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  • Other Sources  (2,980)
  • AERODYNAMICS  (2,968)
  • Korrelationsmethode
  • Animals
  • 1985-1989  (2,967)
  • 1925-1929  (13)
  • 1
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    Korrelation zwischen Getreideernten und Monatssummen der Niederschläge in Baden (1926)
    In:  Diss.; Freiburg
    Details
    Publication Date: 1926
    Description: Abhängigkeit der Getreideerträge von Witterungseinflüssen mithilfe der Korrelationsmethode in 11 orographisch abgegrenzen Gebieten KATASTER-BESCHREIBUNG: Korrelation zwischen der Abweichung vom 11, bzw. 30jährigen monatlichen Mittel (April-Juli) der Niederschläge und dem Ertrag von Getreidearten (Weizen, Dinkel, Roggen, Gerste, Hafer) KATASTER-DETAIL: Nied 〉 (11, bzw. 30jährigen monatlichen Mittel von 1888-1898 und 1888-1917 im Monat Mai, je nach Region 55-158mm), dann höchste Übereinstimmung der Korrelationskoeffienten für die Ertragszunahme über alle Kulturen
    Keywords: Baden ; 1888-1898 und 1888-1917 ; Ertrag ; Getreide ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung
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  • 2
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    Untersuchungen über die Beziehung zwischen Klima und Ernte-Erträgen in Württemberg (1929)
    In:  Diss. Hohenheimm
    Details
    Publication Date: 1929
    Description: Ergebnisse (Rangordungs- und Korrelationsmethode) der Beziehung zwischen Witterung und Ertrag vieler Kulturen eingeteilt nach Monaten KATASTER-BESCHREIBUNG: Einfluss der Temperatur und des Niederschlags auf den Ertrag folgender Kulturpflanzen: Winterweizen, Winterroggen, Dinkel, Sommerweizen, Sommerroggen, Sommergerste, Hafer, Hopfen, Luzerne, Rotklee, Wiesen, Kartoffeln) KATASTER-DETAIL: Delta T (Vegetationszeit) -, dann Ertrag (Winter- und Sommergetreide) +; Delta T (Winter, Juni und Juli) -, dann Ertrag (Sommergetreide) +; Delta Nied (Winter) +, dann Ertrag (Getreide) -; Delta T (September) - und Delta Nied (Vegetationszeit) +, dann Ertrag (Futterpflanzen) +; Details für einzelne Kulturpflanzen: siehe Artikel
    Keywords: Württemberg ; 1899-1913 ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Weizen ; Witterung
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  • 3
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    Beitrag zur Kenntnis der Backqualität einiger Weizensorten unter besonderer Berücksichtigung der Methodik und Ursachen (1929)
    In:  Archiv für Landwirtschaft, A.3: 471-555
    Details
    Publication Date: 1929
    Description: Einfluß der Witterung auf die Qualität von Weizen KATASTER-BESCHREIBUNG: Witterungsverhältnisse der letzten 5 bis höchstens 10 Tage vor der Gelbreife sind von entscheidendem Einfluss, Backqualität nimmt von kontinentalem zum maritimen Klima ab KATASTER-DETAIL: Tmit+, Sonn+, Nied-, dann gute Qualität Nied+, dann Tausendkorngewicht + aber Nied**, dann Tausendkorngewicht - und N-Gehalt +
    Keywords: Mitteldeutschland ; 1900-1925 ; Ertrag ; Korrelationsmethode ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit ; Weizen ; Witterung ; Sonnenscheindauer
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  • 4
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    Landwirtschaftlich-klimatologische Charakteristik Anhalts als Regenschattengebietes des Harzes (1929)
    In:  Buch von: Höhne, E., (1919): Landwirtschaftlich-klimatologische Untersuchung des Gebietes zwiwchen mittlerer Saale und Pleiße und Einteilung in klimatische Unterbezirke auf Grund der Beziehungen zwischen Witterungsfaktoren und Ernteerträgen
    Details
    Publication Date: 1929
    Description: Untersuchung zur Beziehung zwischen Witterungsfaktoren und Ernteerträgen in verschiedenen Untersuchungsgebieten mittels Rangordnungsdifferenzen. Betrachtet wurden die Erträge von Roggen, Winterweizen, Sommergerste, Hafer, Sommerweizen, Zuckerrübe, Kartoffel und Erbse KATASTER-BESCHREIBUNG: Einfluss der Witterung (Niederschlag, Temperatur, Sonnenschein) auf die Erträge KATASTER-DETAIL: Delta Nied (Oktober bis März) -, dann Erträge (Roggen) +; Delta Nied (Januar) -, dann Erträge (Roggen) ++; Delta Nied (Februar) +, dann Erträge (Roggen) +; Delta Nied (Mai) +, dann Erträge (Roggen) +; Delta Nied (Mai) 〉 1,5x Mittel, dann Erträge -; Delta Sonn (Mai, im Bezirk Köthen) +, dann Erträge (Roggen) -; Delta Nied (Januar, März, April) -, dann Erträge (Sommergerste) +; Delta Nied (Februar, Mai bis Ernte) +, dann Erträge (Sommergerste) +; Delta Nied (Mai) +, dann Erträge (Sommergerste) ++; Köthen (Nied 15-30mm im März), (Delta T- im April/Juni, besonders im Mai), dann Winterweizenertrag++ (weitere Informationen zu den weiteren landwirtschaftlicher Kulturpflanzen und Regionen: siehe Artikel)
    Keywords: Sachsen und Thüringen ; 1899-1926 ; Boden ; Ertrag ; Getreide ; Klima ; Korrelationsmethode ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Globalstrahlung ; Hackfrüchte
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  • 5
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    Über Änderungen im Zuckergehalt und Wachstumsgeschindigkeit der Rüben als Folge verschiedener Wasserniederschläge. (1925)
    In:  Zeitschr. Zuckerindus Chechsolovak Republic 49:299-305, 307-312.
    Details
    Publication Date: 1925
    Description: Korrelation von 6200 Proben zum Zuckergehalt (6200 Proben) und der Niederschlagshöhe an verschiedenen Standorten über einen Beobachtungszeitraum von 5 Jahren KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Tschechien ; 1918-23 ; Zuckerrüben ; Korrelationsmethode ; Niederschlag
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  • 6
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    Die Feldberegnung in Mitteldeutschland (1927)
    In:  Arb. deut. Landw. Gesell. 354:66
    Details
    Publication Date: 1927
    Description: Zusammenhang zwischen dem Ertrag von Kartoffeln, Hafer und Luzerne und dem Niederschlag KATASTER-BESCHREIBUNG: Korrelationen zwischen dem Ertrag von Kartoffeln und Hafer und dem jährlichen Niederschlag, bzw. der jährlichen Anzahl nasser Monate (〉50mm pro Monat); stärkerer Zusammenhang mit jährlichem Niederschlag als mit Anzahl nasser Monate und umso schwächer, je niederschlagsreicher das Jahr, am ausgeprägtesten in Mitteldeutschland selbst auf schweren Böden KATASTER-DETAIL:
    Keywords: Mitteldeutschland ; 1904-1914, 1922-1924 ; Kartoffeln ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag
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  • 7
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    The Relationship of Crop Yield and Weather (1928)
    In:  Nature 122:258.
    Details
    Publication Date: 1928
    Description: Berechnung partieller Korrelationskoeffizienten zwischen Temperatur, Niederschlag, Sonnenschein und Feuchte, in einzelnen Monaten KATASTER-BESCHREIBUNG: Erträge sind abhängig von Temperatur, Sonnenscheindauer, Niederschlag und Feuchte in der Zeit von April bis Juli in Norddakota und von April bis September in Ohio KATASTER-DETAIL:
    Keywords: Norddakota und Ohio ; 1920? ; Ertrag ; Korrelationsmethode ; Niederschlag ; Temperatur ; Globalstrahlung
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  • 8
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    Über den Einfluß der Witterungsfaktoren auf die Ernteerträge (1925)
    In:  Kühn-Archiv:53-78.
    Details
    Publication Date: 1925
    Description: Einführung der Rangordnungs- und Korrelationsmethode anhand langjähriger Beobachtungen, Einfluss des Niederschlages und der Temperatur auf den Ertrag von Erbsen, Kartoffeln, Weizen, Hafer und Roggen KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur und Niederschlag) auf den Ertrag KATASTER-DETAIL: Delta T (März und April) + und Delta Nied (März und April) -, dann Erträge (Erbsen) +; Delta T (Mai und Juni) - und Delta Nied (Mai und Juni) +, dann Erträge (Erbse) +; Delta T (Oktober Vorjahr) +, dann Erträge (Kartoffel) +; Delta T (März) + und Delta T (Mai und Juni) -, dann Erträge (Winterweizen) +; Delta Nied (Januar bis März)-, dann Erträge (Hafer) +; Delta Nied (Januar bis März)-, dann Erträge (Winterroggen) +;
    Keywords: Halle ; 1893-25 ; Kartoffeln ; Ertrag ; Fichte ; Hafer ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Roggen ; Temperatur ; Weizen ; Witterung
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  • 9
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    Die Beziehung zwischen Ernte und Witterung in der Landwirtschaft (1925)
    In:  Diss., Göttingen
    Details
    Publication Date: 1925
    Description: Ergebnisse ( Korrelationsmethode) der Bezeihung zwischen Witterung und Ertrag vieler Kulturen eingeteilt nach Monaten KATASTER-BESCHREIBUNG: Beziehungen zwischen Witterung (Temperatur und Niederschlag)und Ernte KATASTER-DETAIL: Delta Nied (erste 10 Blütetage) -, dann Ertrag (Roggen) +; Delta Nied (Beginn der Blüte bis 10 tage nach Ende der Blüte)-, dann Ertrag (Winterweizen) +; Delta Nied (während der 20 Tage nach Beginn der Blüte) -, dann Ertrag (Sommerweizen) +; Delta Tmit (während der 20 Tage nach dem Aufgang) -, dann Ertrag (Hafer) +; Delta Tmin (während der 20 Tage nach dem Aufgang) -, dann Ertrag (Gerste) +; Delta Tmit (während der 20 Tage nach Beginn der Blüte) -, dann Ertrag (Kartoffeln) +; Delta Nied (vom Aufgang bis zum Beginn der Blüte) -, dann Ertrag (Erbsen) +; Delta Nied +, dann Ertrag (Vietsbohnen) +;
    Keywords: Göttingen ; 1901-1922 ; Kartoffeln ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Temperatur ; Weizen ; Witterung ; Erbsen
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  • 10
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    Untersuchungen über Beziehungen zwischen Witterung und Ernteertrag in der Landwirtschaft (1928)
    In:  Diss., Hohenheim.
    Details
    Publication Date: 1928
    Description: Beziehung zwischen Witterung (unterteilt in einzelne Monate) und Ertragshöhe mithilfe der Rangordnungs- und der Korrelationsmethode KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenscheindauer) auf den Ertrag von Winterweizen, Sommerweizen, Sommergerste, Wintergerste, Hafer und Runkelrüben auf dem Versuchsfeld (wasserundurchlässiger Boden) KATASTER-DETAIL: Delta Sonn (Oktober bis November)+, dann Erträge (Winterweizen) +; Delta Sonn (Dezember bis März)+, dann Erträge (Winterweizen) -; Delta Sonn (April) -, dann Erträge (Winterweizen) +; Delta Nied (April) +, dann Erträge (Winterweizen) +; Delta Nied (Mai, Juni und Juli) -, dann Erträge (Winterweizen) +; Delta Nied (August bis Oktober) +, dann Erträge (Winterweizen) +; Delta T (April) -, dann Erträge (Winterweizen) +; (Details sowie Informationen für Sommerweizen, Sommergerste, Wintergerste, Hafer und Runkelrüben siehe Artikel)
    Keywords: Hohenheim (Baden-Württemberg) ; 1914-25 ; Ertrag ; Getreide ; Hafer ; Klima ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Weizen ; Witterung ; Hackfrüchte
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  • 11
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    Die Beziehung zwischen Ernte und Witterung in der Landwirtschaft (1926)
    In:  Landw. Jahrbuch Berlin 63(1):1-81
    Details
    Publication Date: 1926
    Description: Auszug aus der Diss. KATASTER-BESCHREIBUNG: Beziehungen zwischen Witterung (Temperatur und Niederschlag)und Ernte KATASTER-DETAIL:
    Keywords: Göttingen ; 1901-1922 ; Ertrag ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung ; Hackfrüchte ; Erbsen
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  • 12
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    Die "kritischen Zeiten" und das "ökologische Optimum" der Witterungsfaktoren, ein Mittel zur Bestimmung der Ernteertäge (1926)
    In:  Zeitschrift für Acker- und Pflanzenbau 3:330-334.
    Details
    Publication Date: 1926
    Description: Angabe von Niederschlagsmengen und Durchschnittstemperaturen für das ökologische Optimum bestimmter Sorten, kritische Zeiten (vor und nach der Blüte) sind hierfür entscheidend KATASTER-BESCHREIBUNG: Einfluss von Wasser und Wärme, bzw. Niederschlag und Temperatur auf den Ertrag KATASTER-DETAIL: Roggen, Weizen: Delta Nied (Beginn Blütezeit)-, dann Ertrag +; Hafer, Gerste, Kartoffel: Delta T (Beginn der Blüte) -, dann Ertrag +; Bohne: Delta T (gesamte Wachstumszeit)+ und Delta Nied (gesamte Wachstumszeit) +, dann Ertrag +
    Keywords: Göttingen ; 1901-22 ; Kartoffeln ; Ertrag ; Getreide ; Hafer ; Klima ; Korrelationsmethode ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Witterung ; Hackfrüchte ; Erbsen
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  • 13
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    Shuttle Tethered Aerothermodynamics Research Facility (STARFAC) (1986)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Earth's atmosphere from 90 km to 200 km provides the last aerothermodynamics frontier. Present NASA programs which require but also can provide an understanding of the aerodynamics and aerothermodynamics of the free molecule and transition flows that exist at these altitudes are the Aeroassisted OTV, Entry Research Vehicle and the Tethered Satellite. Each of these programs provides a unique opportunity to do flight research in the rarefied upper atmosphere. However, the Tethered Satellite Program provides, because of its capability to obtain global, in-situ, steady state data, the greatest potential to: (1)define the performance of aerodynamic shapes as a function of environmental characteristics (free molecule, transition, slip flow regimes); (2)define the characteristics of the upper atmosphere and the global variability of properties such as composition temperature, pressure and density. Such data are required to accomplish the systematic development and verification of analytical prediction techniques required to support advance configuration designs.
    Keywords: AERODYNAMICS
    Type: NASA, Washington Applications of Tethers in Space: Workshop Proceedings, Vol. 2; p 265-285
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  • 14
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    Nonequilibrium hypersonic aerothermodynamics (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Nonequilibrium phenomena in hypersonic flows are examined on the basis of theoretical models and selected experimental data, in an introduction intended for second-year graduate students of aerospace engineering. Chapters are devoted to the physical nature of gas atoms and molecules, transitions of internal states, the formulation of the master equation of aerothermodynamics, the conservation equations, chemical reactions in CFD, the behavior of air flows in nonequilibrium, experimental aspects of nonequilibrium flow, a review of experimental results, and gas-solid interaction. Diagrams, graphs, and tables of numerical data are provided.
    Keywords: AERODYNAMICS
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  • 15
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    Conservative full-potential model for unsteady transonic rotor flows (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 193-198
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  • 16
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    Numerical modeling of the vortex/airfoil interaction (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A modeling of the vortex-airfoil interaction is presented in which the finite-area of the real vortices is taken into consideration. Two vortex models are used. In the first, a disturbed piece of vorticity layer is simulated by four rows of discrete vortices of small strength. In the second, a number of discrete vortices is arranged within a circle. The first model may simulate a shear layer or a wake, while the second, a well-formed vortex. The method was applied to the calculation of the pressure induced on the surface of the airfoil by the interacting vortex. Both models give similar results. It was found that for large distances of the vortex from the surface of the airfoil, the consideration or not of the finite-area of the vortex is not a significant factor in determining the induced pressure field. However, when the distance of the vortex from the surface is reduced, its shape is distorted and the induced pressure pulses have lower amplitude than the ones induced by an equivalent point vortex. In the limit, where the vortex impinges on the leading edge of the airfoil, it is split into two and the time dependent pressure coefficient takes even negative values at some time intervals.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 5-11
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  • 17
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    Numerical investigation of unsteady inlet flowfields (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 75-81
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  • 18
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    Unsteady transonic flow calculations for wing/fuselage configurations (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 897-903
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  • 19
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    Circulation control airfoils as applied to rotary-wing aircraft (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 865-875
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  • 20
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    Hypersonic merged-layer flow on a sphere (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Thermophysics and Heat Transfer (ISSN 0887-8722); 1; 21-27
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  • 21
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    Transonic separated solutions for an augmentor wing (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 837-842
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  • 22
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    Density stratification effects on wake vortex decay (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 820-824
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  • 23
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    Artificial dissipation models for the Euler equations (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1931-194
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  • 24
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    Steady and unsteady incompressible free-wake analysis (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The flows around highly sweptback wings and bodies of revolution at high angle of attack are described, and inviscid model approximations and mathematical formulation of the problem are given to steady and unsteady incompressible flows. A general presentation of the methods of solution is given, with emphasis on current computational techniques. Detailed descriptions of the nonlinear vortex-lattice and vortex-panel techniques are presented to show how the boundary conditions are enforced using iteration. Typical numerical results are compared with the available experimental data.
    Keywords: AERODYNAMICS
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  • 25
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    Finite difference methods for the solution of unsteady potential flows (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A brief review is presented of various problems which are confronted in the development of an unsteady finite difference potential code. This review is conducted mainly in the context of what is done for a typical small disturbance and full potential methods. The issues discussed include choice of equation, linearization and conservation, differencing schemes, and algorithm development. A number of applications including unsteady three-dimensional rotor calculation, are demonstrated.
    Keywords: AERODYNAMICS
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  • 26
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    Unsteady transonic flows - Introduction, current trends, applications (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The computational treatment of unsteady transonic flows is discussed, reviewing the historical development and current techniques. The fundamental physical principles are outlined; the governing equations are introduced; three-dimensional linearized and two-dimensional linear-perturbation theories in frequency domain are described in detail; and consideration is given to frequency-domain FEMs and time-domain finite-difference and integral-equation methods. Extensive graphs and diagrams are included.
    Keywords: AERODYNAMICS
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  • 27
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    Unsteady subsonic and supersonic flows - Historical review; state of the art (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: This lecture is introductory to the subject of unsteady subsonic and supersonic flows. The primary objective is to present fundamental concepts in order to promote an understanding of the relations between the basic physical problems and their mathematical formulation as well as to establish a common foundation for the more detailed presentations of subsequent lectures in this session. Linearized (small-perturbation) potential flow is emphasized, although needs beyond that limit are indicated. The basic equations, concepts, and procedures common to all the methods are reviewed first, followed by the development, discussion, and status of methods for creating two-dimensional incompressible flow, strip theory, subsonic lifting-surface theory, subsonic/supersonic surface-panel methods, and supersonic lifting-surface theory.
    Keywords: AERODYNAMICS
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  • 28
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    Paneling methods with vorticity effects and corrections for nonlinear compressibility (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The prediction of missile aerodynamic characteristics is presently undertaken through the application of supersonic paneling methods and nonlinear corrections to the prediction of missile aerodynamic characteristics. Attention is given to supersonic panel methods and line-singularity methods for the modeling of axisymmetric bodies, in combination with corrections for nonlinear flow phenomena, which are applied to complete missile, inlets, and wing-body combinations. The LRCDM2 computer program is used as an example of the methods presented.
    Keywords: AERODYNAMICS
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  • 29
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    Vortex cloud model for body vortex shedding and tracking (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The discrete vortex cloud approach models a missile airframe's vortex wake by means that are capable of treating a variety of configurations over a range of flow conditions. Attention is given to the sheets of vorticity formed on the lee side of a missile at moderate angles-of-attack. While three-dimensional attached flow models are used to represent the missile body, two-dimensional, incompressible, separated flow models are used to represent the separated vortex wake. The predicted pressure distribution of the body under the influence of the freestream and the separation vortex wake are used to calculate aerodynamic loads on the body. The separation vortex wake is represented by clouds of discrete vortices in cross flow planes normal to the body axis.
    Keywords: AERODYNAMICS
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    Laser velocimetry for transonic aerodynamics (1986)
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    Publication Date: 2011-08-19
    Description: Applications of laser velocimetry to the measurement of turbulent flow properties of strong transonic viscous-inviscid interactions are reviewed. The data resulting from these studies are then discussed in relation to their importance in the development of improved viscous-flow calculation methods. Also considered are the current limitations of laser velocimetry, the need for further improvements in the method, and potential future applications.
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  • 31
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    Two-dimensional blade-vortex flow visualization investigation (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1468-147
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  • 32
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    Comparison of finite volume flux vector splittings for the Euler equations (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1453-146
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  • 33
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    Spectral methods for modeling supersonic chemically reacting flowfields (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1461-146
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  • 34
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    Computation of sharp-fin-induced shock wave/turbulent boundary-layer interactions (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1433-144
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  • 35
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    Transonic airfoil calculations including wind tunnel wall-interference effects (1986)
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    Publication Date: 2011-08-19
    Description: The results of Reynolds-averaged time-dependent inviscid and turbulent compressible Navier-Stokes computations using the implicit finite-difference approach of Steger (1978), modified by incorporating a pressure boundary condition, (PBC) to account for wall interference are compared with experimental data on a NACA 64A010 airfoil (Johnson and Bachalo, 1980) in graphs and briefly characterized. The computational approach is the same as that used by King and Johnson (1980), but a 137 x 50 mesh is used instead of a 97 x 35 mesh, and special care is taken in resolving the nose, shock, and trailing-edge regions. Imposition of PBC is shown to improve significantly the accuracy of the computations for the flowfield on the upper surface of the airfoil, shifting the shock forward to its experimentally measured position in the case of turbulent flow. The failure of the method, even with PBC, to match the experimental shock location in the case of a flow with a separation bubble is attributed to inadequacies in the algebraic turbulence model employed (Baldwin and Lomax, 1978).
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1378-138
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  • 36
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    Airfoil trailing-edge flow measurements (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1245-125
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  • 37
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    Recent developments in rotary-wing aerodynamic theory (1986)
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    Publication Date: 2011-08-19
    Description: Current progress in the computational analysis of rotary-wing flowfields is surveyed, and some typical results are presented in graphs. Topics examined include potential theory, rotating coordinate systems, lifting-surface theory (moving singularity, fixed wing, and rotary wing), panel methods (surface singularity representations, integral equations, and compressible flows), transonic theory (the small-disturbance equation), wake analysis (hovering rotor-wake models and transonic blade-vortex interaction), limitations on computational aerodynamics, and viscous-flow methods (dynamic-stall theories and lifting-line theory). It is suggested that the present algorithms and advanced computers make it possible to begin working toward the ultimate goal of turbulent Navier-Stokes calculations for an entire rotorcraft.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1219-124
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  • 38
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    Applications of potential theory computations to transonic aeroelasticity (1986)
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    Publication Date: 2011-08-19
    Description: Unsteady aerodynamic and aeroelastic stability calculations based upon transonic small disturbance (TSD) potential theory are presented. Results from the two-dimensional XTRAN2L code and the three-dimensional XTRAN3S code are compared with experiment to demonstrate the ability of TSD codes to treat transonic effects. The necessity of nonisentropic corrections to transonic potential theory is demonstrated. Dynamic computational effects resulting from the choice of grid and boundary conditions are illustrated. Unsteady airloads for a number of parameter variations including airfoil shape and thickness, Mach number, frequency, and amplitude are given. Finally, samples of transonic aeroelastic calculations are given. A key observation is the extent to which unsteady transonic airloads calculated by inviscid potential theory may be treated in a locally linear manner.
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  • 39
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    Algebraic grid generation about wing-fuselage bodies (1986)
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    Publication Date: 2011-08-19
    Description: An algebraic procedure for the generation of boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration is specified by cross sections and mathematically represented by Coons' patches. A configuration is divided into sections so that several grid blocks that either adjoin each other or partially overlap each other can be generated. Each grid has six exterior surfaces that map into a computational cube. Grids are first determined on the six boundary surfaces and then in the interior. Grid curves that are on the surface of the configuration are derived from the intersection of planes with the Coons' patch definition. Single-valued functions relating approximate arc lengths along the grid curves to a computational coordinate define the distribution of grid points. The two-boundary technique and transfinite interpolation are used to determine the boundary surface grids that are not on the configuration, and transfinite interpolation with linear blending functions is used to determine the interior grid.
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  • 40
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    Overview of helicopter wake and airloads technology (1985)
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    Publication Date: 2011-08-19
    Description: An overview of helicopter aerodynamics technology is presented with emphasis on rotor wake and airloads methodology developed at the United Technologies Research Center (UTRC). The evolution over the past twenty years of various levels of computerized wake geometry models at UTRC, such as undistorted wake, prescribed empirical wake, predicted distorted wake, and generalized wake models for the hover and forward flight regimes, is reviewed. The requirement for accurate wake modeling for flow field and airload prediction is demonstrated by comparisons of theoretical and experimental results. These results include blade pressure distributions predicted from a recently developed procedure for including the rotor wake influence in a full potential flow analysis. Predictions of the interactional aerodynamics of various helicopter components (rotor, fuselage, and tail) are also presented. It is concluded that, with advanced computers and the rapidly progressing computational aerodynamics technology, significant progress toward reliable prediction of helicopter airloads is forseeable in the near future.
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  • 41
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    Transient induced drag (1986)
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    Publication Date: 2011-08-19
    Description: In the present treatment of the calculation of forces on a wing that is suddenly brought into motion at a constant speed, attention is given to the unsteady potential's contribution to the force balance. Total bound vorticity is produced at the initial impulse. The results obtained are independent of wing aspect ratio; as time increases, this effect on the drag force becomes smaller as the vortex emanating from the trailing edge is left behind. The second contributor to induced drag is the spanwise vorticity shedding that results from the spanwise load distribution of three-dimensional wings. This contribution grows with time as the length of the wake grows.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1203-120
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  • 42
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    Comparison of various drag coefficient expansions using polynomials and splines (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 23; 259-263
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  • 43
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    Measured and predicted heating distributions for biconics at Mach 10 (1986)
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    Publication Date: 2011-08-19
    Description: Laminar heating distributions have been measured on a 1.9 percent scale model of a generic aeroassisted vehicle taking the shape of a spherically blunted, 13-deg/7-deg biconic whose forecone section is bent upward (by 7 deg) to furnish self-trim capability at a 20-deg angle-of-attack. The results thus obtained were compared with data gathered for a straight biconic. While no Reynolds number effect on heating was noted on the windward side of the forecone, the opposite was true of the leeward side, where a Reynolds number increase caused circumferential flow separation at lower angles of attack. Generally, windward heating was predicted to within 10 percent with a computer code solving the steady, three-dimensional parabolized Navier-Stokes equations.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 23; 251-258
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  • 44
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    Three-dimensional adaptive grid method (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 948-954
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  • 45
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    Application of a supersonic Euler code (SWINT) to wing-body-tail geometries (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 513-519
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  • 46
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    Wake hazard alleviation associated with roll oscillations of wake-generating aircraft (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 484-491
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  • 47
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    Application of optical interferometry in compressible flows (1985)
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    Publication Date: 2011-08-19
    Description: Interferometry methods were applied to the investigation of steady and unsteady flows in large scale transonic wind tunnels. Holographic interferometry was demonstrated to provide reliable flow visualization and quantitative results for a number of two-dimensional flows. These conclusions were based on extensive comparisons with results obtained by other means. Data obtained on a NACA 64A010 airfoil with an oscillating flap installed in the Ames 11-foot transonic tunnel are presented. Interferograms were recorded at a free stream Mach number of 0.8, flap frequency of 30 Hertz and chord Reynolds numbers of 6.6 x 10 to the 6th and 12.3 x 10 to the 6th. The interferometric results were reduced to dynamic surface pressures, Mach contours and wake flow profiles. A new interferometry method that is capable of providing real-time interferometry data is also discussed.
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  • 48
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    Flow field and near and far sound field of a subsonic jet (1986)
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    Publication Date: 2011-08-19
    Description: Flow and sound field data are presented for a 2.54 cm diameter air jet at a Mach number of 0.50 and a Reynolds number of 300,000. Distributions of mean velocity, turbulence intensities, Reynolds stress, spectral components of turbulence as well as of the near field pressure, together with essential characteristics of the far field sound are reported. This detailed set of data for one particular flow, erstwhile unavailable in the literature, is expected to help promoote and calibrate subsonic jet noise theories. 'Source locations' in terms of the turbulence maxima, coupling between the entrainment dynamics and the near pressure field, the sound radiation paths, and the balance in mass, momentum and sound energy fluxes are discussed. The results suggest that the large scale coherent structures of the jet govern the 'source locations' by controlling the turbulence and also strongly influence the near field pressure fluctuations.
    Keywords: AERODYNAMICS
    Type: Journal of Sound and Vibration (ISSN 0022-460X); 106; 1-16
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  • 49
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    Force and pressure study of thick cambered/twisted 58 deg delta wings (1988)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 25; 69-75
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  • 50
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    Progress in analysis and prediction of dynamic stall (1988)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 25; 6-17
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  • 51
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    Theoretical analysis of aircraft afterbody flow (1987)
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    Publication Date: 2011-08-19
    Description: Computational methods solving the thin shear layer formulation of the compressible, Reynolds-averaged Navier-Stokes equations are presently used to investigate the strongly interactive flow field about aircraft afterbodies. Solutions for a variety of axisymmetric afterbody and nozzle geometries are solved by means of a time-dependent implicit numerical algorithm for both subsonic and supersonic external flows, and the results obtained are compared with experimental data. A novel adaptive-grid technique is used to resolve flow regimes having large gradients, as well as to improve the accuracy and efficiency of the computational scheme.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 496-503
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  • 52
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    Efficient self-consistent viscous-inviscid solutions for unsteady transonic flow (1987)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 737-744
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  • 53
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    Application of axisymmetric analog for calculating heating in three-dimensional flows (1987)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 296-302
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  • 54
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    Prospects for destructive self-induced interactions in a vortex pair (1987)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 433-440
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  • 55
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    Influence of forebody cross-sectional shape on wing vortex-burst location (1987)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 645-652
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  • 56
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    Aerothermodynamics of transatmospheric vehicles (1987)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 594-602
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  • 57
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    Vortical flow management techniques (1987)
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    Publication Date: 2011-08-19
    Description: The aerodynamic performance and controllability of advanced, highly maneuverable supersonic aircraft can be enhanced by means of 'vortex management', which refers to the purposeful manipulation and reordering of stable and concentrated vortical structures due to flow separations from highly swept leading edges and slender forebodies at moderate-to-high angles-of-attack. Attention is presently given to a variety of results obtained in the course of experiments on generic research models at NASA Langley, clarifying their underlying aerodynamics and evaluating their performance-improvement potential. The vortex-management concepts discussed encompass aerodynamic compartmentation of highly swept leading edges, vortex lift augmentation and modulation, and forebody vortex manipulation.
    Keywords: AERODYNAMICS
    Type: Progress in Aerospace Sciences (ISSN 0376-0421); 24; 3, 19; 173-224
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    Multitasking the code ARC3D (1986)
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    Publication Date: 2011-08-19
    Description: The CRAY multitasking system was developed in order to utilize all four processors and sharply reduce the wall clock run time. This paper describes the techniques used to modify the computational fluid dynamics code ARC3D for this run and analyzes the achieved speedup. The ARC3D code solves either the Euler or thin-layer N-S equations using an implicit approximate factorization scheme. Results indicate that multitask processing can be used to achieve wall clock speedup factors of over three times, depending on the nature of the program code being used. Multitasking appears to be particularly advantageous for large-memory problems running on multiple CPU computers.
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    Lower-upper implicit scheme for high-speed inlet analysis (1987)
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    Publication Date: 2011-08-19
    Description: (Previously cited in issue 20, p. 2915, Accession no. A86-42687)
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 1052
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  • 60
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    Supersonic full-potential method applied to missile bodies (1986)
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    Publication Date: 2011-08-19
    Description: The NCOREL full-potential method with an entropy correction is presently applied to supersonic missile flowfield problems. After defining the salient characteristics of the method, a combination of linear theory with NCOREL and experimental data is used to isolate the nonlinear features of the supersonic flow so that the influence of geometry and flow conditions on the development of such flow nonlinearities can be appreciated. Comparisons of experimental longitudinal force and moment data with NCOREL and various linear theory predictions are presented for several generic missile airframe configurations of circular and elliptic cross section. The NCOREL code solves the nonconservative full potential equation in a spherical coordinate system; exact boundary conditions are defined on the missile surface.
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  • 61
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    Low aspect ratio wings at high angles of attack (1986)
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    Publication Date: 2011-08-19
    Description: A comprehensive evaluation is made of experimental data compiled to date for the flowfields and aerodynamic forces that occur at high angles of attack for low aspect ratio wings with delta, rectangular, clipped delta, and strake/wing planform geometries. Attention is given to wing leading edge-generated vortex breakdown, aspect ratio and compressibility effects, and strake vortex effects on main wing areas. Although the nonlinear effects created by a wing-body combination significantly alter wing-alone aerodynamics, the wing-alone data presented are vital to the development of prediction methodologies for large angle of attack aerodynamics.
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    Rotor wake characteristics of a transonic axial-flow fan (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1802-181
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  • 63
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    Euler calculations for rotor configurations in unsteady forward flight (1986)
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    Publication Date: 2011-08-19
    Description: A solution procedure is presented for the lifting transonic flow past modern rotor configurations in forward flight. In this procedure, the three-dimensional, unsteady Euler equations are solved in strong conservation form on a body-fitted moving coordinate system. A hybrid procedure of second order spatial accuracy and first order temporal accuracy is used to integrate the governing equations. In lifting flows, the effect of the elements of wake not captured by the computational procedure, and other aeroelastic effects are accounted for as local angle of attack corrections. Detailed comparisons with experimental data are presented for a 1/7 scale model of the Cobra OLS rotor, and for a three-bladed rotor tested in France. Some preliminary results are also presented for a three-dimensional blade vortex interaction problem.
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    A review of current finite difference rotor flow methods (1986)
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    Publication Date: 2011-08-19
    Description: Rotary-wing computational fluid dynamics is reaching a point where many three-dimensional, unsteady, finite-difference codes are becoming available. This paper gives a brief review of five such codes, which treat the small disturbance, conservative and nonconservative full-potential, and Euler flow models. A discussion of the methods of applying these codes to the rotor environment (including wake and trim considerations) is followed by a comparison with various available data. These data include tests of advancing lifting and nonlifting, and hovering model rotors with significant supercritical flow regions. The codes are also compared for computational efficiency.
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    Acoustic propagation using computational fluid dynamics (1986)
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    Publication Date: 2011-08-19
    Description: The propagation characteristics of several helicopter airfoil profiles have been investigated using the transonic small disturbance equation. A test case was performed to generate a moving shock that propagated off the airfoil. Various grids were then examined to determine their ability to accurately capture these propagating shock waves. Finally, the case of airfoil-vortex interactions was thoroughly studied over a wide range of Mach numbers and airfoil shapes with particular emphasis on the transonic regime; this results in a highly conplicated fluctuation of lift, drag, and pitching moment. The calculated acoustic intensity levels, along with the details of the computational flow field, provide new insights into the understanding of transonic airfoil-vortex interactions.
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    Rotor/wing aerodynamic interactions in hover (1986)
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    Publication Date: 2011-08-19
    Description: An experimental and theoretical investigation of rotor/wing aerodynamic interactions in hover is described. The experimental investigation consisted of both a large-scale and small-scale test. A 0.658-scale, V-22 rotor and wing was used in the large-scale test. Wind download, wing surface pressure, rotor performance, and rotor downwash data from the large-scale test are presented. A small-scale experiment was conducted to determine how changes in the rotor/wing geometry affected the aerodynamic interactions. These geometry variations included the distance between the rotor and wing, wing incidence angle, and configurations both with the rotor axis at the tip of the wing (tilt rotor configuration) and with the rotor axis at the center of the wing (compound helicopter oonfiguration). A wing with boundary-layer control was also tested to evaluate the effect of leading and trailing edge upper surface blowing on the wing download. A computationally efficient, semi-empirical theory was developed to predict the download on the wing. Finally, correlations between the theoretical predictions and test data are presented.
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    Active transition fixing and control of the boundary layer in air (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1577-158
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    Comment on 'Convergence characteristics of a vortex-lattice method for nonlinear configuration aerodynamics' (1986)
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    Publication Date: 2011-08-19
    Description: It is proposed that the study of Rusak et al. (1985), which reports numerical modeling sensitivities on longitudinal force/moment properties for a vortex-lattice method incorporating free vortex filaments to represent the leading-edge vortex separation, employs a formula that is strongly affected by the particular points of analysis chosen. This results in a narrowly applicable curve fit, where numerical sensitivities of the theory are inappropriately traded off against physical effects that are not modeled in that theory. Attention is also given to questionable drag estimate computations.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 798
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    Aerodynamic design considerations for efficient high-lift supersonic wings (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 783-788
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  • 70
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    Modeling of turbulent separated flows for aerodynamic applications (1986)
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    Publication Date: 2011-08-19
    Description: Steady, high speed, compressible separated flows modeled through numerical simulations resulting from solutions of the mass-averaged Navier-Stokes equations are reviewed. Emphasis is placed on benchmark flows that represent simplified (but realistic) aerodynamic phenomena. These include impinging shock waves, compression corners, glancing shock waves, trailing edge regions, and supersonic high angle of attack flows. A critical assessment of modeling capabilities is provided by comparing the numerical simulations with experiment. The importance of combining experiment, numerical algorithm, grid, and turbulence model to effectively develop this potentially powerful simulation technique is stressed.
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  • 71
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    Vectorizable multigrid algorithms for transonic-flow calculations (1986)
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    Publication Date: 2011-08-19
    Description: The analysis and the incorporation into a multigrid scheme of several vectorizable algorithms are discussed. von Neumann analyses of vertical-line, horizontal-line, and alternating-direction ZEBRA algorithms were performed; and the results were used to predict their multigrid damping rates. The algorithms were then successfully implemented in a transonic conservative full-potential computer program. The convergence acceleration effect of multiple grids is shown, and the convergence rates of the vectorizable algorithms are compared with those of standard successive-line overrelaxation (SLOR) algorithms.
    Keywords: AERODYNAMICS
    Type: Applied Mathematics and Computation (ISSN 0096-3003); 19; 217-238
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  • 72
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    Impact of airfoil profile on the supersonic aerodynamics of delta wings (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 695-702
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  • 73
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    A comparison of interactive boundary-layer and thin-layer Navier-Stokes procedures (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Numerical procedures for solving the thin-shear-layer Navier-Stokes equations and for the interaction of solutions to inviscid and boundary-layer equations are described and evaluated. To allow appraisal of the numerical and fluid dynamic abilities of the two schemes, they have been applied to one airfoil as a function of angle of attack at two slightly different Reynolds numbers. The NACA 0012 airfoil has been chosen because it allows comparison with measured lift, drag, and moment and with surface-pressure distributions. Calculations have been performed with algebraic eddy-viscosity formulations, and they include consideration of transition. The results are presented in a form that allows easy appraisal of the accuracy of both procedures and of the relative costs. The interactive procedure is computationally efficient but restrictive relative to the thin-layer Navier-Stokes procedure. The latter procedure does a better job of predicting drag than does the former. In both procedures, the location of transition is crucial for accurate or detailed computations, particularly at high angles of attack. When the upstream influence of pressure field through the shear layer is important, the thin-layer Navier-Stokes procedure has an edge over the interactive procedure.
    Keywords: AERODYNAMICS
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  • 74
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    Finite element computations for high speed 30 inviscid flows (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Recent progress in the development of finite element methodology for the prediction of aerothermal loads is described. Three dimensional, inviscid computations are presented, but emphasis is placed on development of an approach extendable to three dimensional viscous flows. Progress in key research areas is described. Initial 30 results from the computational procedure are described.
    Keywords: AERODYNAMICS
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  • 75
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    A simulation of rotor-stator interaction using the Euler equations and patched grids (1986)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
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  • 76
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    Numerical simulation of viscous supersonic flow over a generic fighter configuration (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
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  • 77
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    Computation of turbulent supersonic flows around pointed bodies having crossflow separation (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The numerical method developed by Schiff and Sturek (1980) on the basis of the thin-layer parabolized Navier-Stokes equations of Schiff and Steger (1980) is extended to the case of turbulent supersonic flows on pointed bodies at high angles of attack. The governing equations, the numerical scheme, and modifications to the algebraic eddy-viscosity turbulence model are described; and results for three cones and one ogive-cylinder body (obtained using grids of 50 nonuniformly spaced points in the radial direction between the body and the outer boundary) are presented graphically and compared with published experimental data. The grids employed are found to provide sufficient spatial resolution of the leeward-side vortices; when combined with the modified turbulence model, they are shown to permit accurate treatment of flows with large regions of crossflow separation.
    Keywords: AERODYNAMICS
    Type: Journal of Computational Physics (ISSN 0021-9991); 66; 173-196
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  • 78
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    Real gas effects on the numerical simulation of a hypersonic inlet (1986)
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    Publication Date: 2011-08-19
    Description: The present use of a parabolized Navier-Stokes solver to accurately simulate the flowfield in a supersonic inlet yields good agreement between numerical analysis and experiment for a Mach 7.4 inlet under cruise conditions, with an internal compression ratio of 8. The significance of real gas effects on the performance calculation of a hypersonic inlet is demonstrated, with small changes in the ratio of specific heats resulting in a substantial change in the calculated pitot pressure ratio.
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 2; 381
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  • 79
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    Unsteady transonic flow calculations for interfering lifting surface configurations (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 422-430
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  • 80
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    The aerodynamics of rotor blades with ice shapes accreted in hover and in level flight (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Through a series of flights in artificial clouds, ice accretions on the main rotor of a UH-1H helicopter were documented in detail upon landing by silicone-rubber molds for both hover and level flights. Full scale reproductions of typical accretions in hover were fabricated by means of epoxy castings and used for a wind-tunnel test program. Surface static pressure distributions were recorded and used to evaluate lift and pitching moment increments while drag was determined by wake surveys. For comparison, accreted ice shapes are presented for two level flight cases as well as preliminary analytical predictions.
    Keywords: AERODYNAMICS
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  • 81
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    The mechanisms of determining shock locations in one and two dimensional transonic flows (1986)
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    Publication Date: 2011-08-19
    Description: The mechanism that locates a shock wave in a transonic flow in one and two dimensions is examined. It is found that in one dimension the shock is located by specifying the downstream pressure whereas in two dimensions the shock is located by the application of an entropy condition at the sonic line.
    Keywords: AERODYNAMICS
    Type: ASME, Transactions, Journal of Applied Mechanics (ISSN 0021-8936); 53; 203-205
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  • 82
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    Unsteady transonic flow calculations for two-dimensional canard-wing configurations (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 290-298
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  • 83
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    Three-dimensional inviscid analysis of radial-turbine flow and a limited comparison with experimental data (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The three-dimensional inviscid DENTON code is used to analyze flow through a radial-inflow turbine rotor. Experimental data from the rotor are compared with analytical results obtained by using the code. The experimental data available for comparison are the radial distributions of circumferentially averaged values of absolute flow angle and total pressure downstream of the rotor exit. The computed rotor-exit flow angles are generally underturned relative to the experimental values, which reflect the boundary-layer separation at the trailing edge and the development of wakes downstream of the rotor. The experimental rotor is designed for a higher-than-optimum work factor of 1.126 resulting in a nonoptimum positive incidence and causing a region of rapid flow adjustment and large velocity gradients. For this experimental rotor, the computed radial distribution of rotor-exit to turbine-inlet total pressure ratios are underpredicted due to the errors in the finite-difference approximations in the regions of rapid flow adjustment, and due to using the relatively coarser grids in the middle of the blade region where the flow passage is highly three-dimensional. Additional results obtained from the three-dimensional inviscid computation are also presented, but without comparison due to the lack of experimental data. These include quasi-secondary velocity vectors on cross-channel surfaces, velocity components on the meridional and blade-to-blade surfaces, and blade surface loading diagrams. Computed results show the evolution of a passage vortex and large streamline deviations from the computational streamwise grid lines. Experience gained from applying the code to a radial turbine geometry is also discussed.
    Keywords: AERODYNAMICS
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  • 84
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    An attached flow design of a noninterfering leading-edge extension to a thick delta wing (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 237-243
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  • 85
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    Transonic, turbulent boundary-layer separation generated on an axisymmetric flow model (1986)
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    Publication Date: 2011-08-19
    Description: Experimental data describing the transonic, turbulent, separated flow generated by an axisymmetric flow model are presented. The model consisted of a circular-arc bump affixed to a straight, circular cylinder aligned with the flow direction. Measurements of the mean velocity, turbulence intensity, and Reynolds shear-stress profiles were made in the separated flow. These data revealed dramatic changes in the shear-stress levels as the flow passed through the interaction to reattachment. Behavior of the turbulence reaction to the imposed pressure gradients was examined in terms of the mixing length and the excursions of the turbulence from equilibrium.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 437-443
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  • 86
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    A three-dimensional incompressible Navier-Stokes flow solver using primitive variables (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 390-396
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  • 87
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    Finite-difference computations of rotor loads (1985)
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    Publication Date: 2011-08-19
    Description: This paper demonstrates the current and future potential of finite-difference methods for solving real rotor problems which now rely largely on empiricism. The demonstration consists of a simple means of combining existing finite-difference, integral, and comprehensive loads codes to predict real transonic rotor flows. These computations are performed for hover and high-advance-ratio flight. Comparisons are made with experimental pressure data.
    Keywords: AERODYNAMICS
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  • 88
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    Calculation of external-internal flow fields for mixed-compression inlets (1987)
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    Publication Date: 2011-08-19
    Description: Supersonic inlet flows with mixed external-internal compressions were computed using a combined implicit-explicit (Beam-Warming-Steger/MacCormack) method for solving the three-dimensional unsteady, compressible Navier-Stokes equations in conservation form. Numerical calculations were made of various flows related to such inlet operations as the shock-wave intersections, subsonic spillage around the cowl lip, and inlet started versus unstarted conditions. Some of the computed results were compared with wind tunnel data.
    Keywords: AERODYNAMICS
    Type: Computer Methods in Applied Mechanics and Engineering (ISSN 0045-7825); 64; 21-37
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  • 89
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    Two-component LDV investigation of three-dimensional shock/turbulent boundary-layer interactions (1988)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 26; 52-56
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  • 90
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    Some effects of interference flowfields on supersonic configurations (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 880-885
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  • 91
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    Supersonic airfoil optimization (1987)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 873-879
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  • 92
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    Algebraic grid generation about wing-fuselage bodies (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An algebraic procedure for generating boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration consists of two aircraft components specified by cross sections and mathematically represented by Coons' patches. Several grid blocks are constructed to cover the entire region surrounding the configuration, and each grid block maps into a computational cube. Grid points are first determined on the six boundary surfaces of a block and then in the interior. Grid points on the surface of the configuration are derived from the intersection of planes with the Coons' patch definition. Approximate arc length distributions along the resulting grid curves concentrate and disperse grid points. The two-boundary technique and transfinite interpolation are used to determine grid points on the remaining boundary surfaces and block interiors.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 868-872
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  • 93
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    Planform effects for low-fineness-ratio multibody configurations at supersonic speeds (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 856-860
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  • 94
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    Improved finite-difference schemes for transonic potential flow calculations (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 1456-146
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  • 95
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    Vortex simulation of forced/unforced mixing layers (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 25; 1417
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  • 96
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    Computed and experimental surface pressure and heating on 70-deg sphere cones (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 385-393
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  • 97
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    Transition on swept leading edges at Mach 3.5 (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 710-717
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  • 98
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    Aerodynamic effects of distributed spanwise blowing on a fighter configuration (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 673-679
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  • 99
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    Transonic region of high dynamic response encountered on an elastic supercritical wing (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 870-875
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  • 100
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    Transonic aeroelasticity of fighter wings with active control surfaces (1989)
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 682-684
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