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  • Aerodynamics  (71)
  • Biochemistry and Biotechnology  (39)
  • AERODYNAMICS  (31)
  • Spacecraft Propulsion and Power  (14)
  • Animals
  • 1995-1999
  • 1955-1959  (155)
  • 1925-1929
  • 1959  (155)
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  • 1995-1999
  • 1955-1959  (155)
  • 1925-1929
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  • 1
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 1-11 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The effects of pH and concentration on foam separation of the protein bovine serum albumin (BSA) from solution has been studied. All results agree, at least qualitatively, with theory. BSA maximum enrichments were observed at the isoelectric pH and enrichment ratio was found to increase with decreasing protein concentrations.
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  • 2
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 13-25 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Most of the free fluid can generally be expressed from fibrous pulps in a few seconds at 50 lb/in2 if the layer of pulp is kept thinner than 1 in. after it has been pressed, and if the fluid is allowed to run away freely. The need for this time and the frictional properties of many pulps are serious obstacles to the design of any strictly continuous press. Roller presses do not allow enough time, screw expellers create too much friction, continuous centrifuges and some other arrangements are intricate and vulnerable.An intermittent but automatic press which avoids these defects is described. In this the material on a perforated conveyor is pressed by a ram and then moved forward as the ram lifts. One such machine has already been made. An outline is given of the principles on which an improved design will depend.
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  • 3
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 27-36 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Equipment has been developed in which fermentation processes for fastidious, pathogenic micro-organisms can be operated on a pilot-plant scale. Experience has shown the need for the development of concepts, techniques, and equipment meeting more stringent requirements than those ordinarily encountered in the fermentation industry. A system has been developed for the preparation of pure cultures which may be used either for the development of processes or in the preparation of substantial quantities of pure cultures. The equipment includes specially designed valves, fermentors, piping arrangement, and requires special methods of operation in order to maintain pure cultures during growth of the organism. The number of cultures of pathogenic, fastidious micro-organisms contaminated in the systems commonly used in industry is materially greater than the number of contaminated cultures produced in the system described.
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  • 4
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A strain of C. purpurea has been isolated which will produce L-tryptophan from indole in submerged culture.The L-tryptophan produced is extracellular and in a free form.Levels of up to 1·5 mg/ml of L-tryptophan have been obtained.
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  • 5
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 37-47 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The results of a study on the surface electric charge carried by fresh-water planktonic algae are used to provide a theory for the flocculation of algae with chemical coagulants. Where it is desirable to remove algae from water, for example from lakes or reservoirs for water supply, or from sewage oxidation ponds, the theory indicates certain practices are desirable to obtain the best removal. It is planned to extend the theory and experimental work to cover the removal of untreated algae from water by filtration through porous granular media, believed to be an adsorptive effect. Separation of different species of algae employing their electrokinetic properties is also described.
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  • 6
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 59-76 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An apparatus is described in which large numbers of algal cultures can be maintained under the following conditions: (1) Constant temperature within the range 5 to 70°C, four different temperatures being maintained simultaneously; (2) uniform illumination at intensities up to 20,000 metre-candles; (3) continuous shaking at variable speed; and (4) aeration under aseptic conditions with mixtures of up to four different gases in any desired proportions.Among other features, thermoregulator heads, flow-meters and heaters for sterile filters, of improved design are described.To illustrate the use of the apparatus, data showing the effects of light intensity and temperature on the growth of Monodus subterraneus are presented.
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  • 7
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 99-113 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The nature of the problem of mould growth on baked products is discussed. Existing information on the reduction of this source of wastage by chemical and irradiation techniques is briefly reviewed, and new experimental evidence is presented relating to the use of these procedures. The effectiveness of ionizing radiations in preventing mould growth is indicated but there are many problems to be considered before it can be regarded as a satisfactorily established technique.
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  • 8
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959) 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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  • 9
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 77-98 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Fractions of markedly different protein contents may be obtained by air-classifying flour (in the sub-sieve range) at cut sizes of about 17 and 35 μ respectively. Of these fractions, the fine, 1 (of high protein content), contains fragments of interstitial endosperm protein and small starch granules; the intermediate, 2 (low protein), mainly large starch granules; the coarse, 3, fragments of endosperm cells. The yields and protein contents of the fractions vary with different wheats; the yields of 1 and 2 may be greatly increased through suitably grinding the flour after milling.In general, 1 may be used for raising the protein content of flours deficient in protein to a level suitable for bread-making. The amount of 1 required depends on its protein contents and on whether it came from a hard or soft wheat, the hard wheat fraction having better bread-making qualities. The resulting variation in the proportion of 1 required in the blend causes variation in the proportion of other particulate materials introduced with 1, in which they have become concentrated during the air classification. These include diastatically active agents and finely divided discolouring matter; the level of the former reached in the blend greatly affects its bread-making value. Pre-grinding of the flour may be helpful in this respect.When chlorinated, 2 is potentially useful for making light-structured cakes, but hard English wheats have mainly given less satisfactory results than soft. Under certain conditions, 3, with or without 2, may be better for biscuit-making than the parent flour.
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  • 10
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 129-141 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Applying radio-isotope 32P, the distribution of bacterial cells retained within glass-fibre air sterilization filters was measured. In particular, the time-dependence of the radial as well as the longitudinal distribution was studied. The collection efficiency of glass-fibre was obtained and the experimental result was compared with a theoretical value based upon the sum of interception, inertia and diffusion. Discrepancies could not be accounted for and are similar to those in the literature. An equation was proposed for the estimation of air filter life. This was not completely verified but leads to some suggestive results.
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  • 11
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 207-215 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The mathematical relationship between the throughput of a batch centrifuge and its mechanical characteristics has been applied to the scale-up of one of the steps in virus processing for possible application to the production of vaccines and similar antigens. Slurries that contained a test virus were purified in a laboratory centrifuge. The Q/Σ relationship, developed by Ambler, was used to predict the operating conditions of a larger centrifuge in order to achieve the same clarification of slurry as that produced in the laboratory centrifuge. A correlation between conditions of centrifugation and amount of virus removed from the feed to the centrifuge shows that there is a well-defined Q/Σ value at which significant concentrations of the test virus are sedimented.
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  • 12
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 239-242 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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  • 13
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 243-243 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
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  • 14
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 229-238 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An account is given of the construction and operation of a fully automatic apparatus in which the material is kept under agitation in a closed container alternately surrounded by hot and cold alcohol supplied from separate baths. The apparatus has the following applications in microbiology and cell physiology: (1)Extraction of micro-organisms and cell tissues by repeated freezing (F) and thawing (T) at variable temperatures and lengths of FT cycle. Extraction can be controlled automatically or manually. As a practical example of the use of the apparatus a description is given of the extraction of living virulent S. typhi bacteria.(2)Studies of the reactions of living micro-organisms and tissues under varying physical conditions (e.g. high- and low-temperature resistance experiments, osmotic studies, thermal synchronization of bacterial cultures, etc.).(3)If required, the normal gas mixture in the residual air space can without difficulty be replaced by other gases or mixtures such as CO2 or N2.
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  • 15
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 217-228 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A process is described for the extraction of co-enzyme A from dried yeast. It involves cold water extraction, charcoal adsorption followed by pyridine elution, preparation of an acetone power, co-precipitation as the double cuprous complex with glutathione and removal of the glutathione by means of an ion exchange resin.Improvements over previous processes include use of drum dried yeast plus cold extraction resulting in easy filtration and increase of throughput by a factor of three to five, together with the elimination of the ion exchange step formerly thought necessary to remove zine before the co-precipitation stage. Under the best conditions yields represent 30% recovery of the co-enzyme A in the yeast, the product being 90% pure.
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  • 16
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    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959) 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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  • 17
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 244-244 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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  • 18
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 245-259 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The design and construction of a highly sensitive katharometer is described with special reference to the application of the instrument for the precise determination of traces of ethylene by gas chromatography. Factors influencing katharometer sensitivity, and the relative advantages and disadvantages of katharometers as compared with other types of detectors, are discussed.
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  • 19
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 273-288 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An electrophoretic method for the separation of acid polyelectrolytes from proteins in cell extracts is described.A description of the apparatus is given and some results of the separation of extracts from Bordetella pertussis are included.
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  • 20
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 289-295 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An ultrasonic generator was tested at 3 frequencies for its effects on Serratia marcescens during fermentation. The generator controlled foam adequately at 26, 29, and 34 kc/sec at medium aeration rates up to 0·6 ft3/min. Final viable counts were in the same range as those for cultures grown using lard oil as a foam control agent. At 34 kc/sec the final viable counts were slightly higher than those of cultures with lard oil.No harmful effects were evident when large volumes of cultures were exposed to ultrasonic energy during growth.
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  • 21
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The feasibility of producing antibiotics by single-stage continuous fermentation was explored by means of a specially designed pilot plant. Both the chloramphenicol and penicillin processes appeared adaptable to such an operation. At dilution rates of 1·0 and 0·5 volume changes per day respectively, yields of from ¼ to ½ of the maxima obtained in batch operation were maintained in the steady-state for more than 2 weeks.
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  • 22
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 393-412 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Kinetic data are needed to develop basic understanding of fermentation processes and to permit rational design of continuous fermentation processes.The kinetics of the fermentation of glucose to lactic acid have been studied at six constant pH levels between 4·5 and 6·0 by measuring the instantaneous rates of bacterial growth and of lactic acid formation throughout each fermentation.It was found that the instantaneous rate of acid formation dP/dt, could be related to the instantaneous rate of bacterial growth dN/dt, and to the bacterial density N, throughout a fermentation at a given pH, by the expression \documentclass{article}\pagestyle{empty}\begin{document}$\frac{{{\rm d}P}}{{{\rm d}t}} = \alpha \frac{{{\rm d}N}}{{{\rm d}t}} + \beta N$\end{document} where the constants α and β are determined by the pH of the fermentation.
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  • 23
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 413-429 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Information on fermentation process kinetics is potentially valuable for the improvement of batch process performance; it is essential for continuous process design. An empirical examination of rate patterns in various fermentations discloses three basic types: (1) ‘growth associated’ products arising directly from the energy metabolism of carbohydrates supplied, (2) indirect products of carbohydrate metabolism and (3) products apparently unrelated to carbohydrate oxidation. Effects of operating variables on the primary kinetic processes, growth, sugar utilization and antibiotic formation, in the penicillin process, illustrate the special nature of this type.
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  • 24
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Steady-state and transient equations are derived for continuous-flow fermentation processes. Analytical as well as graphical methods for predicting from batch data the performance of single- or multi-stage continuous fermentations are developed. The criteria for stability are also examined. Actual experimental measurements of continuous lactic acid fermentations conducted at controlled pH levels agree with the theory developed.
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  • 25
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 379-392 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A pilot plant unit for continuous cultivation of hyphaeforming micro-organisms, providing for a uniform flow velocity in fermentations on suspension media with a massive growth of mycelium, is described. For the maintenance of aseptic conditions, over-pressre of air is maintained in the whole equipment. This equipment has been used for studies of the continuous biosynthesis of streptomycin. A three-stage fermentation proved the most advantageous. The first stage serves for multiplication of the inoculum; the second and third for the formation of the antibiotic. The system was maintained for 300-400 h with yields amounting to 2,000-2,500 u. of streptomycin/ml without any signs of contamination or degeneration of the growing culture.
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  • 26
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959) 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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  • 27
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 143-162 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An analysis of the organic constituents of whole, domestic sewage was made by analysing four physically separated fractions. Settlement, centrifuging and filtration were used to obtain one liquid and three solid fractions. Concentration of the filtrate was achieved by freeze-drying with only minor changes in composition. The average concentration of organic carbon in fresh, whole domestic sewage was 310 p.p.m., of which about 70 per cent was in suspension. Eight classes of compounds were found, on analysis, to comprise about 75 per cent of the organic carbon in whole sewage and of the soluble organic carbon 80 per cent was distributed between five groups. Using chromatographic methods the concentrations of four volatile acids were determined and the presence of other acids was detected. Similarly, seven of the soluble sugars and eight present in hydrolysed suspended solids have been identified. The probable nature of some of the compounds unaccounted for is discussed.
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  • 28
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 163-172 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The influence of mechanical agitation in aerobic fermentations is felt mainly through increased aeration efficiency. For yeast propagations in which oxygen supply is abundant - and presumably not limiting to growth - a specific, but limited, effect of fluid agitation on growth rate has been demonstrated. The improved growth rate is attributed primarily to better mixing of the entire fluid mixture rather than to improved cell-fluid mass transfer.
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  • 29
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 115-127 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Information on a reliable method for determining the nutritive value of existing and experimental peptones is lacking in the literature. To overcome this handicap, a method for comparative evaluation of microbiological peptones has been developed.The method is based on measuring the growth of eight carefully selected, fastidious, test cultures. The cultures are grown in presence and absence of yeast extract in an inorganic basal medium containing test peptone and a low and high level of glucose.Statistical analysis of replicate peptone evaluations of six peptones, conducted over a period of six months, shows that 95 per cent confidence limits for this method are ± 2·5 to 7·9 per cent of the mean.Four criteria are employed for determining the overall performance of 12 widely used, commercial peptones.The method is very sensitive for detecting differences between batches of commercial peptones. With the aid of this method a new peptone ‘N-Z-Amine YT’ has been developed. Considering performance and relative cost, this peptone is the most economical of the peptones evaluated.
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  • 30
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 173-184 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A study of factors affecting the reproducibility and yields in cultivations of H. pertussis (the whooping cough organism). The search for suitable media led to the development of a new kind of blood medium suitable for pre-cultures. Sterility of the blood additive could be ensured by filtration, and contamination on starting the freeze-dried cells was avoided by the use of a special kind of ampoule.In the course of studies of different cultivation techniques a 6,000 ml ‘pulsaerator’ was found to be ideal for the preparation of ordinary small batches. Inoculation density, aeration and other factors affecting the yield were studied and a culture cycle suitable for preparing 500 l. batches was developed.
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  • 31
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 185-205 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The mathematical theory of the sedimentation type of centrifuge is developed in terms of unhindered settling of a single particle that has reached equilibrium velocity. From this is derived the sigma value for several of the different forms of sedimentation type centrifuge which is the calculated equivalent area of a settling tank theoretically capable of doing the same amount of work in a unit gravitational field. The limitations controlling the accuracy of scale up between centrifuges of similar geometry and between centrifuges of substantially different geometry are discussed.
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  • 32
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    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 261-271 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: During the biosynthetic production of chlortetracycline on a medium with sucrose, soy meal, corn steep extract, sodium chloride, ammonium sulphate, calcium carbonate and beet molasses, the amount of nucleic acids synthesized by the culture and the maximum respiration of the culture is determined by the amount of inorganic phosphate in the original medium. Chlortetracycline production does not start until all the inorganic phosphate has been consumed. The adverse influence of increased amounts of inorganic phosphate upon production of chlortetracycline is more apparent in flasks on a shaking machine than in agitated and aerated fermentation tanks with higher oxygen transfer numbers.
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  • 33
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 297-302 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A simple, rugged and compact automatic feed control attachment for the laboratory-size glass circulating evaporator has been designed and constructed. Experience has demonstrated that this apparatus operates satisfactorily with a variety of aqueous biological extracts and solutions having resistivity values of 50,000 ohm-in. or less. The device in adaptable to other evaporators and stills.
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  • 34
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 303-309 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: A description of the cultivation of Rhodospirillum rubrum in 1,000 and 3,000 l. fermentors fitted with a special illumination device, and a discussion of the results.
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  • 35
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959) 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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  • 36
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 311-324 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Novobiocin fermentations in 20 l. baffled fermentors were studied as a function of the size and speed of the dual four-bladed flat-blade turbines used. Power input and sulphite oxidation rate measurements were made. The courses of pH, sugar utilization, mycelial dry weight, carbon dioxide evolution and antibiotic titer were determined. Optimum antibiotic yields were achieved at a power input of 0·5 h.p./100 gal, equivalent to a sulphite oxidation rate of 110 mmoles O2/l.h, when the impeller diameters were 29 per cent or 39 per cent of the tank diameter. A power input of 0·75 h.p./100 gal, equivalent to a sulphite oxidation rate of 160 mmoles O2/l.h, was required for equivalent results with the impeller diameter 49 per cent of the tank diameter. Some explanations of the lack of equivalent results with the large impeller are discussed.
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  • 37
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 325-334 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Probability theory has been applied to the analysis of bacterial distribution within a fibrous air sterilization filter. For a long filter layer, to which the so-called ‘log-penetration’ law is no longer applicable, the probability theory is considered to be effective in interpreting the distribution data.The effects of the diameter, volume fraction and moisture content of the glass-fibre on the longitudinal distribution of bacterial cells, were studied. The distribution was estimated beyond the experimental data points. This estimation will be of use for predicting the ‘life’ of an air sterilization filter.
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  • 38
    Electronic Resource
    Electronic Resource
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Biochemical and Microbiological Technology and Engineering 1 (1959), S. 349-357 
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The equations of Monod that describe the course of bacterial population growth and substrate concentration during continuous culturing are usually analysed with reference to steady-state conditions. These equations are analysed to give information on the course of bacterial population growth from inoculation to the achievement of a steady-state condition. For common values of certain parameters occurring in Monod's development, growth is well approximated by an exponential law (logarithmic phase) which depends on: (a) the maximum specific growth-rate constant for the organism and medium concerned, and (b) the constant dilution rate.
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  • 39
    ISSN: 0368-1467
    Keywords: Chemistry ; Biochemistry and Biotechnology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: The effect of agitation on the rate of acid formation by the microaerophilic organism Lactobacillus delbrueckii was studied. Fermentations were conducted at constant temperature and pH, and with the continuous addition of a nutrilite source. The range of agitator speeds was from 85 to 720 rev/min.The acid formation rate was found to increase with increasing agitator speeds and decrease with decreasing speeds if corn-steep liquor was the nutrilite source. No effect of agitation was observed with yeast extract as the nutrilite source.The data from corn-steep liquor media were found to be consistent with a mass transfer mechanism, but did not warrant a conclusion as to the specific nature of the effect of agitation. It was concluded, however, that the effect of agitation on the acid formation rate was at most very small.
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  • 40
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    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 41
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    Publication Date: 2006-10-26
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  • 42
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    Publication Date: 2006-10-26
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  • 43
    Publication Date: 2006-03-16
    Keywords: AERODYNAMICS
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  • 44
    Publication Date: 2012-05-11
    Keywords: AERODYNAMICS
    Type: RM-2419-NASA , RM-2419-NASA
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  • 45
    Publication Date: 2019-05-11
    Description: A design guide is suggested as a basis for indicating combinations of airplane design variables for which the possibilities of pitch-up are minimized for tail-behind-wing and tailless airplane configurations. The guide specifies wing plan forms that would be expected to show increased tail-off stability with increasing lift and plan forms that show decreased tail-off stability with increasing lift. Boundaries indicating tail-behind-wing positions that should be considered along with given tail-off characteristics also are suggested. An investigation of one possible limitation of the guide with respect to the effects of wing-aspect-ratio variations on the contribution to stability of a high tail has been made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.92. The measured pitching-moment characteristics were found to be consistent with those of the design guide through the lift range for aspect ratios from 3.0 to 2.0. However, a configuration with an aspect ratio of 1.55 failed t o provide the predicted pitch-up warning characterized by sharply increasing stability at the high lifts following the initial stall before pitching up. Thus, it appears that the design guide presented herein might not be applicable when the wing aspect ratios lower than about 2.0.
    Keywords: Aerodynamics
    Type: NASA-TM-X-26
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  • 46
    Publication Date: 2019-05-23
    Description: Wind tunnel data of X-15 and B-52 aircraft models carry loads and mutual interference
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-184
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  • 47
    Publication Date: 2019-05-23
    Description: Wind tunnel tests - effect of wind induced loads on dynamically scaled model of large missile in launching position
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-109
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  • 48
    Publication Date: 2019-05-23
    Description: High subsonic speed of static longitudinal aerodynamic characteristics of delta wing configuration for angle of attack from 0 deg to 90 deg
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-168
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  • 49
    Publication Date: 2019-05-23
    Description: Stability and control of variable sweep wing configuration with outboard wing panels swept back 75 degrees at Mach 2.01
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-32
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  • 50
    Publication Date: 2019-05-23
    Description: Zero angle of attack performance of isentropic spike inlet designed for maximum external compression at hypersonic speed
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-4
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  • 51
    Publication Date: 2019-06-28
    Description: An investigation of some aspects of the sonic boom has been made with the aid of wind-tunnel measurements of the pressure distributions about bodies of various shapes. The tests were made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and at a Reynolds number per foot of 2.5 x 10(exp 6). Measurements of the pressure field were made at orifices in the surface of a boundary-layer bypass plate. The models which represented both fuselage and wing types of thickness distributions were small enough to allow measurements as far away as 8 body lengths or 64 chords. The results are compared with estimates made using existing theory. To the first order, the boom-producing pressure rise across the bow shock is dependent on the longitudinal development of body area and not on local details. Nonaxisymmetrical shapes may be replaced by equivalent bodies of revolution to obtain satisfactory theoretical estimates of the far-field pressures.
    Keywords: Aerodynamics
    Type: NASA-TN-D-161
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  • 52
    Publication Date: 2019-06-28
    Description: Time histories of noise pressures near ground level were measured during flight tests of fighter-type airplanes over fairly flat, partly wooded terrain in the e Mach number range between 1.13 and 1.4 and at altitudes from 25,000 to 45,000 feet. Atmospheric soundings and radar tracking studies were made for correlation with the measured noise data. The measured and calculated values of the pressure rise across the shock wave were generally in good agreement. There is a tendency for the theory to overestimate the pressure at locations remote from the track and to underestimate the pressures for conditions of high tailwind at altitude. The measured values of ground-reflection factor averaged about 1.8 f or the surface tested as compared to a theoretical value of 2.0. P o booms were measured in all cases. The observers also generally reported two booms; although, in some cases, only one boom was reported. The shock-wave noise associated with some of the flight tests was judged to be objectionable by ground observers, and in one case the cracking of a plate-glass store window was correlated in time with the passage of the airplane at an altitude of 25,000 feet.
    Keywords: Aerodynamics
    Type: NASA-TN-D-48
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  • 53
    Publication Date: 2019-05-29
    Description: Transonic wind tunnel study of aerodynamic characteristics of blunt reentry vehicles at varying angles of attack
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-1-21-59L
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  • 54
    Publication Date: 2019-05-30
    Description: Hypersonic flutter tests on rectangular flat-plate models and double-wedge airfoils in helium flow
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-4-8-59L
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  • 55
    Publication Date: 2019-05-23
    Description: Wind tunnel studies at supersonic and transonic speeds to determine aerodynamic characteristics of variable sweep wing aircraft - configuration
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-206
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  • 56
    Publication Date: 2019-05-23
    Description: Mach number and air temperature effect on hypersonic flow over blunt bodies
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-9-58A
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  • 57
    Publication Date: 2019-05-23
    Description: Overall stage and stator blade element performance with straight stator and tilted stator in transonic axial flow compressor stage
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-99
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  • 58
    Publication Date: 2019-05-23
    Description: Pressure measurements in flight over conically cambered delta wing of F-102A aircraft at transonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-48
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  • 59
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    Publication Date: 2019-05-10
    Keywords: AERODYNAMICS
    Type: NASA-CR-50493 , RM-2417-NASA
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  • 60
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    Publication Date: 2019-05-10
    Keywords: AERODYNAMICS
    Type: JPL-170
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  • 61
    Publication Date: 2019-05-29
    Description: Low speed measurements of oscillatory lateral stability derivatives of 60 degree delta wing bomber model
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-13
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  • 62
    Publication Date: 2019-05-30
    Description: Pitch and control stiffness effects on flutter characteristics of all-moveable wing and vertical and horizontal tails on fighter aircraft at supersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-16-58L
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  • 63
    Publication Date: 2019-05-30
    Description: Aerodynamic effects of airfoil thickness on transonic flutter characteristics of swept and unswept wings
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-79
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  • 64
    Publication Date: 2019-05-23
    Description: Effect of forebody strakes on aerodynamic characteristics in sideslip and pitch of hypersonic aircraft configurations
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-116
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  • 65
    Publication Date: 2019-05-23
    Description: Determination of loads due to wing twist at transonic and low supersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-126
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  • 66
    Publication Date: 2019-05-23
    Description: Investigation of amplitude and phase shift of static pressure variations in supersonic diffuser for separate oscillation of spike and bypass
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-10
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  • 67
    Publication Date: 2019-05-23
    Description: Fighter aircraft external stores ejection at transonic and supersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-128
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  • 68
    Publication Date: 2019-05-23
    Description: Aerodynamic characteristics of variable sweep aircraft configurations - low altitude supersonic vehicle
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-142
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  • 69
    Publication Date: 2019-06-28
    Description: A two-blade rotor having a diameter of 4 feet and a solidity of 0.037 was subjected to sharp-edge vertical gusts while being operated at various forward speeds to study the effect of the gusts on the blade periodic bending moments and flapping angles. Variables studied included gust velocity, collective pitch angle, flapping hinge offset, and tip-speed ratio. Dimensionless coefficients are derived for the periodic components of the incremental changes in blade flapping angles and bending moments which arise when a rotor blade penetrates a sharp-edge gust. Mental changes in both the flapping angles and bending moments are essentially proportional to gust velocity, and the coefficients express the ratio of these increments to gust velccity. The results show that the flapping coefficient usually increases with an increase in collective pitch angle, is generally dependent on tip-speed ratio, and is essentially independent of the amount of flapping hinge offset. The bending-moment coefficient is also dependent on collective pitch angle and tip-speed ratio. Expected reductions in bending moments are realized by the use of flapping hinges, and further reductions in bending moments are achieved as the amount of flapping hinge offset is increased. Comparison of the experimental results of this investigation with limited available theoretical results shows substantial agreement but indicates that the assumption that the response of the rotor to a sharp-edge gust is independent of the collective pitch angle prior to gust entry is probably inadequate.
    Keywords: Aerodynamics
    Type: NASA-TN-D-31
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  • 70
    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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  • 71
    Publication Date: 2019-06-27
    Description: Constant chord, trailing edge, control deflection effects on aerodynamic loading characteristics of 60 degree delta wing-body combination at transonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-122
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  • 72
    Publication Date: 2019-06-27
    Description: Wind tunnel determination of supersonic flow properties in vicinity swept, delta, and trapezoidal wing-body combinations
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-64
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  • 73
    Publication Date: 2019-06-27
    Description: Full-scale wind tunnel determination of effect of corrugated canister surface on static aerodynamic characteristics of reentry capsule
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-220
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  • 74
    Publication Date: 2019-06-27
    Description: Pressure distribution on hypersonic glide configuration having 79.5 deg sweepback and 45 deg dihedral at Mach number of 4.95
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-223
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  • 75
    Publication Date: 2019-08-17
    Description: The longitudinal aerodynamic characteristics of a wing-body-horizontal-tail configuration designed for efficient performance at transonic speeds has been investigated at Mach numbers from 0.80 to 1.03 in the Langley 16-foot transonic tunnel. The effect of adding an outboard leading-edge chord-extension to the highly tapered 45 deg. swept wing was also obtained. The average Reynolds number for this investigation was 6.7 x 10(exp 6) based on the wing mean aerodynamic chord. The relatively low tail placement as well as the addition of a chord-extension achieved some alleviation of the pitchup tendencies of the wing-fuselage configuration. The maximum trimmed lift-drag ratio was 16.5 up to a Mach number of 0.9, with the moment center located at the quarter-chord point of the mean aerodynamic chord. For the untrimmed case, the maximum lift-drag ratio was approximately 19.5 up to a Mach number of 0.9.
    Keywords: Aerodynamics
    Type: NASA-TM-X-130
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  • 76
    Publication Date: 2019-08-17
    Description: A diamond wing and body combination was designed to have an area distribution which would result in near optimum zero-lift wave-drag coefficients at a Mach number of 1.00, and decreasing wave-drag coefficient with increasing Mach number up to near sonic leading-edge conditions for the wing. The airfoil section were computed by varying their shape along with the body radii (blending process) to match the selected area distribution and the given plan form. The exposed wing section had an average maximum thickness of about 3 percent of the local chords, and the maximum thickness of the center-line chord was 5.49 percent. The wing had an aspect ratio of 2 and a leading-edge sweep of 45 deg. Test data were obtained throughout the Mach number range from 0.20 to 3.50 at Reynolds numbers based on the mean aerodynamic chord of roughly 6,000,000 to 9,000,000. The zero-lift wave-drag coefficients of the diamond model satisfied the design objectives and were equal to the low values for the Mach number 1.00 equivalent body up to the limit of the transonic tests. From the peak drag coefficient near M = 1.00 there was a gradual decrease in wave-drag coefficient up to M = 1.20. Above sonic leading-edge conditions of the wing there was a rise in the wave-drag coefficient which was attributed in part to the body contouring as well as to the wing geometry. The diamond model had good lift characteristics, in spite of the prediction from low-aspect-ratio theory that the rear half of the diamond wing would carry little lift. The experimental lift-curve slope obtained at supersonic speeds were equal to or greater than the values predicted by linear theory. Similarly the other basic aerodynamic parameters, aerodynamic center position, and maximum lift-drag ratios were satisfactorily predicted at supersonic speeds.
    Keywords: Aerodynamics
    Type: NASA-TM-X-105
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  • 77
    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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  • 78
    Publication Date: 2019-08-17
    Description: An investigation of a model of a standard size body in combination with a representative 45 deg swept-wing-fuselage model has been conducted in the Langley 8-foot transonic pressure tunnel over a Mach number range from 0.80 to 1.43. The body, with a fineness ratio of 8.5, was tested with and without fins, and was pylon-mounted beneath the fuselage or wing. Force measurements were obtained on the wing-fuselage model with and without the body, for an angle-of-attack range from -2 deg to approximately 12 deg and an angle-of-sideslip range from -8 deg to 8 deg. In addition, body loads were measured over the same angle-of-attack and angle-of-sideslip range. The Reynolds number for the investigation, based on the wing mean aerodynamic chord, varied from 1.85 x 10(exp 6) to 2.85 x 10(exp 6). The addition of the body beneath the fuselage or the wing increased the drag coefficient of the complete model over the Mach number range tested. On the basis of the drag increase per body, the under-fuselage position was the more favorable. Furthermore, the bodies tended to increase the lateral stability of the complete model. The variation of body loads with angle of attack for the unfinned bodies was generally small and linear over the Mach number range tested with the addition of fins causing large increases in the rates of change of normal-force coefficient and nose-down pitching-moment coefficient. The variation of body side-force coefficient with sideslip for the unfinned body beneath the fuselage was at least twice as large as the variation of this load for the unfinned body beneath the wing. The addition of fins to the body beneath either the fuselage or the wing approximately doubled the rate of change of body side-force coefficient with sideslip. Furthermore, the variation of body side-force coefficient with sideslip for the body beneath the wing was at least twice as large as the variation of this load with angle of attack.
    Keywords: Aerodynamics
    Type: NASA-MEMO-4-20-59L , L-206
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  • 79
    Publication Date: 2019-08-17
    Description: The linearized theory for heat addition under a wing has been developed to optimize wing geometry, heat addition, and angle of attack. The optimum wing has all of the thickness on the underside of the airfoil, with maximum-thickness point well downstream, has a moderate thickness ratio, and operates at an optimum angle of attack. The heat addition is confined between the fore Mach waves from under the trailing surface of the wing. By linearized theory, a wing at optimum angle of attack may have a range efficiency about twice that of a wing at zero angle of attack. More rigorous calculations using the method of characteristics for particular flow models were made for heating under a flat-plate wing and for several wings with thickness, both with heat additions concentrated near the wing. The more rigorous calculations yield in practical cases efficiencies about half those estimated by linear theory. An analysis indicates that distributing the heat addition between the fore waves from the undertrailing portion of the wing is a way of improving the performance, and further calculations appear desirable. A comparison of the conventional ramjet-plus wing with underwing heat addition when the heat addition is concentrated near the wing shows the ramjet to be superior on a range basis up to Mach number of about B. The heat distribution under the wing and the assumed ramjet and airframe performance may have a marked effect on this conclusion. Underwing heat addition can be useful in providing high-altitude maneuver capability at high flight Mach numbers for an airplane powered by conventional ramjets during cruise.
    Keywords: Aerodynamics
    Type: NASA-MEMO-3-17-59E
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  • 80
    Publication Date: 2019-08-17
    Description: The performance characteristics of several flush and shielded auxiliary exits were investigated at Mach numbers of 1.5 to 2.0, and jet pressure ratios from jet off to 10. The results indicate that the shielded configurations produced better overall performance than the corresponding flush exits over the Mach-number and pressure-ratio ranges investigated. Furthermore, the full-length shielded exit was highest in performance of all the configurations. The flat-exit nozzle block provided considerably improved performance compared with the curved-exit nozzle block.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-18-59E , E-139
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  • 81
    facet.materialart.
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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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  • 82
    Publication Date: 2019-08-17
    Description: Two methods for reducing the external cowl angle, and hence the cowl pressure drag, were investigated on a two-dimensional model. One method used at both on- and off-design Mach numbers was the addition of a cowl visor that had the inner surface parallel to the free stream at 0 deg angle of attack. The other method investigated consisted in replacing the original cowl by a flatter cowl that also provided internal contraction. Both the visor and the internal-contraction cowl reduced the cowl pressure drag 64 percent or more. The visor had little effect on inlet performance at the design Mach number except to reduce the stability range slightly. At off-design, the visor caused an increase in critical pressure recovery.
    Keywords: Aerodynamics
    Type: NASA-MEMO-3-18-59E , E-173
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  • 83
    Publication Date: 2019-08-17
    Description: A compilation of charts of the induced velocities near a lifting rotor is presented. The charts cover uniform as well as various non-uniform distributions of disk loading and should be applicable to many aerodynamic interference problems involving rotors.
    Keywords: Aerodynamics
    Type: NASA-MEMO-4-15-59L
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  • 84
    Publication Date: 2019-08-17
    Description: Semispan-wing models were tested at angles of attack from 0 to 180 deg at low subsonic speeds. Eight plan forms were considered, both swept and unswept with aspect ratios ranging from 2 to 6. Except for a delta-wing model of aspect ratio 2. all models had a taper ratio of 0.5 and an NACA 64AO10 airfoil section. The delta-wing model had an NACA 0005 (modified) airfoil section. With two exceptions, the models were tested both with and without a full-span trailing-edge flap deflected 25 deg. The Reynolds numbers based on the mean aerodynamic chord were between 1.5 and 2.2 million. Lift, drag, and pitching-moment coefficients are presented as functions of angle of attack. Approximate corrections for the effects of blockage were applied to the data.
    Keywords: Aerodynamics
    Type: NASA-MEMO-2-27-59A
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  • 85
    Publication Date: 2019-08-17
    Description: An investigation of the effects of variation of leading-edge sweep and surface inclination on the flow over blunt flat plates was conducted at Mach numbers of 4 and 5.7 at free-stream Reynolds numbers per inch of 6,600 and 20,000, respectively. Surface pressures were measured on a flat plate blunted by a semicylindrical leading edge over a range of sweep angles from 0 deg to 60 deg and a range of surface inclinations from -10 deg to +10 deg. The surface pressures were predicted within an average error of +/- 8 percent by a combination of blast-wave and boundary-layer theory extended herein to include effects of sweep and surface inclination. This combination applied equally well to similar data of other investigations. The local Reynolds number per inch was found to be lower than the free-stream Reynolds number per inch. The reduction in local Reynolds number was mitigated by increasing the sweep of the leading edge. Boundary-layer thickness and shock-wave shape were changed little by the sweep of the leading edge.
    Keywords: Aerodynamics
    Type: NASA-MEMO-12-26-58A
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  • 86
    Publication Date: 2019-08-17
    Description: Pressure distributions obtained in the Langley 8-foot transonic pressure tunnel on a thin, highly tapered, twisted, 450 sweptback wing in combination with a body are presented. The wing has a cubic spanwise twist variation from 0 deg. at 10 percent of the semispan to 60 at the tip. The tip is at a lower angle of attack than the root. Tests were made at stagnation pressures of 1.0 and 0.5 atmosphere, at Mach numbers from 0 0.800 to 1.200, and at angles of attack from -4 deg. to 20 deg.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-12-59L
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  • 87
    Publication Date: 2019-08-17
    Description: Surface pressures were measured over a blunt 60 deg delta wing with extended trailing edge at a Mach number of 5.7, a free-stream Reynolds number of 20,000 per inch, and angles of attack from -10 to +10 deg. Aft of four leading-edge thicknesses the pressure distributions evidenced no appreciable three-dimensional effects and were predicted qualitatively by a method described herein for calculation of pressure distribution in two-dimensional flow. Results of tests performed elsewhere on blunt triangular wings were found to substantiate the near two-dimensionality of the flow and were used to extend the range of applicability of the method of surface pressure predictions to Mach numbers of 11.5 in air and 13.3 in helium.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-12-59A
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  • 88
    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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  • 89
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-08-17
    Description: A review of the physical condition's under which future airplanes will operate has been made and the necessity for considering fatigue in the design has been established. A survey of the literature shows what phases of elevated-temperature fatigue have been investigated. Other studies that would yield data of particular interest to the designer of aircraft structures are indicated.
    Keywords: Aerodynamics
    Type: NASA-MEMO-6-4-59W
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  • 90
    Publication Date: 2019-08-17
    Description: A brief review of airplane altitude errors due to typical pressure installations at the fuselage nose, the wing tip, and the vertical fins is presented. A static-pressure tube designed to compensate for the position errors of fuselage-nose installations in the subsonic speed range is described. This type of tube has an ogival nose shape with the static-pressure orifices located in the low-pressure region near the tip. The results of wind-tunnel tests of these compensated tubes at two distances ahead of a model of an aircraft showed the position errors to be compensated to within 1/2 percent of the static pressure through a Mach number range up to about 1.0. This accuracy of sensing free-stream static pressure was extended up to a Mach number of about 1.15 by use of an orifice arrangement for producing approximate free-stream pressures at supersonic speeds and induced pressures for compensation of error at subsonic speeds.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-10-59L
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  • 91
    Publication Date: 2019-08-17
    Description: An investigation has been conducted on a triangular wing and body combination to determine the effects on the aerodynamic characteristics resulting from deflecting portions of the wing near the tips 900 to the wing surface about streamwise hinge lines. Experimental data were obtained for Mach numbers of 0.70, 1.30, 1.70, and 2.22 and for angles of attack ranging from -5 deg to +18 deg at sideslip angles of 0 deg and 5 deg. The results showed that the aerodynamic center shift experienced by the triangular wing and body combination as the Mach number was increased from subsonic to supersonic could be reduced by about 40 percent by deflecting the outboard 4 percent of the total area of each wing panel. Deflection about the same hinge line of additional inboard surfaces consisting of 2 percent of the total area of each wing panel resulted in a further reduction of the aerodynamic center travel of 10 percent. The resulting reductions in the stability were accompanied by increases in the drag due to lift and, for the case of the configuration with all surfaces deflected, in the minimum drag. The combined effects of reduced stability and increased drag of the untrimmed configuration on the trimmed lift-drag ratios were estimated from an analysis of the cases in which the wing-body combination with or without tips deflected was assumed to be controlled by a canard. The configurations with deflected surfaces had higher trimmed lift-drag ratios than the model with undeflected surfaces at Mach numbers up to about 1.70. Deflecting either the outboard surfaces or all of the surfaces caused the directional stability to be increased by increments that were approximately constant with increasing angle of attack at each Mach number. The effective dihedral was decreased at all angles of attack and Mach numbers when the surfaces were deflected.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-18-59A
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  • 92
    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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  • 93
    Publication Date: 2019-08-17
    Description: An investigation has been conducted to determine the effects of a high positioned horizontal tail on a wing-body configuration having a thin unswept wing of aspect ratio 3.09. Lift and pitching-moment coefficients were obtained for Mach numbers from 0.80 to 1.40 at Reynolds numbers of 1.0 and 1.5 million and for angles of attack to 20 deg. An experimental study of the pitching-moment contribution of the horizontal tail indicated that the marked destabilizing effect of the horizontal tail at high angles of attack for Mach numbers of 0.80 to 1.00 was associated with the formation of completely separated flow on the upper surface of the wing. Computations of the interference effects of the wing-body combination on the tail for Mach numbers of 0.80 and 0.94 and high angles of attack confirmed this conclusion. For a Mach number of 1.40, and high angles of attack, computations disclosed that the destabilizing effect primarily resulted from the trailing vortices of the wing. Two modifications to the basic wing plan form, which consisted of chord extensions, were generally unsuccessful in reducing the destabilizing contributions of the horizontal tail at high angles of attack.
    Keywords: Aerodynamics
    Type: NASA-TM-X-43
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  • 94
    Publication Date: 2019-08-16
    Description: An investigation has been made in the Langley 20-foot free-spinning tunnel on a 1/25-scale dynamic model to determine the spin and recovery characteristics of the Chance Vought F8U-1P airplane. Results indicated that the F8U-IP airplane would have spin-recovery characteristics similar to the XF8U-1 design, a model of which was tested and the results of the tests reported in NACA Research Memorandum SL56L31b. The results indicate that some modification in the design, or some special technique for recovery, is required in order to insure satisfactory recovery from fully developed erect spins. The recommended recovery technique for the F8U-lP will be full rudder reversal and movement of ailerons full with the spin (stick right in a right spin) with full deflection of the wing leading- edge flap. Inverted spins will be difficult to obtain and any inverted spin obtained should be readily terminated by full rudder reversal to oppose the yawing rotation and neutralization of the longitudinal and lateral controls. In an emergency, the same size parachute recommended for the XFBU-1 airplane will be adequate for termination of the spin: a stable parachute 17.7 feet in diameter (projected) with a drag coefficient of 1.14 (based on projected diameter) and a towline length of 36.5 feet.
    Keywords: Aerodynamics
    Type: NASA-TM-SX-196 , L-714 , NASA-AD-3137
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  • 95
    Publication Date: 2019-08-16
    Description: Pressure distributions obtained in the Langley 8-foot transonic pressure tunnel on a thin highly tapered twisted 45 deg sweptback wing-body combination are presented. The wing has a quadratic spanwise twist variation from 0 deg at 10 percent of the semispan to 6 deg at the tip. The tip is at a lower angle of attack than the root. Tests were made at stagnation pressures of both 0.5 and 1.0 atmosphere at Mach numbers from 0.800 to 1.200 through an angle-of-attack range from -4 deg to 20 deg.
    Keywords: Aerodynamics
    Type: NASA-MEMO-2-24-59L , L-207
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  • 96
    Publication Date: 2019-08-16
    Description: Surface pressure measurements were obtained at three chordwise stations on the wings of the X-3 and X-lE airplanes at Mach numbers from 0.73 to 1.13 for the X-3, and from 0.82 to 1.90 for the X-IE. Leading-edge separation is present on the X-3 wing at a Mach number of about 0.73 and an angle of attack of about 6 deg. However., when the Mach number is increased to 0.88, the trailing-edge separation dominates the pressure distribution and no leading-edge separation is visible although it is anticipated at the higher angles of attack shown. Conversely, the X-lE wing shows no indication of leading-edge separation within the scope of this investigation, but an overexpansion immediately behind the leading edge is present at a Mach number of approximately 0.82. Two separate normal shocks are present on the X-3 wing at a Mach number of about 0.88 and at a low angle of attack as an effect of wing geometry. These shocks merge to form a single shock when the angle of attack is increased to about 6 deg. At supersonic speeds the upper-surface expansion on the X-lE wing is limited by the approach of the pressure coefficients to the pressure coefficient for a vacuum.
    Keywords: Aerodynamics
    Type: NASA-MEMO-5-1-59H
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  • 97
    Publication Date: 2019-08-16
    Description: A turbojet-engine-exhaust simulator which utilizes a hydrogen peroxide gas generator has been developed for powered-model testing in wind tunnels with air exchange. Catalytic decomposition of concentrated hydrogen peroxide provides a convenient and easily controlled method of providing a hot jet with characteristics that correspond closely to the jet of a gas turbine engine. The problems associated with simulation of jet exhausts in a transonic wind tunnel which led to the selection of a liquid monopropellant are discussed. The operation of the jet simulator consisting of a thrust balance, gas generator, exit nozzle, and auxiliary control system is described. Static-test data obtained with convergent nozzles are presented and shown to be in good agreement with ideal calculated values.
    Keywords: Aerodynamics
    Type: NASA-MEMO-1-10-59L
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  • 98
    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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  • 99
    Publication Date: 2019-08-15
    Description: An experimental investigation was conducted to determine the effect of moment-of-area-rule modifications on the drag, lift, and pitching-moment characteristics of a wing-body combination with a relatively high aspect-ratio unswept wing. The basic configuration consisted of an aspect-ratio-6 wing with a sharp leading edge and a thickness ratio of 0.06 mounted on a cut-off Sears-Haack body. The model with full moment-of-area-rule modifications had four contoured pods mounted on the wing and indentations in the body to improve the longitudinal distributions of area and moments of area. Also investigated were modifications employing pods and indentations that were only half the size of the full modifications and modifications with partial body indentations. The models were tested at angles of attack from -2 deg to +12 deg at Mach numbers from 0.6 to 1.4. In general, the moment-of-area-rule modifications had a large effect on the drag characteristics of the models but only a small effect on their lift and pitching-moment characteristics. The modifications provided substantial reductions in the zero-lift drag at transonic and low supersonic speeds, but at subsonic speeds the drag was increased. Near Mach number 1.0, the model with full modification provided the greatest reduction in drag, but at the highest test Mach numbers the half modification gave the largest drag reduction. In general, the percent reductions of zero- lift drag obtained with the aspect-ratio-6 wing were as great or greater than those previously obtained with aspect-ratio-3 wings. The effect of the modifications on the drag due to lift was small except at Mach num- bers below 0.9 where the modified models had higher drag-rise factors. Above Mach number 0.9, the modified models had higher lift-drag ratios than the basic model. The modified models also had higher lift curve slopes and generally were slightly more stable than the basic configuration.
    Keywords: Aerodynamics
    Type: NASA-MEMO-2-24-59A , A-145
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  • 100
    Publication Date: 2019-08-15
    Description: Blowing boundary-layer control was applied to the leading- and trailing-edge flaps of a 45 deg sweptback-wing complete model in a full-scale low-speed wind-tunnel study. The principal purpose of the study was to determine the effects of leading-edge flap deflection and boundary-layer control on maximum lift and longitudinal stability. Leading-edge flap deflection alone was sufficient to maintain static longitudinal stability without trailing-edge flaps. However, leading-edge flap blowing was required to maintain longitudinal stability by delaying leading-edge flow separation when trailing-edge flaps were deflected either with or without blowing. Partial-span leading-edge flaps deflected 60 deg with moderate blowing gave the major increase in maximum lift, although higher deflection and additional blowing gave some further increase. Inboard of 0.4 semispan leading-edge flap deflection could be reduced to 40 deg and/or blowing could be omitted with only small loss in maximum lift. Trailing-edge flap lift increments were increased by boundary-layer control for deflections greater than 45 deg. Maximum lift was not increased with deflected trailing-edge flaps with blowing.
    Keywords: Aerodynamics
    Type: NASA-MEMO-1-23-59A
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