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  • 1
    Electronic Resource
    Electronic Resource
    Development of an RFLP linkage map in diploid peanut species (1993)
    Springer
    Theoretical and applied genetics 87 (1993), S. 379-384 
    Details
    ISSN: 1432-2242
    Keywords: Arachis hypogaea ; Arachis sp. ; Restriction fragment length polymorphism ; Linkage map
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology
    Notes: Abstract An RFLP linkage map of peanut has been developed for use in genetic studies and breeding programs aimed at improving the cultivated species (Arachis hypogaea L.). An F2 population derived from the interspecific hybridization of two related diploid species in the sectionArachis (A. stenosperma ×A. cardenasii) was used to construct the map. Both random genomic and cDNA clones were used to develop the framework of the map. In addition, three cDNA clones representing genes coding for enzymes involved in the lipid biosynthesis pathway have been mapped in peanut. Of the 100 genomic and 300 cDNA clones evaluated, 15 and 190, respectively, revealed polymorphisms among the parents of our mapping population. Unfortunately, a large number of these produced complex banding patterns that could not be mapped. Of the 132 markers analyzed for segregation, 117 are distributed among 11 linkage groups, while 15 have not yet been associated with any other marker. A total map distance of approximately 1063 cM has been covered to-date.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF01184927
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    Paper (German National Licenses)
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  • 2
    Electronic Resource
    Electronic Resource
    Variation in progenies of an Arachis hypogaea x diploid wild species hybrid (1979)
    Springer
    Euphytica 28 (1979), S. 675-684 
    Details
    ISSN: 1573-5060
    Keywords: Arachis hypogaea ; groundnut ; peanut ; Arachis sp. ; germplasm ; interspecific hybrids ; Cercospora arachidicola ; Cercosporidium ; leafspot ; yield
    Source: Springer Online Journal Archives 1860-2000
    Topics: Agriculture, Forestry, Horticulture, Fishery, Domestic Science, Nutrition
    Notes: Summary Derivatives of a cross between cultivated peanuts, Arachis hypogaea L. (2n=40), and the wild species collection GKP 10017 (2n=20) were compared morphologically, for leafspot resistance and for yield. The objective of the study was to determine the effects of wild species germplasm on the A. hypogaea genome. The sterile F1 hybrid which resulted from crossing the two species was treated with colchicine to restore fertility at the 6x ploidy level. The resulting hexaploid was cytologically unstable and progeny lost chromosomes until stability was regained at the 2n=40 chromosome level. Forty-seven characters were used to analyze the variation among plants in the tetraploid interspecific hybrid population. The plants were compared to four cultivated lines plus GKP 10017. Many hybrids were intermediate to the two parents in morphology. Individual traits such as growth habit, pod and seed size, elongation of the constricted area between pods, nodulation and leaflet size were altered by the presence of GKP 10017 germplasm in many of the hybrid plants. Cercospora arachidicola Hori and Cercosporidium personatum (Berk. & Curt.) Deighton resistances were evaluated for all plants. Several hybrids had few lesions due to either leafspot pathogen. In addition, 24 largeseeded interspecific hybrid selections were compared to the cultivated variety NC 5 for yield. Five selections were superior to both parents at p=0.01. Morphology, disease resistance and yields appeared to be greatly influenced by the wild species GKP 10017 germplasm in plants of the interspecific hybrid population. The potentials of using wild species for improvement of the cultivated peanut are discussed.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00038934
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  • 3
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    Scramjet thrust measurement in a shock tunnel (1995)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: This note reports tests in a shock tunnel in which a fully integrated scramjet configuration produced net thrust. The experiments not only showed that impulse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/sec, and shock tunnels offer a means of generating high Mach number flows at such speeds.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Shock Tunnel Studies of Scramjet Phenomena 1993; p 19-27
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  • 4
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    Thrust measurements of a complete axisymmetric scramjet in an impulse facility (1995)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: This paper describes tests which were conducted in the hypersonic impulse facility T4 on a fully integrated axisymmetric scramjet configuration. In these tests the net force on the scramjet vehicle was measured using a deconvolution force balance. This measurement technique and its application to a complex model such as the scramjet are discussed. Results are presented for the scramjet's aerodynamic drag and the net force on the scramjet when fuel is injected into the combustion chambers. It is shown that a scramjet using a hydrogen-silane fuel produces greater thrust than its aerodynamic drag at flight speeds equivalent to 260 m/s.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Shock Tunnel Studies of Scramjet Phenomena 1993; p 15-18
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  • 5
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    Pressure scaling effects in a scramjet combustion chamber (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The test results obtained for a model scramjet over a range of pressure levels corresponding to different flight altitudes involve enthalpies that vary from the ignition limit, at the low temperature end, to temperatures where the dissociation of combustion products severely limits heat release. The minimum temperature is noted to be highly pressure-sensitive; above the ignition limit, the amount of heat release increased markedly with pressure and with combustion chamber length. A FEM computer code has been used to model the mixing and combustion processes.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 6
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    Hydrogen scramjet with sidewall injection - Shock tunnel simulations (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A free-piston shock tunnel has been used to obtain test data on a scramjet combustion chamber with sidewall injection. The results obtained indicate that combustion was strongly influenced by a region of fuel whose temperature was held below its ignition temperature by wall-cooling effects; this increased the fraction of unburned fuel and resulted in a significant loss of specific impulse. Aerodynamic heating would keep the walls above hydrogen ignition temperature in an actual scramjet powerplant, however. Maximum specific impulse was obtained with a combination of parallel and transverse injection in a long combustion chamber, followed by a dual stage expansion.
    Keywords: AIRCRAFT PROPULSION AND POWER
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  • 7
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    Supersonic combustion ramjet propulsion experiments in a shock tunnel (1995)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Measurements have been made of the propulsive effect of supersonic combustion ramjets incorporated into a simple axisymmetric model in a free piston shock tunnel. The nominal Mach number was 6, and the stagnation enthalpy varied from 2.8 MJ kg(exp -1) to 8.5 MJ kg(exp -1). A mixture of 13 percent silane and 87 percent hydrogen was used as fuel, and experiments were conducted at equivalence ratios up to approximately 0.8. The measurements involved the axial force on the model, and were made using a stress wave force balance, which is a recently developed technique for measuring forces in shock tunnels. A net thrust was experienced up to a stagnation enthalpy of 3.7 MJ kg(exp -1), but as the stagnation enthalpy increased, an increasing net drag was recorded. pitot and static pressure measurements showed that the combustion was supersonic. The results were found to compare satisfactorily with predictions based on established theoretical models, used with some simplifying approximations. The rapid reduction of net thrust with increasing stagnation enthalpy was seen to arise from increasing precombustion temperature, showing the need to control this variable if thrust performance was to be maintained over a range of stagnation enthalpies. Both the inviscid and viscous drag were seen to be relatively insensitive to stagnation enthalpy, with the combustion chambers making a particularly significant contribution to drag. The maximum fuel specific impulse achieved in the experiments was only 175 sec., but the theory indicates that there is considerable scope for improvement on this through aerodynamic design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Shock Tunnel Studies of Scramjet Phenomena 1994; 54 p
    Format: application/pdf
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  • 8
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    Shock tunnel studies of scramjet phenomena (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Commissioning of the new T4 shock tunnel at the University of Queensland implied that it was no longer necessary to focus the work of the research group about an annual test series conducted in the T3 shock tunnel in Canberra. Therefore, it has been possible to organize a group for work to proceed along lines such that particular personnel are associated with particular project areas. The format of this report consists of a series of reports on specific project areas, with a brief general introduction commenting on each report. The introduction is structured by project areas, with the title of the relevant report stated under the project area heading. The reports themselves follow in the order of the project area headings.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-181721 , NAS 1.26:181721
    Format: application/pdf
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  • 9
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    Shock tunnel measurements of heat transfer in a model scramjet (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of heat transfer measurements to the walls of a two dimensional scramjet combustion chamber in a shock tunnel are presented. Thin film heat transfer gauges on a ceramic glass substrate were used. The range of experimental conditions covered produced boundary layers ranging from laminar to transitional, as was independently checked by flow visualization. Empirical flat plate correlations, corrected for local pressure disturbances were used to make a comparison with the experimental results. In the fully laminar regime the heating rates were found to give approximate agreement with the empirical estimates. In the nonlaminar tests the heating rate is found to be well below the fully turbulent levels. It is not known at present if this is a transition effect, or if the pressure corrected flat plate turbulent correlations do not apply to the configuration used.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 85-0908
    Format: text
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  • 10
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    Hypersonic combustion of hydrogen in a shock tunnel (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Results are reported on shock-tunnel experiments testing the feasibility of hypersonic combustion and thrust generation in a hydrogen scramjet model. Tests with a constant-area duct show that hypersonic combustion is possible with a central injection at static intake pressures of about 20 kPa. The results of a comparison made between model configurations with nominal combustion-chamber intake Mach numbers of 4 and 6 indicated that the hypersonic duct gives a better performance at flight enthalpies above 7 mJ/kg. It is argued that the lower temperatures associated with hypersonic flow produce more efficient combustion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: International Symposium on Air Breathing Engines; Sept. 3-8, 1989; Athens; Greece
    Format: text
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