KATASTER-BESCHREIBUNG: Bestimmung der Winterroggenblüte mithilfe der Blunckschen Hyperbel (Temperatursummenregel) für Wernigerode und Dölitz (Sachsen) Bestimmung der Niederschläge (y) im Juli auf die Reifezeit von Roggen (ertragswirksamste Phase) KATASTER-DETAIL: Wernigerode (T=4,0+138,0/t) mit T mittlere Temp. während der Entwicklungsdauer in Tagen t, Blühbeginn Roggen zwischen dem 34. und 64. Tag, Dölitz (T=4,0+347,6/t), Blühbeginn Roggen zwischen dem 38. und 52. Tag, y (in mm)= -353,1+9,3Xt
    Keywords: Mitteldeutschland ; 1854-1953 ; Ertrag ; Niederschlag ; Phänologie ; Roggen ; Temperatur
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  • 3
    Publication Date: 1959
    Description: Mit Hilfe von Aufzuchtversuchen in Aufzuchtzylindern, der Analyse eigener Beobachtungen und der Analyse von Berichten des Meldedienstes im Zeitraum 1953-1957 sucht der Autor nach Zusammenhängen zwischen dem Auftreten der Kohldrehherzmücke und klimatischen Parametern. Im Zuge der Analysen wird als Modell für die Entwicklung des Schaderregers bzw. für die Ermittlung des ersten Schlupftermins im Jahr ein Schwellenwert berechnet. KATASTER-BESCHREIBUNG: Prognose des ersten Schlüpftermins der Kohldrehherzmücke im Jahr mittels einer Temperatursummenregel KATASTER-DETAIL: C=(Temperatursumme von t1-t2)-(Anzahl aufsummierter Tage*Schwellwert) mit den vorher im Versuch bestimmten Werten C(Temperaturkonstante)=160 und Schwellwert(Temperaturnullpunkt)=7,2°C
    Keywords: DDR ; 1953-1957 ; Insekten ; Pflanzenschädling ; Temperatur ; Kohl
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  • 4
    facet.materialart.
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    In:  Höfchen-Briefe, Jahrgang 12, Heft 3, p. 111-140
    Publication Date: 1959
    Description: Erkenntnisse über die Art des sommerlichen Entwicklungsablaufes und der Freilandüberwinterung der Mittelmeerfruchtfliege in Mitteleuropa KATASTER-BESCHREIBUNG: Zusammenhang zwischen Befallsintensität und Temperatur während der einzelnen Stadien KATASTER-DETAIL: Delta T (Sommer, Herbst) +, dann Anzahl +; Delta T (Januar)+, dann Zeit der Puppenruhe - und weitere Überwinterung als Imago; T 〉 12°C, dann Schlüpfen; Delta T (Januar) + und Delta T (Februar)-, dann Anzahl -; Delta T (Winter) --, dann Anzahl --; Delta T (Winter) + und Delta T (Sommer) +, dann Anzahl ++;
    Keywords: Mitteleuropa ; 1. Hälfte 20. Jahrhundert ; Insekten ; Pfirsich ; Apfel ; Boden ; Ertrag ; Pflanzenschädling ; Temperatur ; Frost ; Obst
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  • 5
    Publication Date: 1959
    Description: Untersuchungen zur Klärung der Einflüsse von Mikro- und Bestandsklima auf die Entwicklung der Cercospora beticola KATASTER-BESCHREIBUNG: Zusammenhänge zwischen dem Mikroklima (Luftfeuchte und Temperatur) und der Befallsstärke KATASTER-DETAIL: Delta Relf: Relf〉95% bei t〉8h/d und Zeitperiode: t〉3d, dann Befall +; Benetzungszeiten t〉10h/d und Zeitperiode: t〉3d, dann Befall + Delta T: 15°C〈T〈22°C, dann Infektion +
    Keywords: Niederbayern ; 1956-1957 ; Zuckerrüben ; Luftfeuchte ; Klima ; Pflanzenkrankheit ; Temperatur
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  • 6
    facet.materialart.
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    In:  Mitt. Biol. Bundesanst. Land-Fortwirtsch. Berlin-Dahlem, p.178-180
    Publication Date: 1959
    Description: Freilandversuche zur Bestimmung des 1. Schlüpftermins der Kohldrehherzmücke KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperatur und Beginn der Flugzeit KATASTER-DETAIL: Delta Nied -, dann Entwicklung -; Nied = 20mm (innerhalb weniger Tage) und T(Boden 5-10cm Tiefe)= 20-22°C, dann Ende Diapause und Entwicklung +; 1. Schlüpftermin=Beginn der Flugzeit: Bluncksche Wärmesummenregel: C-Wert = 160 , Schwellenwert = 7,2°C
    Keywords: DDR ; 1950-58 ; Insekten ; Boden ; Niederschlag ; Pflanzenschädling ; Temperatur
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  • 7
    Publication Date: 1959
    Description: Untersuchung der Beziehung zwischen Temperaturabweichungen und phänologischen Beobachtungen in verschiedenen Regionen KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf die Pflanzenentwicklung, bzw. auf den Zeitpunkt der Reife KATASTER-DETAIL: Delta T (Mai, Juni, Juli) -, dann Pflanzenentwicklung - (später);
    Keywords: Paris, Berlin, Mittel-England, Niederlande ; 1731-40 ; Phänologie ; Roggen ; Temperatur ; Weizen
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  • 8
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: PROPELLANTS
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  • 9
    Publication Date: 2019-05-11
    Description: Injector evaluation in 2400-pound-thrust rocket engine using liquid oxygen and liquid ammonia
    Keywords: PROPELLANTS
    Type: NASA-MEMO-12-11-58E
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  • 10
    Publication Date: 2019-05-11
    Description: Single fuel-vaporizing combustor with injectors adapted for gaseous hydrogen
    Keywords: PROPELLANTS
    Type: NACA-RM-E55I14
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  • 11
    Publication Date: 2019-05-24
    Description: Gaseous hydrogen and liquid oxygen experiments in uncooled 20,000-pound-thrust rocket engines
    Keywords: PROPELLANTS
    Type: NASA-MEMO-4-8-59E
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  • 12
    Publication Date: 2019-05-23
    Description: Performance of composite solid propellant at simulated high altitudes
    Keywords: PROPELLANTS
    Type: NASA-TM-X-95
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  • 13
    Publication Date: 2019-06-28
    Description: Measurements of near- and far-field noise pressures are presented for a 1,500-pound-thrust engine and for several 5,000-pound-thrust engines for which the nozzle exit pressure was changed systematically in order to study its effects on the noise level and spectra. Near-field surveys indicated that the highest noise pressure occurred at about 20 exit diameters downstream if the nozzle near the transition from super-sonic to subsonic flow. The acoustical power radiated from all engines averaged about 0.5 percent of the mechanical power of the exhaust stream, the least noise being radiated by the nozzle having an exit pressure less than atmospheric. The rocket engines of these tests radiate more power per cycle at the lower frequencies than arte reported for subsonic jets in other related studies.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TN-D-21
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  • 14
    Publication Date: 2019-08-17
    Description: Two rocket configurations with turbopump drive were investigated analytically. In one configuration the inlet pressure to the turbine was fixed at the design value. The second configuration employed a "bootstrap" technique for supplying energy to the turbine. An injector was the chief resistance between the pump and the rocket combustion chamber. From the analysis two parameters were developed from which the speed response time of the turbopump, the flow response time, and the maximum dynamic line loss could be evaluated. These parameters were functions of turbopump moment of inertia, design performance of the turbine, and flow-system geometry. The moment of inertia of the turbopump and the ratio of turbine torque at zero speed to design torque had the most influence on the starting dynamics of the flow system. These parameters were also applicable to the bootstrap configuration as long as the inlet pressure to the turbine exceeded half the design value.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-4-21-59E
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  • 15
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    In:  CASI
    Publication Date: 2019-08-17
    Description: A five-stage solid-fuel sounding-rocket system which can boost a payload of 25 pounds to an altitude of 525 nautical miles and that of 100 pounds to 300 nautical miles is described. Data obtained from a typical flight test of the system are discussed.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-3-6-59L
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  • 16
    Publication Date: 2019-08-17
    Description: An experimental study shows that 2 percent by weight ozone in oxygen has little effect on overall reactivity for a range of oxidant-fuel weight ratios from 1 to 6. This conclusion is based on characteristic-velocity measurements in 200-pound-thrust chambers at a pressure of 300 pounds per square inch absolute with low-efficiency injectors. The presence of 9 percent ozone in oxygen also did not affect performance in an efficient chamber. Explosions were encountered when equipment or procedure permitted ozone to concentrate locally. These experiments indicate that even small amounts of ozone in oxygen can cause operational problems.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-5-26-59E , E-327
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  • 17
    Publication Date: 2019-08-17
    Description: With the advent of the space age, new adjustments in technical thinking and engineering experience are necessary. There is an increasing and extensive interest in the utilization of materials for components to be used at temperatures ranging from -423 to over 3500 deg F. This paper presents a description of the materials problems associated with the various components of chemical liquid rocket systems. These components include cooled and uncooled thrust chambers, injectors, turbine drive systems, propellant tanks, and cryogenic propellant containers. In addition to materials limitations associated with these components, suggested research approaches for improving materials properties are made. Materials such as high-temperature alloys, cermets, carbides, nonferrous alloys, plastics, refractory metals, and porous materials are considered.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-X-89
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  • 18
    Publication Date: 2019-08-15
    Description: The effect of turbine-inlet temperature on rocket gross weight was investigated for three high-energy long-range rockets in order to explore the desirability of turbine cooling in rocket turbodrive applications. Temperatures above and below the maximum that is permissible in uncooled turbines were included. Turbine bleed rate and stage number were considered as independent variables. The gross weight of the hydrogen-reactor system was more sensitive to changes in turbine-inlet temperature than either the hydrogen-oxygen or the hydrogen-fluorine systems. Gross weight of the hydrogen-reactor system could be reduced by 2.6 percent by the use of cooling and a turbine-inlet temperature of 3000 R. The reductions in the first stages of the hydrogen-oxygen and hydrogen-fluorine systems were 0.7 and 0.2 percent, respectively. The effect of turbine-inlet temperature on rocket gross weight was small because the resulting turbine weight and bleed rate variations were small. Since these small gains must be balanced against considerations of greater cost, weight, and complexity as well as lessened reliability with a system utilizing a cooled turbine, none of the systems investigated showed gains warranting the use of turbine cooling.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-1-6-59E
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  • 19
    Publication Date: 2019-08-15
    Description: Tests have been conducted to determine the starting characteristics of a 50,000-pound-thrust rocket engine with the conditions of a quantity of fuel lying dormant in the simulated main thrust chamber. Ignition was provided by a smaller rocket firing rearwardly along the center line. Both alcohol-water and anhydrous ammonia were used as the residual fuel. The igniter successfully expelled the maximum amount of residual fuel (3 1/2 gal) in 2.9 seconds when the igniter.was equipped with a sonic discharge nozzle operating at propellant flow rates of 3 pounds per second. Lesser amounts of residual fuel required correspondingly lower expulsion times. When the igniter was equipped with a supersonic exhaust nozzle operating at a flow of 4 pounds per second, a slightly less effective expulsion rate was encountered.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-2-1-59H , H-101
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  • 20
    Publication Date: 2019-08-15
    Description: Two 10-inch-diameter spherical rocket motors have been flight tested at the NASA Wallops Station. These tests were conducted to measure "spin-up" or amplification of the spinning velocity of the motor during the thrusting process due to internal swirling of the exhaust gases. Model 1, a heavy-wall motor, experienced an increase in spin rate during thrusting of about 10 percent, whereas model 2, a flight-type motor with a lightweight motor case, experienced an increase of about 19 percent. The propellant weight and geometry were the same for both motors. A simple relationship for "spin-up" which satisfies these measured results is reported herein. Both models were spin stabilized throughout their flights. A theoretical method of predicting spin-up was derived and used to extend the measured 10-inch-motor results to spherical rocket motors of other sizes having a similar propellant geometry. This method is presented and its predictions are shown to compare favorably with the measured flight results.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-X-75
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  • 21
    Publication Date: 2019-08-15
    Description: A conceptual design of a nuclear turboelectric powerplant, producing 20,000 kilowatts of power suitable for manned space vehicles is presented. The study indicates that the radiator necessary for rejecting cycle waste heat is the dominant weight, and emphasis is placed on the selection of cycle operating conditions in order to reduce this weight. A thermodynamic cycle using sodium vapor as the working fluid and operating at a turbine-inlet temperature of 2500 R was selected. The total powerplant weight was calculated to be approximately 6 pounds per kilowatt. The radiator contributes approximately 2.1 pounds per kilowatt to the total weight and the reactor and reactor shield contribute approximately 0.24 and 1.2 pounds per kilowatt, respectively. The generator, turbine, and piping add significantly to the total weight (between 0.5 and 0.6 lb/kw), but the heat exchanger, pumps, and so on are less important. Several important research areas associated with the development of a reliable nuclear turboelectric powerplant of the type analyzed are discussed.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-2-20-59E , E-156
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  • 22
    Publication Date: 2019-07-10
    Description: Limitations on fully developed laminar flows due to compressibility and property variations are examined. The cases, for liquids and for gases, wherein such motions are "exact" are determined and solutions are given. For more general conditions, not permitting an exact fully developed flow, limitations are set. Two cases arise depending on the size of the temperature variation across the channel. Both the forced and free flow are solved for the case of large temperature variation. Finally, there are described briefly some circumstances under which streamwise variations of velocity occur. The case where the velocity varies inversely with the square root of the distance is solved.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TR-R-33
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  • 23
    Publication Date: 2019-07-10
    Description: A concept of combustion time lag that includes dependency on injection velocity is introduced. The concept is used in the formulation of chamber transfer functions and in an analysis of low-frequency combustion instability. Theoretical frequency responses and stability boundaries are compared with those obtained when the injection-velocity effect on the time lag to be an important consideration, in the theory of chamber dynamics and combustion instability
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TR-R-43
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  • 24
    Publication Date: 2019-08-15
    Description: The performance for four altitudes (sea-level, 51,000, 65,000, and 70,000 ft) of a rocket engine having a nozzle area ratio of 48.39 and using JP-4 fuel and liquid oxygen as a propellant was evaluated experimentally by use of a 1000-pound-thrust engine operating at a chamber pressure of 600 pounds per square inch absolute. The altitude environment was obtained by a rocket-ejector system which utilized the rocket exhaust gases as the pumping fluid of the ejector. Also, an engine having a nozzle area ratio of 5.49 designed for sea level was tested at sea-level conditions. The following table lists values from faired experimental curves at an oxidant-fuel ratio of 2.3 for various approximate altitudes.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-5-14-59E
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  • 25
    Publication Date: 2019-08-15
    Description: A rocket engine with an exhaust-nozzle area ratio of 25 was operated at a constant chamber pressure of 600 pounds per square inch absolute over a range of oxidant-fuel ratios at an altitude pressure corresponding to approximately 47,000 feet. At this condition, the nozzle flow is slightly underexpanded as it leaves the nozzle. The altitude simulation was obtained first through the use of an exhaust diffuser coupled with the rocket engine and secondly, in an altitude test chamber where separate exhauster equipment provided the altitude pressure. A comparison of performance data from these two tests has established that a diffuser used with a rocket engine operating at near-design nozzle pressure ratio can be a valid means of obtaining altitude performance data for rocket engines.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-X-100
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  • 26
    Publication Date: 2019-08-15
    Description: The effect of turbopump design on rocket gross weight was investigated for a high-pressure bleed-type hydrogen-reactor long-range rocket with a fixed mission. Axial-flow, mixed-flow, and centrifugal pumps driven by single and twin turbines were considered. With an efficiency of 0.7 assumed for all pumps, the lowest rocket gross weights were obtained with an axial-flow or a mixed-flow pump driven by a single turbine of at least eight stages. All turbopump combinations could be used, however, with gross weight varying less than 8 percent for a given payload. Turbopump efficiencies have a significant effect on the ratio of gross weight to payload with the magnitude of the effect determined by the ratio of rocket structural weight to total propellant weight. One point in pump efficiency is worth 0.2 percent in gross weight for a given payload with a structural weight parameter of 0.1 and 0.6 percent with a structural weight parameter of 0.2. Turbine and pump weights are much less significant in terms of gross-to-pay weight ratio than the efficiencies of these components. One point in pump efficiency is equivalent to approximately 13 percent in pump weight, while 1 point in turbine efficiency is equivalent to about 7 percent in turbine weight.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-5-12-59E , E-215
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  • 27
    Publication Date: 1958
    Description: Auswertung aus 25jährigen Stammscheiben ermöglichen lagebedingte Darstellung von Ertragsunterschieden bei Fichte, Kiefer, weniger bei Buchen, Einfluss der Temperatur, des Niederschlages und der Höhe auf den Zuwachs KATASTER-BESCHREIBUNG: Der Zusammenhang von Niederschlag (Mai-August) und Temperatur (Mai-August) zum jährlichen Durchmesserwachstum ermöglich die Berechnung von Korrelations- und Regressionskoeffizienten, echte Beziehung in den unteren (〈400m) Höhenlagen, teilweise gesicherte Beziehungen in den mittleren (400-700m) Höhenlagen KATASTER-DETAIL: Delta Nied+ (Fichten in Eisenach): x=261+77.5(y-2.7) mit x=jährlicher Durchmesserzuwachs in mm, y=Niederschlagssumme Mai-August;
    Keywords: Thüringen ; letzten100 Jahre ; Buche ; Fichte ; Forst ; Kiefer ; Niederschlag ; Temperatur ; Vegetationsperiode ; Waldwachstum
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  • 28
    facet.materialart.
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    In:  Nachrichtenblatt für den deutschen Pflanzenschutzdienst Neue Folge, p. 143-150
    Publication Date: 1958
    Description: Untersuchungen des Schlupfverlaufs zur Ermittlung von Bedingungen, unter welchen mit einem verstärkten Auftreten der 2. Generation zu rechnen ist. KATASTER-BESCHREIBUNG: Regulation der Stärke der 2. Generation durch die während der Larvenentwicklung herrschenden Temperatur- und Lichtverhältnisse KATASTER-DETAIL: Delta Tmit (Monat) +, dann Schlüpftermin früher; Tmax 〈14°C, dann Anzahl schlüpfender Falter - bis 0;
    Keywords: Labor ; 1953-1957 ; Apfel ; Pflanzenschädling ; Temperatur
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  • 29
    facet.materialart.
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    In:  Nachr.bl. Deutsch. Pflanzenschutzdienst, p. 9-10
    Publication Date: 1958
    Description: Verbale Beobachtungen über das Freilandvorkommen der Zwiebellaus KATASTER-BESCHREIBUNG: Zusammenhang zwischen der Witterung (Temperatur) im Winter und dem Freilandauftreten der Laus KATASTER-DETAIL: Delta T (Winter) +, dann Massenvermehrung +
    Keywords: Hannover, Niedersachsen ; 1956-1957 ; Pflanzenschädling ; Temperatur ; Witterung
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  • 30
    Publication Date: 2019-05-11
    Description: A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor. Temperature as high as 1200 F was measured in the base region because of the ignition of burnable rocket gases. combustibles that are dumped into the base by accessories seriously aggravate the base-burning temperature rise.
    Keywords: Spacecraft Propulsion and Power
    Type: NACA-RM-E58G17
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  • 31
    Publication Date: 2019-05-11
    Description: Injection techniques for 200-pound thrust ammonia- oxygen rocket engine
    Keywords: PROPELLANTS
    Type: NACA-RM-E57H01
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  • 32
    Publication Date: 2019-06-28
    Description: Theoretical rocket performance for equilibrium composition during expansion was calculated for JP-4 fuel with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature, molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, thermal conductivity, and equilibrium gas compositions. A correlation is given for the effect of chamber pressure on several of the parameters. The maximum value of specific impulse for a chamber pressure of 600 pounds per square inch absolute (40.827 atm) and an exit pressure of 1 atmosphere is 325.7 for 70.37 percent fluorine in the oxidant as compared with 284.9 and 305.1 for 100 percent oxygen and 100 percent fluorine, respectively.
    Keywords: Spacecraft Propulsion and Power
    Type: NACA-RM-E57K22
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  • 33
    Publication Date: 2019-06-28
    Description: Theoretical rocket performance for frozen composition during expansion was calculated for liquid methane with several fluorine-oxygen mixtures for a range of pressure ratios and oxidant-fuel ratios. The parameters included are specific impulse, combustion-chamber temperature, nozzle-exit temperature molecular weight, characteristic velocity, coefficient of thrust, ratio of nozzle-exit area to throat area, specific heat at constant pressure, isentropic exponent, viscosity, and thermal conductivity. The maximum calculated value of specific impulse for a chamber pressure of 600 pounds per square inch absolute (40.827atm) and an exit pressure of 1 atmosphere is 315.3 for 79.67 percent fluorine in the oxidant.
    Keywords: Spacecraft Propulsion and Power
    Type: NACA-RM-E58B20
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  • 34
    Publication Date: 2019-05-11
    Description: Effect of pressure level on afterburner wall temperature
    Keywords: PROPELLANTS
    Type: NACA-RM-E58D01
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  • 35
    Publication Date: 2019-05-11
    Description: Design of single-stage turbine for rotor entering at supersonic speed - performance characteristics
    Keywords: PROPELLANTS
    Type: NACA-RM-E58F2OA
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  • 36
    Publication Date: 2019-05-30
    Description: Fluorine-liquid oxygen mixture and injector design effects on JP-4 jet fuel performance in rocket engines
    Keywords: PROPELLANTS
    Type: NACA-RM-E58C18
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  • 37
    Publication Date: 2019-06-27
    Description: Thermostability and heat sink capacity of diborane, pentaborane, and ethyl decaborane fuels for jet aircraft
    Keywords: PROPELLANTS
    Type: NASA-MEMO-10-7-58E
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  • 38
    Publication Date: 2019-08-17
    Description: The results of a static investigation conducted to measure the normal forces on the entire jet-vane assembly and the hinge moments on the jet vane produced by a paddle vane oscillating in the jet of a 1,500-pound-thrust rocket motor are presented for vane-deflection angles from -5 deg to 25 deg. A maximum average normal force of 71 pounds with a corresponding value for maximum average hinge moment of 228 inch-pounds was obtained with the maximum area of jet vane immersed at a jet-vane angle of 25 deg decrease in thrust caused by immersion of the jet vane varied from a maximum loss of about 58 pounds, or approximately 5 percent at maximum jet-vane angle of 25 deg, to zero loss at jet-vane angles less than approximately 10 deg.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-10-19-58L
    Format: application/pdf
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  • 39
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    Unknown
    In:  CASI
    Publication Date: 2019-08-14
    Description: Off-design performance of divergent ejectors
    Keywords: PROPELLANTS
    Type: NACA-RM-E58G10A , AD0224447
    Format: application/pdf
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