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  • Aircraft Stability and Control  (57)
  • Biochemistry and Biotechnology  (39)
  • AERODYNAMICS  (31)
  • 1995-1999
  • 1955-1959  (127)
  • 1925-1929
  • 1959  (127)
Collection
Publisher
Years
  • 1995-1999
  • 1955-1959  (127)
  • 1925-1929
Year
  • 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
    Topics: Biology , Process Engineering, Biotechnology, Nutrition Technology
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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
    Type of Medium: Electronic Resource
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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: 2019-05-23
    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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  • 46
    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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  • 47
    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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  • 48
    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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  • 49
    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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  • 50
    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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  • 51
    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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  • 52
    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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  • 53
    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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  • 54
    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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  • 55
    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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  • 56
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    Publication Date: 2019-05-10
    Keywords: AERODYNAMICS
    Type: NASA-CR-50493 , RM-2417-NASA
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  • 57
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    Publication Date: 2019-05-10
    Keywords: AERODYNAMICS
    Type: JPL-170
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  • 58
    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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  • 59
    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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  • 60
    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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  • 61
    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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  • 62
    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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  • 63
    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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  • 64
    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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  • 65
    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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  • 66
    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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  • 67
    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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  • 68
    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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  • 69
    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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  • 70
    Publication Date: 2019-06-27
    Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L55G06A
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  • 71
    Publication Date: 2019-08-17
    Description: Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tall locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data by empirical correlation or theoretical means in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 10(exp 6) and at Mach numbers less than 0.25.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-49
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  • 72
    Publication Date: 2019-08-17
    Description: Carrier landing-approach studies of a tailless delta-wing fighter airplane disclosed that approach speeds were limited by ability to control altitude and lateral-directional characteristics. More detailed flight studies of the handling-qualities characteristics of the airplane in the carrier-approach configuration documented a number of factors that contributed to the adverse comments on the lateral-directional characteristics. These were: (1) the tendency of the airplane to roll around the highly inclined longitudinal axis, so that significant sideslip angles developed in the roll as a result only of kinematic effects; (2) reduction of the rolling response to the ailerons because of the large dihedral effect in conjunction with the kinematically developed sideslip angles; and (3) the onset of rudder lock at moderate angles of sideslip at the lowest speeds with wing tanks installed. The first two of the factors listed are inseparably identified with this type of configuration which is being considered for many of the newer designs and may, therefore, represent a problem which will be encountered frequently in the future. The results are of added significance in the demonstration of a typical situation in which extraneous factors occupy so much of the pilot's attention that his capability of coping with the problems of precise flight-path control is reduced, and he accordingly demands a greater speed margin above the stall to allow for airspeed fluctuations.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-15-59A
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  • 73
    Publication Date: 2019-08-17
    Description: An investigation has been made to determine the effect of wing fences, fuselage contouring, varying wing sweepback angle from 40 deg. to 45 deg., mounting the horizontal tail on an outboard boom) and wing thickness distribution upon the buffeting response of typical airplane configurations employing sweptback wings of high aspect ratio. The tests were conducted through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million. For the combinations with 40 deg. of sweepback, the addition of multiple wing fences usually decreased the buffeting at moderate and high lift coefficients and reduced the erratic variation of buffet intensities with increasing lift coefficient and Mach number. Fuselage contouring also reduced buffeting but was not as effective as the wing fences. At most Mach numbers, buffeting occurred at higher lift coefficients for the combination with the NACA 64A thickness distributions than for the combination with the NACA four-digit thickness distributions. At high subsonic speeds, heavy buffeting was usually indicated at lift coefficients which were lower than the lift coefficients for static-longitudinal instability. The addition of wing fences improved the pitching-moment characteristics but had little effect on the onset of buffeting. For most test conditions and model configurations, the root-mean- square and the maximum values measured for relative buffeting indicated similar effects and trends; however, the maximum buffeting loads were usually two to three times the root-mean-square intensities.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-23-59A
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  • 74
    Publication Date: 2019-08-17
    Description: A wind-tunnel investigation has been made to determine the aerodynamic characteristics of a 1/4-scale model of a tilt-wing vertical-take-off-and-landing aircraft. The model had two 3-blade single-rotation propellers with hinged (flapping) blades mounted on the wing, which could be tilted from an incidence of 4 deg for forward flight to 86 deg for hovering flight. The investigation included measurements of both the longitudinal and lateral stability and control characteristics in both the normal forward flight and the transition ranges. Tests in the forward-flight condition were made for several values of thrust coefficient, and tests in the transition condition were made at several values of wing incidence with the power varied to cover a range of flight conditions from forward-acceleration (or climb) conditions to deceleration (or descent) conditions The control effectiveness of the all-movable horizontal tail, the ailerons and the differential propeller pitch control was also determined. The data are presented without analysis.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-11-3-58L
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  • 75
    Publication Date: 2019-08-17
    Description: Wind-tunnel measurements were made of the static and dynamic rotary stability derivatives of an airplane model having sweptback wing and tail surfaces. The Mach number range of the tests was from 0.23 to 0.94. The components of the model were tested in various combinations so that the separate contribution to the stability derivatives of the component parts and the interference effects could be determined. Estimates of the dynamic rotary derivatives based on some of the simpler existing procedures which utilize static force data were found to be in reasonable agreement with the experimental results at low angles of attack. The results of the static and dynamic measurements were used to compute the short-period oscillatory characteristics of an airplane geometrically similar to the test model. The results of these calculations are compared with military flying qualities requirements.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-5-16-59A
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  • 76
    Publication Date: 2019-08-17
    Description: An investigation of the use of ballast at the leading edge of a sweptback wing as a flutter fix has been made. The investigation was conducted in the Langley transonic blowdown tunnel with wing models which had an aspect ratio of 4, sweepback of the quarter-chord line of 450, and a taper ratio of 0.2. Four ballast configurations, which included different amounts of ballast distributed at two different span-wise locations, were investigated. Full-span sting-mounted models were employed. Data were obtained over a Mach number range from 0.65 to 1.32. Comparison of the data for the ballasted wings with data for a similar wing without ballast shows that in the often critical Mach number range between 0.85 and 1.05, the dynamic pressure required for flutter is increased by as much as 100 percent due to the addition of about 6 percent of the wing mass as ballast at the leading edge of the outboard sections. Furthermore, there are indications that similar benefits of leading-edge ballast can be obtained at Mach numbers above M = 1.1. Changing the spanwise location of the ballast and increasing the amount of the ballast by a factor of about 2 had very little additional effect on the dynamic pressure required for flutter. The possibility, therefore, exists that the beneficial effects obtained may be accomplished by using less than the minimum of about 6 percent of the wing mass as ballast as investigated in this paper.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-135
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  • 77
    Publication Date: 2019-08-16
    Description: Free-oscillation tests were made in the Langley high-speed 7- by 10-foot tunnel to determine the effects of wing thickness and wing sweep on the hinge-moment and flutter characteristics of a trailing-edge flap-type control. The untapered semispan wings had full-span aspect ratios of 5 and NACA 65A-series airfoil sections. Unswept wings having ratios of wing thickness to chord of 0.04, 0.06, 0.08, and 0.10 were investigated. The swept wings were 6 percent thick and had sweep angles of 30 deg and 45 deg. The full-span flap-type controls had a total chord of 50 percent of the wing chord and were hinged at the 0.765-wing-chord line. Tests were made at zero angle of attack over a Mach number range from 0.60 to 1.02, control oscillation amplitudes up to about 12 deg, and a range of control-reduced frequencies. Static hinge-moment data were also obtained. Results indicate that the control aerodynamic damping for the 4-percent-thick wing-control model was unstable in the Mach number range from 0.92 to 1.02 (maximum for these tests). Increasing the ratio of wing thickness to chord to 0.06, 0.08, and then to 0.10 had a stabilizing effect on the aerodynamic damping in this speed range so that the aerodynamic damping was stable for the 10-percent-thick model at all Mach numbers. The 6-percent-thick unswept-wing-control model generally had unstable aerodynamic damping in the Mach number range from 0.96 to 1.02. Increasing the wing sweep resulted in a general decrease in the stable aerodynamic damping at the lower Mach numbers and in the unstable aerodynamic damping at the higher Mach numbers. The one-degree-of-freedom control-surface flutter which occurred in the transonic Mach number range (0.92 to 1.02) for the 4-, 6-, and 8-percent-thick unswept-wing-control models could be eliminated by further increasing the ratio of thickness to chord to 0.10. Flutter could also be eliminated by increasing the wing sweep angle to either 30 deg or 45 deg. The magnitude of variation in spring moment derivative with Mach number at transonic speeds was decreased by either increasing the ratio of wing thickness to chord or increasing the wing sweep angle.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-123
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  • 78
    Publication Date: 2019-08-16
    Description: An investigation was conducted to obtain the aerodynamic characteristics of a model of a fighter-type airplane embodying partial body indentation. The wing had an aspect ratio of 4, taper ratio of 0.5, 35 deg sweepback of the 0.25-chord line, and a modified NACA 65A006 airfoil section at the root and a modified NACA 65A004 airfoil section at the tip. The fuselage has been indented in the region of the wing in order to obtain a favorable area distribution. The results reported herein consist of the performance and of the static longitudinal and lateral stability and control characteristics of the complete model. The Mach number range extended from 0.60 to 1.13, and the corresponding Reynolds number based on the wing mean aerodynamic chord varied from 1.77 x 10(exp 6) to 2.15 x 10(exp 6). The drag rise for both the cambered leading edge and symmetrical wing sections occurred at a Mach number of 0.95. Certain local modifications to the body which further improved the distribution of cross-sectional area gave additional reductions in drag at a Mach number of 1.00. The basic configuration indicated a mild pitch-up tendency at lift coefficients near 0.70 for the Mach number range from 0.80 to 0.90; however, the pitch-up instability may not be too objectionable on the basis of dynamic-stability considerations. The basic configuration indicated positive directional stability and positive effective dihedral through the angle-of-attack range and Mach number range with the exception of a region of negative effective dihedral at low lifts at Mach numbers of 1.00 and slightly above.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-13-58L , L-476
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  • 79
    Publication Date: 2019-08-16
    Description: An analytical investigation has been carried out to determine the responses of a flicker-type roll control incorporated in a missile which traverses a range of Mach number of 6.3 at an altitude of 82,000 feet to 5.26 at an altitude of 282,000 feet. The missile has 80 deg delta wings in a cruciform arrangement with aerodynamic controls attached to the fuselage near the wing trailing edge and indexed 450 to the wings. Most of the investigation was carried out on an analog computer. Results showed that roll stabilization that may be adequate for many cases can be obtained over the altitude range considered, providing that the rate factor can be changed with altitude. The response would be improved if the control deflection were made larger at the higher altitudes. lag times less than 0.04 second improve the response appreciably. Asymmetries that produce steady rolling moments can be very detrimental to the response in some cases. The wing damping made a negligible contribution to the response.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-23-59L , L-211
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  • 80
    Publication Date: 2019-08-16
    Description: An investigation was made to determine the characteristics of a nonlinear linkage installed in a power control system incorporated in a ground simulator. The nonlinear linkage provided for increased control-stick motion for relatively small simulator response at control motions near neutral. The quality of the control system was rated on the ease and precision with which various tracking tasks were performed by the pilots who operated the simulator. The results obtained with the nonlinear linkage installed in the control system were compared with those obtained by using the normal linear control system. Several combinations of nonlinearity of the linkage were tested for various dynamic characteristics of the simulator. It was found that the pilots were able to track almost as well with the nonlinear linkage installed as with the normal system. All of the pilots were of the opinion, however, that the nonlinearity was an undesirable feature in the control system because of the apparent lack of simulator response through the neutral range of the linkage where relatively large stick deflections could be made with very little simulator motion. The results showed that increased lag between the target and chair position, higher stick-force levels, and uneven stick forces due to the dynamics of the linkage were general characteristics of all the nonlinear linkage conditions tested. It was also found that for cases of low simulator damping, rapid control motions caused considerably higher overshoots when the nonlinear linkage was installed than were obtained for the normal linear control system. These characteristics were considered to be sufficiently undesirable to out-weigh the advantages to be gained from the use of a nonlinear linkage in the control system of an airplane.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-15-59L , L-174
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  • 81
    Publication Date: 2019-08-16
    Description: The possibility of obtaining useful estimates of the static longitudinal stability of aircraft flying at high supersonic Mach numbers at angles of attack between 0 and +/-180 deg is explored. Existing theories, empirical formulas, and graphical procedures are employed to estimate the normal-force and pitching-moment characteristics of an example airplane configuration consisting of an ogive-cylinder body, trapezoidal wing, and cruciform trapezoidal tail. Existing wind-tunnel data for this configuration at a Mach number of 6.86 provide an evaluation of the estimates up to an angle of attack of 35 deg. Evaluation at higher angles of attack is afforded by data obtained from wind-tunnel tests made with the same configuration at angles of attack between 30 and 150 deg at five Mach numbers between 2.5 and 3.55. Over the ranges of Mach numbers and angles of attack investigated, predictions of normal force and center-of-pressure locations for the configuration considered agree well with those obtained experimentally, particularly at the higher Mach numbers.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-1-17-59A
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  • 82
    Publication Date: 2019-08-16
    Description: A wind-tunnel investigation was made at low speed in the Langley stability tunnel in order to determine the effects of fuselage nose length and a canopy on the oscillatory yawing derivatives of a complete swept-wing model configuration. The changes in nose length caused the fuselage fineness ratio to vary from 6.67 to 9.18. Data were obtained at various frequencies and amplitudes for angles of attack from 0 deg. to about 32 deg. Static lateral and longitudinal stability data are also presented.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-1-15-59L
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  • 83
    Publication Date: 2019-08-16
    Description: Results of an investigation of the static longitudinal stability and control characteristics of an aspect-ratio-3.1, unswept wing configuration equipped with an aspect-ratio-4, unswept horizontal tail are presented without analysis for the Mach number range from 0.70 to 2.22. The hinge line of the all-movable horizontal tail was in the extended wing chord plane, 1.66 wing mean aerodynamic chords behind the reference center of moments. The ratio of the area of the exposed horizontal-tail panels to the total area of the wing was 13.3 percent and the ratio of the total areas was 19.9 percent. Data are presented at angles of attack ranging"from -6 deg to +18 deg for the horizontal tail set at angles ranging from +5 deg to -20 deg and for the tail removed.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-6-11-59A
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  • 84
    Publication Date: 2019-08-16
    Description: An experimental investigation has been made to determine the static stability characteristics of three thick wing models with parabolic plan forms at a Mach number of 3.11 for angles of attack from about -6 to 16 deg. The primary variable was aspect ratio, with the plan-form area and the ratio of base height to span kept the same for all three models. All models had stable, linear pitching-moment curves about the quarter chord of the wing mean aerodynamic chord. The model with the lowest aspect ratio attained a maximum untrimmed lift-drag ratio of about 5.0 at an angle of attack of about 8 deg. Increasing the aspect ratio (which was accompanied by an increase in base area because the ratio of the base height to span was kept constant) caused a decrease in maximum lift-drag ratio. All models were directionally stable for the range of angle of attack of the tests. Addition of a vertical tail to the models caused an increase in the directional stability over the angle-of-attack range. In general, the lateral aerodynamic characteristics of the models were not linear functions of angle of attack over any appreciable angle-of-attack range.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-141 , L-597
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  • 85
    Publication Date: 2019-08-16
    Description: An investigation of the static stability characteristics of several hypersonic boost-glide configurations has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 (with Reynolds numbers per foot of 2.90 x 10(exp 6) and 2.41 x 10(exp 6) respectively). This series of configurations consisted of a cone, with and without cruciform fins, a trihedron, two low-aspect-ratio delta wings that differed primarily in cross-sectional shape, and two wing-body configurations. All configurations indicated reasonably linear pitching-, yawing-, and rolling-moment characteristics for angles of attack to at least 12 deg. The maximum lift-drag ratio for the zero-thrust condition (base drag included) was about 3 for the delta-wing configurations and about 4 for the wing-body configurations.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-167
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  • 86
    Publication Date: 2019-08-14
    Description: Results of tests at Mach numbers of 3.0 and 7.3 for possible wing flutter of a series of models of a boost-glide-vehicle wing are presented herein. All of the models were tested at conditions which exceeded the proposed nominal design requirements for the full-scale vehicle; namely, dynamic pressure of 1,000 pounds per square foot at the test Mach numbers. None of the models experienced flutter; therefore, large margins of safety from wing flutter are indicated. However, the effects of body freedoms on the flutter characteristics and local types of flutter were not investigated.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-37 , HQ-E-DAA-TN54209
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  • 87
    Publication Date: 2019-08-15
    Description: The results of several flutter investigations to determine the effects of plan-form variations on the flutter characteristics of thin cantilevered wings at transonic Mach numbers have been reported previously. In the present investigation the data are extended to include a wing having an aspect ratio of 4, 45 of sweepback, and a taper ratio of 0.2. The data were obtained in the Langley transonic blowdown tunnel over a Mach number range from 0.6 to 1.4. The experimental results indicate an abrupt and rather large increase in both a flutter-speed parameter and a flutter-frequency parameter as the Mach number is increased from 1.05 to 1.10. The foregoing is interpreted as indicating a marked change in the flutter mode. Calculated flutter speeds, based on incompressible-flow aerodynamic coefficients, were too high by 20 percent or more throughout the subsonic Mach number range of the investigation. Calculated flutter frequencies were about 7 percent too high at a Mach number of 0.65 and were about 20 percent too high at a Mach number of 0.9. No significant independent effects of thickness were indicated for the plan form investigated as the thickness was changed from 3 to 4 percent chord.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-136
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  • 88
    Publication Date: 2019-08-15
    Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of tail dihedral on lateral control effectiveness of a complete-model configuration having differentially deflected horizontal-tail surfaces. Limited tests were made to determine the lateral characteristics as well as the longitudinal characteristics in sideslip. The wing had an aspect ratio of 3, a taper ratio of 0.14, 28.80 deg sweep of the quarter-chord line with zero sweep at the 80-percent-chord line, and NACA 65A004 airfoil sections. The test Mach number range extended from 0.60 to 0.92. There are only small variations in the roll effectiveness parameter C(sub iota delta) with negative tail dihedral angle. The tail size used on the test model, however, is perhaps inadequate for providing the roll rates specified by current military requirements at subsonic speeds. The lateral aerodynamic characteristics were essentially constant throughout the range of sideslip angle from 12 deg to -12 deg. A general increase in yawing moment was noted with increased negative dihedral throughout the Mach number range.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-1-58L
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  • 89
    Publication Date: 2019-08-15
    Description: Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase against a nonmaneuvering target is presented. Control of the interceptor's flight path is obtained by use of a pitch rate command system. Topics lift, and pitching moment, effects of initial tracking errors, discussion of normal acceleration limited, limitations of control surface rate and deflection, and effects of neglecting forward velocity changes of interceptor during attack phase.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-19
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  • 90
    Publication Date: 2019-08-15
    Description: Normal forces, axial forces, pitching moments, and rolling moments on the model and hinge moments on each of the four control surfaces were measured. Control surfaces were deflected from -35 deg to 15 deg in various combinations to produce pitching, yawing, and rolling moments on the model over a range of angles of attack from -5 deg to 25 deg at roll angles from -135 deg to 45 deg.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-6-6-59A , AF-AM-162 , A-213 , AF-AM-162
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  • 91
    Publication Date: 2019-08-15
    Description: Results of an investigation to determine the static longitudinal stability and control characteristics of an aspect-ratio-2 triangular wing and body configuration equipped with either a canard control, a trailing-edge-flap control, or a cambered forebody are presented without analysis for Mach numbers from 0.70 to 2.22. The canard surface had a triangular plan form and a ratio of exposed area to total wing area of 7.8 percent. The hinge line of the canard was in the extended wing chord plane, 0.83 wing mean aerodynamic chord ahead of the reference center of moments. The trailing-edge controls were constant-chord full-span flaps with exposed area equal to 10.7 percent of the total wing area. The cambered body was a modified Sears-Haack body with camber only ahead of the wing apex. Data are presented for various canard and flap deflections at angles of attack ranging from -6 deg to +18 deg.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-21-59A
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  • 92
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    In:  CASI
    Publication Date: 2019-08-14
    Description: No abstract available
    Keywords: AERODYNAMICS
    Type: MSF-TN-J-13-59 , BAC-7021-3252-002
    Format: text
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  • 93
    Publication Date: 2019-07-10
    Description: The results are presented in the form of preliminary design charts which give a comparison between the dynamic-response factors of the semi-rigid case and the airplane longitudinal short-period case and between the dynamic-response factors of the semi-rigid case and the steady-state value of the airplane longitudinal short-period response. These charts can be used to estimate the first-order effects of the addition of a wing-bending degree of freedom on the short-period dynamic-response factor and on the maximum dynamic-response factor when compared with the steady-state response of the system.
    Keywords: Aircraft Stability and Control
    Type: NASA-TR-R-12
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  • 94
    Publication Date: 2019-08-15
    Description: A 0.10-scale model of a swept-wing fighter airplane was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 to determine the effects of adding underfuselage speed brakes. The results of brief spoiler-aileron lateral control tests also are included. The tests show acceptable trim and drag increments when the speed brakes are installed at the 32-71-inch fuselage station.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-188 , L-381
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  • 95
    Publication Date: 2019-08-15
    Description: Force tests of the static and dynamic lateral stability characteristics of a VTOL airplane having a triangular wing mounted high on the fuselage with a triangular vertical tail on top of the wing and no horizontal tail have been made in the Langley free-flight tunnel. The static lateral stability parameters and the rolling, yawing, and sideslipping dynamic stability derivatives are presented without analysis.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-143 , L-640
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  • 96
    Publication Date: 2019-08-15
    Description: Results of hypersonic flutter tests on some simple models are presented. The models had rectangular plan forms of panel aspect ratio 1.0, no sweepback, and bending-to-torsion frequency ratios of about 1/3. Two airfoil sections were included in the tests; double wedges of 5-, 10-, and 15-percent thickness and flat plates with straight, parallel sides and beveled leading and trailing edges. The models were supported by a cantilevered shaft. The double-wedge wings were tested in helium at a Mach number of 7.2. An effect of airfoil thickness on flutter speed was found, thicker wings requiring more stiffness to avoid flutter. A few tests in air at a Mach number of 6.9 showed the same thickness effect and also indicated that tests in helium would predict conservative flutter boundaries in air. The data in air and helium seemed to be correlated by piston-theory calculations. Piston-theory calculations agreed well with experiment for the thinner models but began to deviate as the thickness parameter MT approached and exceeded 1.0. A few tests on flat-plate models with various elastic-axis locations were made. Piston-theory calculations would not satisfactorily predict the flutter of these models, probably because of their blunt leading edges.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-8-59L , L-199
    Format: text
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  • 97
    Publication Date: 2019-08-15
    Description: An investigation was made at transonic speeds to determine some of the dynamic stability derivatives of a 45 deg. sweptback-wing airplane model. The model was sting mounted and was rigidly forced to perform a single-degree-of-freedom angular oscillation in pitch or yaw of +/- 2 deg. The investigation was made for angles of attack alpha, from -4 deg. to 14 deg. throughout most of the transonic speed range for values of reduced-frequency parameter from 0.015 to 0.040 based on wing mean aerodynamic chord and from 0.04 to 0.14 based on wing span. The results show that reduced frequency had only a small effect on the damping-in-pitch derivative and the oscillatory longitudinal stability derivative for all Mach numbers M and angles of attack with the exception of the values of damping coefficient near M = 1.03 and alpha = 8 deg. to 14 deg. In this region, the damping coefficient changed rapidly with reduced frequency and negative values of damping coefficient were measured at low values of reduced frequency. This abrupt variation of pitch damping with reduced frequency was a characteristic of the complete model or wing-body-vertical-tail combination. The damping-in-pitch derivative varied considerably with alpha and M for the horizontal-tail-on and horizontal-tail-off configurations, and the damping was relatively high at angles of attack corresponding to the onset of pitch-up for both configurations. The damping-in-yaw derivative was generally independent of reduced frequency and M at alpha = -4 deg. to 4 deg. At alpha = 8 deg. to 14 deg., the damping derivative increased with an increase in reduced frequency and alpha for the configurations having the wing, whereas the damping derivative was either independent of or decreased with increase in reduced frequency for the configuration without the wing. The oscillatory directional stability derivative for all configurations generally decreased with an increase in the reduced-frequency parameter, and, in some instances, unstable values were measured for the model configuration with the horizontal tail removed.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-X-39
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  • 98
    Publication Date: 2019-08-15
    Description: An analytical approach is presented which is applicable to the optimization of homing navigation guidance systems which are forced to operate in the presence of radar noise. The two primary objectives are to establish theoretical minimum miss distance performance and a method of synthesizing the optimum control system. The factors considered are: (1) target evasive maneuver, (2) radar glint noise, (3) missile maneuverability, and (4) the inherent time-varying character of the kinematics. Two aspects of the problem are considered. In the first, consideration is given only to minimization of the miss distance. The solution given cannot be achieved in practice because the required accelerations are too large. In the second, results are extended to the practical case where the limited acceleration capabilities of the missile are considered by placing a realistic restriction on the mean-square acceleration so that system operation is confined to the linear range. Although the exact analytical solution of the latter problem does not appear feasible, approximate solutions utilizing time-varying control systems can be found. One of these solutions - a range multiplication type control system - is studied in detail. It is shown that the minimum obtainable miss distance with a realistic restriction on acceleration is close to the absolute minimum for unlimited missile maneuverability. Furthermore, it is shown that there is an equivalence in performance between the homing and beam-rider type guidance systems. Consideration is given to the effect of changes in target acceleration, noise magnitude, and missile acceleration on the minimum miss distance.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-2-13-59A
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  • 99
    Publication Date: 2019-08-15
    Description: An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/30-scale model of the Grumman WF-2 airplane. The effects of control settings and movements upon the erect-spin and recovery characteristics for the flight gross-weight loading with normal center-of-gravity and rearward center-of-gravity positions were determined. For the inverted-spin tests, the flight gross-weight loading with normal center-of-gravity position was used. Brief tests were also made with the radome removed to determine the effect of the radome on the spin and recovery characteristics of the airplane. The results of the tests of the model indicate that erect spins of the airplane in the flight gross-weight loading with the normal (26.3-percent mean aerodynamic chord) center-of-gravity position and with the most rearward (30-percent mean aerodynamic chord) center-of-gravity position possible will be satisfactorily terminated by full rudder reversal to against the spin accompanied by movement of the elevator to at least two-thirds down. With the radome removed, the spin will be steeper and considerably more oscillatory than with the radome on. Recoveries by the preceding technique will be satisfactory. Inverted spins of the airplane will be satisfactorily terminated by full rudder reversal followed by neutralization of the longitudinal and lateral controls.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-4-24-59L , L-326 , NASA-AD-3134
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  • 100
    Publication Date: 2019-08-15
    Description: A wind-tunnel investigation was made of the low-speed characteristics of a canard configuration having triangular wing and canard surfaces with an aspect ratio of 2. The exposed area of the canard was 6.9 percent of the total wing area. The canard hinge line was located at 0.35 of its mean aerodynamic chord and was 0.5 wing mean aerodynamic chord lengths forward of the wing apex. The ground effects, which made the lift more positive and the -Pitching moment more negative at a given angle of attack, were unaffected by the canard. The stability of the model at a constant canard hinge-moment coefficient decreased to 0 near a lift coefficient of 1.0. In addition, the maximum lift coefficient at which the canard could provide balance was decreased by ground effects to less than 1.0 if the moment center was as far forward as 0.21 of the wing mean aerodynamic chord. The relative magnitude of interference effects between the canard and the wing and body is presented.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-3-4-59A
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