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  • AERODYNAMICS  (12,790)
  • 101
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    Transonic flow past an airfoil with condensation (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: In connection with investigations conducted to determine the influence of water vapor on experiments in wind tunnels, the question arose as to what changes due to vapor condensation might be expected in airfoil measurements. Density measurements on circular-arc airfoils aided by an interferometer in choked tunnels with parallel walls show that increasing humidity produces increasing changes in the flow field. The flow becomes nonstationary at high humidity. At the airfoil, however, the influence of the condensation is only felt, inasmuch as the shock bounding the local supersonic region moves upstream with increasing humidity while its intensity decreases. The density distribution upstream of the shock remains unchanged. Even if the flow becomes nonstationary in the vicinity of the airfoil, no changes occur at the airfoil.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75201
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  • 102
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    Turbulence modeling of shock separated boundary-layer flows (1977)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: Computations of transonic and hypersonic shock-separated boundary-layer flows using zero-equation (algebraic), one-equation (kinetic energy), and two-equation (kinetic energy plus length scale) turbulence eddy viscosity models are described and compared with measurements. The computations make use of a new Navier-Stokes computer algorithm that has reduced computing times by one to two orders of magnitude. The algorithm, and how the turbulence models are incorporated into it, are described. Results for the transonic flow show that the unmodified one-equation model is superior to the zero-equation model in skin-friction predictions. For the hypersonic flow, a highly modified one-equation model that accurately predicts surface pressure and heat transfer is described. Preliminary two-equation model results are also presented.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Apr 18, 1977 - Apr 20, 1977; University Park, PA
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  • 103
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    Computation of unsteady transonic flows by the indicial method (1977)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The indicial method is investigated for the computation of unsteady transonic force and moment coefficients for use in flutter analyses. This approach has the advantage that solutions for all reduced frequencies for a given mode of motion can be obtained from a single finite-difference flowfield computation. Comparisons of indicial and time-integration computations for oscillating airfoil and flap motions help define limits on the motion amplitude for the applicability of the indicial method to transonic flows. Within these limits, solutions for various motion modes can be superposed to obtain solutions for multiple-degree-of-freedom aeroelastic systems. Also, a simple aeroelastic problem is solved by an alternative approach in which the structural motion and flowfield equations are integrated simultaneously using a time-integration finite-difference procedure.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 77-447 , Mar 24, 1977 - Mar 25, 1977|Conference on Structures, Structural Dynamics and Materials; Mar 21, 1977 - Mar 23, 1977; San Diego, CA; US
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  • 104
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    Measurement of unsteady pressures in rotating systems (1978)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: The principles of the experimental determination of unsteady periodic pressure distributions in rotating systems are reported. An indirect method is discussed, and the effects of the centrifugal force and the transmission behavior of the pressure measurement circuit were outlined. The required correction procedures are described and experimentally implemented in a test bench. Results show that the indirect method is suited to the measurement of unsteady nonharmonic pressure distributions in rotating systems.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75445 , DLR-FB-77-34
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  • 105
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    Design of a transonically profiled wing (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The application of well known design concepts with the combined use of thick transonic profiles to aircraft wing design was investigated. Optimization in terms of weight and operational costs was emphasized. It is shown that the usual design criteria and concepts are too restricted and do not sufficiently represent the physical processes over the wing. Suggestions are made for improving this situation, and a design example given. Compared with a wing design according to previously used criteria, the new design is found to be superior in the most important functions. It is concluded that an isobar concept adjusted to the planform in conjunction with an 'organically' designed wing will lead to the weight optimum solutions of wing profiles.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75440 , PAPER-77-026 , Jahrestagung, Deutsche Ges fuer Luft- und Raumfahrt; Sep 13, 1977 - Sep 15, 1977; Berlin
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  • 106
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    Flutter analysis of a glider made of synthetic materials (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A description of the flutter behavior of the Standard Cirrus is given. Steady vibration tests were conducted, and vibration and flutter calculations were made.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75160
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  • 107
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    Aeronautical Engineering: A special bibliography with indexes, supplement 48 (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This special bibliography lists 291 reports, articles, and other documents introduced into the NASA scientific and technical information system in August 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(48)
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  • 108
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    Aeronautical Engineering: A special bibliography with indexes, supplement 47 (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This special bibliography lists 185 reports, articles, and other documents introduced into the NASA scientific and technical information system in July 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(47)
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  • 109
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    Aeronautical engineering: A special bibliography, supplement 45, June 1974 (1974)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 430 reports, articles, and other documents introduced into the NASA scientific and technical information system in May 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(45)
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  • 110
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    Aeronautical engineering: A special bibliography with indexes, supplement 42, March 1974 (1974)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 338 reports, articles, and other documents introduced into the NASA scientific and technical information system in February 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(42)
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  • 111
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    Aeronautical engineering: A special bibliography with indexes, supplement 41, February 1974 (1974)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 514 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1974.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(41)
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  • 112
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    Aeronautical Engineering: A special bibliography with indexes, supplement 37 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 511 reports, articles, and other documents introduced into the NASA scientific and technical information system in October, 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(37)
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  • 113
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    Aeronautical engineerng: A special bibliography with indexes, supplement 36 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 628 reports, articles, and other documents introduced into the NASA scientific and technical information system in September 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(36)
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  • 114
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    Aeronautical engineering: A special bibliography with indexes, supplement 34 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 462 reports, articles, and other documents introduced into the NASA scientific and technical information system in July 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(34)
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  • 115
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    Aeronautical Engineering: A special bibliography, supplement 31, May 1973 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 307 reports, articles, and other documents introduced into the NASA scientific and technical information system in April 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(31)
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  • 116
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    Aeronautical engineering: A special bibliography, supplement 29, March 1973 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 410 reports, articles, and other documents introduced into the NASA scientific and technical information system in February 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(29)
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  • 117
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    Aeronautical Engineering: A special bibliography with indexes, supplement 28, February 1973 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 308 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(28)
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  • 118
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    Aeronautical engineering: A special bibliography with indexes, supplement 26 (1973)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 448 reports, articles, and other documents introduced into the NASA scientific and technical information system in December 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(26)
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  • 119
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    Aeronautical Engineering: A special bibliography with indexes, supplement 22, September 1972 (1972)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 353 reports, articles, and other documents introduced into the NASA scientific and technical information system in August 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(22)
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  • 120
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    Aeronautical engineering: A special bibliography with indexes, supplement 21, August 1972 (1972)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 362 reports, articles, and other documents introduced into the NASA scientific and technical information system in July 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(21)
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  • 121
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    Aeronautical Engineering: A special bibliography with indexes, supplement 19, June 1972 (1972)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 432 reports, articles, and other documents introduced into the NASA scientific and technical information system in May 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(19)
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  • 122
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    A cumulative index to the 1971 issues of Aeronautical Engineering (1972)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This publication is a cumulative index to the abstracts contained in NASA SP-7037 (02) through NASA SP-7037 (13) of Aeronautical Engineering: A Special Bibliography.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(14)
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  • 123
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    Aeronautical Engineering: A special bibliography with indexes, supplement 18, May 1972 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This special bibliography lists 367 reports, articles, and other documents introduced into the NASA scientific and technical information system in April 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(18)
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  • 124
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    Aeronautical Engineering: A special bibliography with indexes, supplement 17 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This special bibliography lists 409 reports, articles, and other documents introduced into NASA scientific and technical information system in March 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(17)
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  • 125
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    Aeronautical Engineering, a special bibliography with indexes, supplement 15 (1972)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This special bibliography lists 363 reports, articles, and other documents introduced into the NASA scientific and technical information system in January 1972. Emphasis is placed on engineering and theoretical aspects for design, construction, evaluation, testing, operation and performance of aircraft (including aircraft engines) and associated components, equipment and systems. Also included are entries on research and development in aeronautics and aerodynamics and research and ground support for aeronautical vehicles.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(15)
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  • 126
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    Aeronautical Engineering: A special bibliography with indexes, supplement 11, November, 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - Nov. 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(11)
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  • 127
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    Aeronautical engineering, a special bibliography, September 1971 (supplement 10) (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This supplement to Aeronautical Engineering-A Special Bibliography (NASA SP-7037) lists 413 reports, journal articles, and other documents originally announced in September 1971 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries in that order. The citations and abstracts are reproduced exactly as they appeared originally in IAA or STAR, including the original accession numbers from the respective announcement journals.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(10)
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  • 128
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    Aeronautical engineering: A special bibliography with indexes (supplement 8) (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - August 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(08)
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  • 129
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    Aeronautical engineering - A special bibliography with indexes /supplement 5/ (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - May 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(05)
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  • 130
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    Status of Passive Inflatable Falling-Sphere Technology for Atmospheric Sensing to 100 Km (1969)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Research and development of falling spheres for meteorological rocket soundings of upper atmosphere
    Keywords: AERODYNAMICS
    Type: NASA-SP-219 , Sep 23, 1969 - Sep 24, 1969; LANGLEY STATION, VA; United States
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  • 131
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    Spatial adaptation of unstructured meshes for unsteady aerodynamic flow computations (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 5 Ma; 1243-125
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  • 132
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    Multipoint inverse airfoil design method based on conformal mapping (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 5 Ma; 1162-117
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  • 133
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    Use of finite volume schemes for transition simulation (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 1122-112
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  • 134
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    Monte Carlo simulation of entry in the Martian atmosphere (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The Direct Simulation Monte Carlo method of Bird is used to investigate the characteristics of low density hypersonic flowfields for typical aerobrakes during Martian atmospheric entry. The method allows for both thermal and chemical nonequilibrium. Results are presented for a sixty-degree spherically blunt cone for various nose radii and altitudes.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0494
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  • 135
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    A comparative study of turbulence models for overset grids (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The implementation of two different types of turbulence models for a flow solver using the Chimera overset grid method is examined. Various turbulence model characteristics, such as length scale determination and transition modeling, are found to have a significant impact on the computed pressure distribution for a multielement airfoil case. No inherent problem is found with using either algebraic or one-equation turbulence models with an overset grid scheme, but simulation of turbulence for multiple-body or complex geometry flows is very difficult regardless of the gridding method. For complex geometry flowfields, modification of the Baldwin-Lomax turbulence model is necessary to select the appropriate length scale in wall-bounded regions. The overset grid approach presents no obstacle to use of a one- or two-equation turbulence model. Both Baldwin-Lomax and Baldwin-Barth models have problems providing accurate eddy viscosity levels for complex multiple-body flowfields such as those involving the Space Shuttle.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0437
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  • 136
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    Calculation of the distributed loads on the blades of individual multiblade propellers in axial flow using linear and nonlinear lifting surface theories (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: In recent years much attention has been given to the development of methods and programs for the calculation of the aerodynamic characteristics of multiblade, saber-shaped air propellers. Most existing methods are based on the theory of lifting lines. Elsewhere, the theory of a lifting surface is used to calculate screw and lifting propellers. In this work, methods of discrete eddies are described for the calculation of the aerodynamic characteristics of propellers using the linear and nonlinear theories of lifting surfaces.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20173 , NAS 1.77:20173 , (ISSN 0321-3429)
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  • 137
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    Aeronautical engineering: A cumulative index to a continuing bibliography (1988)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: This bibliography is a cumulative index to the abstracts contained in NASA SP-7037(210) through NASA SP-7037(221) of Aeronautical Engineering: A Continuing Bibliography. NASA SP-7037 and its supplements have been compiled through the cooperative efforts of the American Institute of Aeronautics and Astronautics (AIAA) and the National Aeronautics and Space Administration (NASA). This cumulative index includes subject, personal author, corporate source, foreign technology, contract number, report number, and accession number indexes.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(222) , NAS 1.21:7037(222)
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  • 138
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    The interference of the model support mast with measurements of the longitudinal and lateral aerodynamic coefficients (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The effects the single-bottom support masts used in the ONERA S1 and S4 wind tunnels have on aerodynamic data collected with scale model aircraft were examined experimentally and analytically. Systematic studies were performed on the flow characteristics around different diameters for the mounts. Scaling methods used to make data from one wind tunnel correspond to data from the other are described. Airbus 320 models were introduced into the tests and mast-body flow interactions were observed. A summary is presented of restrictions on the mast diameters, relative to cylindrical model diameters, which will minimize the effects the masts have on longitudinal and lateral aerodynamic stability data.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20079 , NAS 1.77:20079 , ONERA-TP-1986-181
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  • 139
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    Hypersonic aerodynamic coefficients and convection flow estimation in a HERMES type project (1987)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: An analysis of all the experimental and computation requirements of the HERMES project is presented. The discussion includes the influence of the upper atmosphere composition and possible chemical reactions, the information collected in Orbiter experiments, the possibility of utilizing plasma generators and CF4 in wind tunnel tests, the development of parabolized Navier-Stokes models and solutions, and the computing capacity requirements.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20019 , NAS 1.77:20019
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  • 140
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    Aerodynamics of the Viggen 37 aircraft. Part 1: General characteristics at low speed (1986)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: A description of the aerodynamics of the Viggen 37 and its performances, especially at low speeds is presented. The aerodynamic requirements for the design of the Viggen 37 aircraft are given, including the basic design, performance requirement, and aerodynamic characteristics, static and dynamic load test results and flight test results. The Viggen 37 aircraft is designed to be used for air attack, surveillance, pursuit, and training applications. It is shown that this aircraft is suitable for short runways, and has good maneuvering, acceleration, and climbing characteristics. The design objectives for this aircraft were met by utilizing the effect produced by the interference between two triangular wings, positioned in tandem.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88403 , NAS 1.15:88403
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  • 141
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    Formation of asymmetric separated flow past slender bodies of revolution at large angles of attack (1986)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: The paper examines the problem of determining stationary positions of pairs of vortices of unequal intensity in the flow behind a cylinder modeling the axisymmetric separated flow past a slender body at large angles of attack. The possible asymmetric stationary positions of two vortices are calculated, and their stability with respect to small perturbations is determined. Bifurcations of the flow field with changes in vortex intensity are analyzed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88441 , NAS 1.15:88441 , (ISSN 0321-3249)
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  • 142
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    Mutual effect of thermochemical surface decomposition and viscous interaction during hypersonic flow past a sharp cone (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Numerical results on the hypersonic gas flow in viscous interaction regime past sharp circular cones with thermally destructible Teflon surface are presented. Characteristics of the mutual influence between the thermochemical decomposition of the surface and the viscous interaction are revealed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78015 , NAS 1.15:78015
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  • 143
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    Three-dimensional boundary layer analysis program Blay and its application (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The boundary layer calculation program (BLAY) is a program code which accurately analyzes the three-dimensional boundary layer of a wing with an undefined plane. In comparison with other preexisting programs, the BLAY is characterized by the following: (1) the time required for computation is shorter than any other; (2) the program is adaptable to a parallel processing computer; and (3) the program is associated with a secondary accuracy in the z-direction. As a boundary layer modification to transonic nonviscous flow analysis programs, it is used to adjust viscous and nonviscous interference problems repeatedly. Its efficiency is an important factor in cost reduction in aircraft designing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77962 , NAS 1.15:77962 , Jun 30, 1983 - Jul 01, 1983; Tokyo; Japan
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  • 144
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    Comparison of computational results of a few representative three-dimensional transonic potential flow analysis programs (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The development of transonic aerodynamic computation methods and specific examples, as well as examples of three-dimensional transonic computation in design, are discussed. The case of the transonic transport and the case of the small transport are analyzed. Requirements for programs of the future are itemized.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77963 , NAS 1.15:77963 , Jun 30, 1983 - Jul 01, 1983; Tokyo; Japan
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  • 145
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    NASA's hypersonic fluid and thermal physics program (Aerothermodynamics) (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: This survey paper gives an overview of NASA's hypersonic fluid and thermal physics program (recently renamed aerothermodynamics). The purpose is to present the elements of, example results from, and rationale and projection for this program. The program is based on improving the fundamental understanding of aerodynamic and aerothermodynamic flow phenomena over hypersonic vehicles in the continuum, transitional, and rarefied flow regimes. Vehicle design capabilities, computational fluid dynamics, computational chemistry, turbulence modeling, aerothermal loads, orbiter flight data analysis, orbiter experiments, laser photodiagnostics, and facilities are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0922
    Format: text
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  • 146
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    Deceleration of a supersonic flow behind a curved shock wave with isentropic precompression (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Three-dimensional supersonic flows of an ideal fluid in the neighborhood of bodies formed by being cut out along the streamlines of an axisymmetric flow are investigated. The flow consists of a region of isoentropic compression and a region of vortex flow. An exact solution with variable entropy is used to describe the flow in the vortex region. In the continuous flow region an approximate solution is constructed by expanding the solution in a series in a small parameter. The effect of the shape of the excision and the vorticity of the flow on compression of the jet and and the total pressure loss coefficient is studied.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77920 , NAS 1.15:77920
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  • 147
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    Presentation of the acoustic and aerodynamic results of the Aladin 2 concept qualification testing (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Wind tunnel tests were conducted of a scale model of the Aladin 2 aircraft. The propulsion system configuration is described and the air flow caused by jet ejection is analyzed. Three dimensional flow studies in the vicinity of the engine installation were made. Diagrams of the leading and trailing edge flaps are provided. Graphs are developed to show the aerodynamic performance under conditions of various airspeed and flap deflection.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77883 , NAS 1.15:77883 , CP-143
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  • 148
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    Discussion of the paper, Some Aspects of Propulsion for the Augmenter-Wing Concept, by D. C. Whittley (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Many modern concepts for STOL and V/STOL aircraft rely on integration of the propulsion system with the wing to create favorable lift interactions, and are known as powered lift concepts. A study of powered lift, concerning management and control of the various propulsive streams or jets is presented, each concept having its own particular objectives and requirements. Some specific objectives of this kind are described which relate to the augmentor wing. Consideration is given to three aspects of the subject, namely the augmentor flap itself, the wind ducting and augmentor primary nozzle, and the choice of powerplant or engine cycle. More generally, comments are made regarding noise attenuation and the prospect for achieving a low overall noise level for jet STOL aircraft of the future.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77884 , NAS 1.15:77884
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  • 149
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    Periodic vortex shedding in the supersonic wake of a planar plate (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Vortex sheets in the wake have been mainly studied in incompressible flows and in the transonic region. Heinemann et al. (1976) have shown that for the subsonic region the Strouhal number is nearly independent of the Mach number. Motallebi and Norbury (1981) have observed an increase in the Strouhal number in transonic supersonic flow at Mach numbers up to 1.25. The present investigation is concerned with an extension of the studies of vortex shedding to higher supersonic Mach numbers, taking into account questions regarding the possibility of a generation of stable von Karman vortex paths in the considered Mach number range. It is found that the vortex sheet observed in a supersonic wake behind a rough plate is only stable and reproducible in cases involving a certain surface roughness and certain aspects of trailing edge geometry.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77854 , NAS 1.15:77854
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  • 150
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    Three-dimensional unsteady lifting surface theory in the subsonic range (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The methods of the unsteady lifting surface theory are surveyed. Linearized Euler's equations are simplified by means of a Galileo-Lorentz transformation and a Laplace transformation so that the time and the compressibility of the fluid are limited to two constants. The solutions to this simplified problem are represented as integrals with a differential nucleus; these results in tolerance conditions, for which any exact solution must suffice. It is shown that none of the existing three-dimensional lifting surface theories in subsonic range satisfy these conditions. An oscillating elliptic lifting surface which satisfies the tolerance conditions is calculated through the use of Lame's functions. Numerical examples are calculated for the borderline cases of infinitely stretched elliptic lifting surfaces and of circular lifting surfaces. Out of the harmonic solutions any such temporal changes of the down current are calculated through the use of an inverse Laplace transformation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77812 , NAS 1.15:77812 , European Aeron. Congr.; Sep 25, 1956 - Sep 29, 1956; Scheveningen; Netherlands
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  • 151
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    On the flow processes in sharply inclined and stalled airfoils in parallel movement and rotation (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The purpose of this study is to obtain a deeper insight into the complicated flow processes on airfoils in the region of the buoyancy maxima. To this end calculated and experimental investigations are carried out on a straight stationary, a twisted stationary and a straight rotating rectangular wing. According to the available results the method gives results which can be applied sufficiently for flow applied firmly on all sides for all rotation values. The reliability of the method may be questioned for a flow undergoing transition from the attached to the separated state or for totally separated flow and higher rotation values.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77509 , NAS 1.15:77509
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  • 152
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    A new method of evaluating the side wall interference effect on airfoil angle of attack by suction from the side walls (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A quantitative evaluation method of the suction effect from a suction plate on side walls is explained. It is found from wind tunnel tests that the wall interference is basically described by the summation form of wall interferences in the case of two dimensional flow and the interference of side walls.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77722 , NAS 1.15:77722 , NAL-TR-680
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  • 153
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    A possibility of avoiding surface roughness due to insects (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Discussion of a method for eliminating turbulence caused by the formation of insect roughness upon the leading edges and fuselage, particularly in aircraft using BLC. The proposed technique foresees the use of elastic surfaces on which insect roughness cannot form. The operational characteristics of highly elastic rubber surface fastened to the wing leading edges and fuselage edges are examined. Some preliminary test results are presented. The technique is seen to be advantageous primarily for short-haul operations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77419 , NAS 1.15:77419 , Feb 01, 1963 - Feb 28, 1963; Junin; Argentina
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  • 154
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    Experimental determination of the inertia constants of an airplane or of a missile (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The possibility to measure the inertia constants of an airplane or of a missile by a unique experimental set up without having to materialize axes of rotation was investigated. It is sufficient to suspend the structure appropriately, to obtain the six natural modes determined by the suspension and to introduce these results as data into a computer. If the structure is very flexible it is necessary to take into account the first natural modes of deformation. Experiments on rigid and flexible models led to precise results and allow consideration of full scale measurements. The final goal is to provide, by a standard ground vibration test completed by the measured characteristics of the suspension modes, the set of data necessary for flutter calculations and for the determination of all the inertia constants.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77767 , NAS 1.15:77767
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  • 155
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    Kasprzyk airfoil. The first wind-tunnel tests (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The Kasprzyk slotted flap glider airfoil (the Kasper wing) enabling glider flight at 32 km/h and 0.5 m/sec descent speed was wind tunnel tested in the U.S. The test layout is described and reasons offered for discrepancies between wind tunnel results and Polish in flight data: high induced drag caused by relative size of model wing span and tunnel, by vortex attenuators on the model and their proximity to the tunnel wall, nonsimilarity between flow over a smooth wing and flow over the Kasprzyk wing with bound vortices, obstruction of the tunnel test chamber cross section by the model wing, discrepant Reynolds numbers, and model airfoil aspect ratio much smaller than the prototype. The overall results offer partial confirmation of the Kasprzyk theory, but further in tunnel and in flight studies are recommended.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77757 , NAS 1.15:77757
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  • 156
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    Analysis of airfoil transitional separation bubbles (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A previously developed local inviscid-viscous interaction technique for the analysis of airfoil transitional separation bubbles, ALESEP (Airfoil Leading Edge Separation) has been modified to utilize a more accurate windward finite difference procedure in the reversed flow region, and a natural transition/turbulence model has been incorporated for the prediction of transition within the separation bubble. Numerous calculations and experimental comparisons are presented to demonstrate the effects of the windward differencing scheme and the natural transition/turbulence model. Grid sensitivity and convergence capabilities of this inviscid-viscous interaction technique are briefly addressed. A major contribution of this report is that with the use of windward differencing, a second, counter-rotating eddy has been found to exist in the wall layer of the primary separation bubble.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3791 , NAS 1.26:3791
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  • 157
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    Cold-air performance of compressor-drive turbine of department of energy upgraded automobile gas turbine engine. 3: Performance of redesigned turbine (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The aerodynamic performance of a redesigned compressor drive turbine of the gas turbine engine is determined in air at nominal inlet conditions of 325 K and 0.8 bar absolute. The turbine is designed with a lower flow factor, higher rotor reaction and a redesigned inlet volute compared to the first turbine. Comparisons between this turbine and the originally designed turbine show about 2.3 percentage points improvement in efficiency at the same rotor tip clearance. Two versions of the same rotor are tested: (1) an as cast rotor, and (2) the same rotor with reduced surface roughness. The effect of reducing surface roughness is about one half percentage point improvement in efficiency. Tests made to determine the effect of Reynolds number on the turbine performance show no effect for the range from 100,000 to 500,000.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83627 , E-2044 , DOE/NASA/50194-39 , NAS 1.15:83627 , USAAVSCOM-TR-84-C-7
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  • 158
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    Kinematics, influence functions and field quantities for disturbance propagation from moving disturbance sources (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A unified method is presented for deriving the influence functions of moving singularities which determine the field quantities in aerodynamics and aeroacoustics. The moving singularities comprise volume and surface distributions having arbitrary orientations in space and to the trajectory. Hence one generally valid formula for the influence functions which reveal some universal relationships and remarkable properties in the disturbance fields. The derivations used are completely consistent with the physical processes in the propagation field, such that treatment renders new descriptions for some standard concepts. The treatment is uniformly valid for subsonic and supersonic Mach numbers.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77410 , NAS 1.15:77410 , DFVLR-FB-83-01
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  • 159
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    Reduction of the shock wave intensity by modifying the transonic blade trailing edge (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: It is shown that the shock wave intensity can be decreased by using modified trailing edge configurations to reduce or even completely compensate for the effect of the finite thickness of the trailing edge. A theoretical analysis is presented together with numerical results for two supersonic streams flowing off the trailing edge at different velocities. The analysis is based on an ideal gas model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77029 , NAS 1.15:77029
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  • 160
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    Air intakes for a probative missile of rocket ramjet (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The methods employed to test air intakes for a supersonic guided ramjet powered missile being tested by ONERA are described. Both flight tests and wind tunnel tests were performed on instrumented rockets to verify the designs. Consideration as given to the number of intakes, with the goal of delivering the maximum pressure to the engine. The S2, S4, and S5 wind tunnels were operated at Mach nos. 1.5-3 for the tests, which were compartmentalized into fuselage-intake interaction, optimization of the intake shapes, and the intake performance. Tests were performed on the length and form of the ogive, the presence of grooves, the height of traps in the boundary layer, the types and number of intakes and the lengths and forms of diffusers. Attention was also given to the effects of sideslip, effects of the longitudinal and circumferential positions of the intakes were also examined. Near optimum performance was realized during Mach 2.2 test flights of the prototype rockets.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77407 , NAS 1.15:77407
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  • 161
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    JBFA - buoyant flight (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A method was developed whereby a balloon was used to carry lumber out of a forest in order to continue lumber production without destroying the natural environment and view of the forest. Emphasis was on the best shape for a logging balloon, development of a balloon logging system suitable for cutting lumber and safety plans, tests on balloon construction and development of netting, and weather of mountainous areas, especially solutions to problems caused by winds.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76815 , NAS 1.15:76815
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  • 162
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    Flow mechanism and experimental investigation of a rotating stall in transonic compressors (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The flow characteristics of the rotating stall in compressors is studied, and a flow model is developed along with a theoretical calculation method based on vortex theory. A detailed theoretical calculation is completed for a two dimensional flow field in a transonic rotor in a rotating stall, and the result is in good agreement with experimental findings. The oscillograms of time-varying stall characteristic parameters recorded for the onset, growth, and cessation processes of rotating stall are analyzed, and some new flow phenomena deserving of further investigation are discovered. These include serious separation of individual blades, often preceding the onset of rotating stall in compressors with very small blade-camber angles, and periodical variation of the circumferential width of the stall cell with time, accompanied by periodical oscillation of the width of the stall cell in the radial direction of the blade. The circumferential and radial oscillation frequencies are the same.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77373 , NAS 1.15:77373
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  • 163
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    Wind tunnel investigations of glider fuselages with different waistings and wing arrangements (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The parameters fuselage pinch glider wing arrangement and fuselage leading edge radius of nine glider configurations were investigated in wind tunnel tests. Laminar separation bubbles were found on strongly recessed fuselages. These separations in the juncture between fuselage and wing are essential in the prevention of harmful aerodynamic drag. Drag reduction was measured with increasing pinch and the wing arrangement in the rear. These results are only valid for laminar flow on the fuselage leading edge.
    Keywords: AERODYNAMICS
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  • 164
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    Laminarization of a boundary layer in a supersonic nozzle by cooling of the surface (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The concept of cooling of the surface of wind tunnel walls in order to laminarize the boundary layer, and thereby eliminate perturbations in the working area, is discussed. Equations are given, which are used to calculate the temperature conditions under which the flow in the boundary layer will be stably laminar.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77341 , NAS 1.15:77341
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  • 165
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    Helicopter blade tips (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Methods of improving helicopter performance and vibration level by proper shaping of helicopter blade tips are considered. The principle involved consists of reducing the extent of the supersonic zone above the advancing tip and of the turbulent interaction. For stationary and advancing flight, the influence of the rotor and the problems posed by blade tips are reviewed. The theoretical methods of dealing with the two types of flight are briefly stated, and the experimental apparatus is described, including model triple and quadruple rotors. Different blade tip shapes are shown and briefly discussed. The theoretical results include an advancing speed of 309 km/H and a blade tip rotational speed of 215 m/s. The experimental values are advancing speed of 302 km/h and blade tip Mach number 0.86 for both types of rotors.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77370 , NAS 1.15:77370 , NT-81-19 , Nov 18, 1981 - Nov 20, 1981; Poitiers; France
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  • 166
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    Successive smoothing algorithm for constructing the semiempirical model developed at ONERA to predict unsteady aerodynamic forces (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Unsteady aerodynamic methods adopted for the study of aeroelasticity in helicopters are considered with focus on the development of a semiempirical model of unsteady aerodynamic forces acting on an oscillating profile at high incidence. The successive smoothing algorithm described leads to the model's coefficients in a very satisfactory manner.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76681 , NAS 1.15:76681
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  • 167
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    NASA/HAA Advanced Rotorcraft Technology and Tilt Rotor Workshops. Volume 1: Executive Summary (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This presentation provides an overview of the NASA Rotorcraft Program as an introduction to the technical sessions of the Advanced Rotorcraft Technology Workshop. It deals with the basis for NASA's increasing emphasis on rotorcraft technology, NASA's research capabilities, recent program planning efforts, highlights of its 10-year plan and future directions and opportunities.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84149 , Dec 03, 1980 - Dec 05, 1980; Palo Alto, CA; United States
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  • 168
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    Characteristics of Flow Past Fuselages and Wing-Fuselage Systems of Gliders (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The results are presented for visualization tests and measurements of the velocity field in diffusion regions (with a positive pressure gradient) for fuselages and transition regions between the wing and the fuselage. Wind tunnel and flight tests were performed. Specific emphasis was placed on examining the secondary flow influencing separation acceleration and the influence of the geometrical form of the wing fuselage system manifested by the occurrence of secondary flows of various types.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75401
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  • 169
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    Discussion of test results in the design of laminar airfoils for competition gliders (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The deformation of flow in the boundary layer and the local separation of a laminar layer (laminar bubbles) from various airfoils were investigated. These phenomena were classified and their influence is discussed. Various aerodynamic characteristics are discussed and the principles for prescribing pressure distribution to attain a high value of c sub z max with a possibly low drag coefficient are described.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75402
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  • 170
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    A nonlinear relaxation/quasi-Newton algorithm for the compressible Navier-Stokes equations (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A highly efficient implicit method for the computation of steady, two-dimensional compressible Navier-Stokes flowfields is presented. The discretization of the governing equations is hybrid in nature, with flux-vector splitting utilized in the streamwise direction and central differences with flux-limited artificial dissipation used for the transverse fluxes. Line Jacobi relaxation is used to provide a suitable initial guess for a new nonlinear iteration strategy based on line Gauss-Seidel sweeps. The applicability of quasi-Newton methods as convergence accelerators for this and other line relaxation algorithms is discussed, and efficient implementations of such techniques are presented. Convergence histories and comparisons with experimental data are presented for supersonic flow over a flat plate and for several high-speed compression corner interactions. Results indicate a marked improvement in computational efficiency over more conventional upwind relaxation strategies, particularly for flowfields containing large pockets of streamwise subsonic flow.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2643 , AIAA Applied Aerodynamics Conference; Jun 22, 1992 - Jun 24, 1992; Palo Alto, CA; United States
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  • 171
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    Leading edge sweep effects in generic three-dimensional sidewall compression scramjet inlets (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A computational and experimental study of generic 3D sidewall compression inlets is conducted to examine the effects of fore and aft leading edge sweep on the internal shock structure. Inlets with leading edge sweeps of +30 deg and -30 deg with sidewall compression angles of 6 deg were tested in the NASA Langley Mach 4 air tunnel at a geometric contraction ratio of 1.87. The principal difference in performance was determined to be in the mass capture. Spillage was identified as having two components: a pressure induced component and a sweep induced component. It was found that while the direction of the leading edge sweep had a large influence on the spillage, the pressure effects were more important.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0674
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  • 172
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    Passive control of supersonic cavity flowfields (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A computational investigation has been conducted to study the effect and mechanisms of the passive control of a supersonic flow over a rectangular two-dimensional cavity. The passive control was included through the use of a porous surface over a vent chamber in the floor of the cavity. The passive control effectively suppressed the low-frequency pressure oscillations for the open type cavity, (length-to-depth ratio = 6.0). The mechanism for the suppression was observed to be the stabilization of the motion of the free shear layer. For the closed type cavity flow, (length-to-depth ratio = 17.5), the passive control modified the flowfield to nearly that of an open type cavity flow; further the cavity drag was reduced by a factor of four. The computational results of both cases showed good agreement with the available experimental data and the predictions of a semiempirical formula. This study demonstrates that the passive control concept can be used to improve the aerodynamic characteristics of open and closed cavity flowfields.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 912153
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  • 173
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    An experimental/computational study of sharp fin induced shock wave/turbulent boundary layer interactions at Mach 5 - Experimental results (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: A combined experimental/computational study has been performed of sharp fin induced shock wave/turbulent boundary layer interactions at Mach 5. The current paper focuses on the experiments and analysis of the results. The experimental data include mean surface heat transfer, mean surface pressure distributions and surface flow visualization for fin angles of attack of 6, 8, 10, 12, 14 and 16-degrees at Mach 5 under a moderately cooled wall condition. Comparisons between the results and correlations developed earlier show that Scuderi's correlation for the upstream influence angle (recast in a conical form) is superior to other such correlations in predicting the current results, that normal Mach number based correlations for peak pressure heat transfer are adequate and that the initial heat transfer peak can be predicted using pressure-interaction theory.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0749
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  • 174
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    Monte Carlo simulation of reentry flows with ionization (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The Direct Simulation Monte Carlo method is applied to a rarefied, weakly ionized, hypersonic flow over a blunt axisymmetric body. An ionization model based on the concept of ambipolar diffusion is used and a model for the sheath is presented. The effects of the new modeling techniques are investigated for flow over the Project Fire II configuration at 11.37 km/s at an altitude of 84.6 km. The calculated results are presented and compared with both experimental data and solutions where ionization effects were not included. In general, the calculated results overpredict the experimental values by about 15-20 percent.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0493
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  • 175
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    Vortex modeling for rotor aerodynamics - The 1991 Alexander A. Nikolsky Lecture (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The efforts toward realistic vortex modeling for rotary wings which began under the guidance of professor A. A. Nikolsky of Princeton University in 1955-1956 are discussed. Attention is given to Nikolsky's flow-visualization studies and major theoretical considerations for vortex modeling. More recent efforts by other researchers have led to models of increasing complexity. The neglect of compressibility and viscous effects in the classical approach is noted to be a major limiting factor in full-scale rotor applications of the classical vortex theory; it has nevertheless been valuable for the delineation of problem areas and the guiding of both experimental and theoretical investigations.
    Keywords: AERODYNAMICS
    Type: American Helicopter Society, Journal (ISSN 0002-8711); 37; 3-14
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  • 176
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    Unsteady flows (1992)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The development status of tactical missile dynamic behavior prediction is evaluated, with a view to the formulation of guidelines for high angle-of-attack tests where highly nonlinear aerodynamics are encountered and strong cross-coupling arises between lateral and longitudinal degrees of freedom. Attention is given to the Ericsson (1979) inviscid computer code, which is entirely general within the geometric constraints of axisymmetry and low aspect ratio lifting surfaces. A serious problem in the prediction of full-scale high-alpha dynamics is the almost total dependence on subscale experimental data, whose use is severely restricted by Reynolds number scaling as well as by model support and wind tunnel wall interference.
    Keywords: AERODYNAMICS
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  • 177
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    International Hypersonic Waverider Symposium, 1st, University of Maryland, College Park, MD, Oct. 17-19, 1990, Proceedings (1990)
    In:  Other Sources
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    Publication Date: 2019-08-28
    Description: The papers presented in this volume provide an overview of current theoretical and experimental research in the field of hypersonic waveriders. In particular, attention is given to efficient waveriders from known axisymmetric flow fields, hypersonic waverider design from given shock waves, limitations of waveriders, and aerodynamic stability theory of hypersonic waveriders. The discussion also covers momentum analysis of waverider flow fields, tethered aerothermodynamic research for hypersonic waveriders, simulation of hypersonic waveriders, and an idealized tip-to-tail waverider model.
    Keywords: AERODYNAMICS
    Type: International Hypersonic Waverider Symposium; Oct 17, 1990 - Oct 19, 1990; College Park, MD; United States
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  • 178
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    Highly separated transonic flows (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Attention is given to the wind tunnel, to photographic visualization of the flow, and to measurements by pressure probes, hot wire anemometry and laser anemometry. The simultaneous use of different means of measurement provided a good description of the phenomenon, and indicated the existence of shocks and their stability, as well as the existence of the bubble, its dimensions, and in particular, the reattachment of its front. The results show that the bursting (or transition) of the bubble front is produced at an unstable position and creates a point of turbulent intensity which diffuses over the entire height of the flow.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75874 , NT80-18 , Colloq. Aerodyn. Appl.; Nov 13, 1979 - Nov 15, 1979; Lille; France
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  • 179
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    Contribution to the aerodynamic study of wings and propellers (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Various problems regarding the aerodynamics of lifting wings are solved. Two methods are proposed for replacing the wing, both involving "viscous" edge vortices. the applications give results which agree well with experiments. Two new methods are also proposed for calculating propellers based on the vortex model consisting of an edge vortex and a "viscous" hub vortex.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77083 , NAS 1.15:77083
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  • 180
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    Comparison of aerodynamic coefficients obtained from theoretical calculations wind tunnel tests and flight tests data reduction for the alpha jet aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The methods by which aerodynamic coefficients are determined and discussed. These include: calculations, wind tunnel experiments and experiments in flight for various prototypes of the Alpha Jet. A comparison of obtained results shows good correlation between expectations and in-flight test results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75237 , AGARD-CP-187 , Meeting of the Flight Mech. Panel; Jun 09, 1975 - Jun 13, 1975; Valloire; France
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  • 181
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    Boundary layer control by means of suction (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The process of boundary layer control by means of suction is described. Its historical development is briefly traced, and its application to airfoils and diffusers is discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75502
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  • 182
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    NASA research objectives and roles (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A chronology of airfoil development is presented in order to put the present NASA airfoil program in perspective. The impact of the NACA series airfoils is considered. Development of advanced analytical and experimental methods for the design and for the determination of the characteristics of not only single element airfoils, but of multielement airfoil combinations used in aerodynamic controls and high lift systems is emphasized along with applications.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1 Pt 1; p 1-9
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  • 183
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    The technology assessment of LTA aircraft systems (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The advantages of conventional small and large airships over heavier than air aircraft are reviewed and the need for developing hybrid aircraft for passenger and heavy charge transport is assessed. Performance requirements and estimated operating costs are discussed for rota-ships to be used for short distance transportation near large cities as well as for airlifting civil engineering machinery and supplies for the construction of power stations, dams, tunnels, and roads in remote areas or on isolated islands.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75535
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  • 184
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    A survey of computational aerodynamics in the United States (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Programs in theoretical and computational aerodynamics in the United States are described. Those aspects of programs that relate to aeronautics are detailed. The role of analysis at various levels of sophistication is discussed as well as the inverse solution techniques that are of primary importance in design methodology. The research is divided into the broad categories of application for boundary layer flow, Navier-Stokes turbulence modeling, internal flows, two-dimensional configurations, subsonic and supersonic aircraft, transonic aircraft, and the space shuttle. A survey of representative work in each area is presented.
    Keywords: AERODYNAMICS
    Type: NASA-SP-394
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  • 185
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    Profile design for an advanced-technology airfoil for general aviation aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A profile from the NASA General Aviation Whitcomb series and NACA profiles are used as a starting point in designing an advanced airfoil for general aviation aircraft. Potential theory pressure distribution calculations, together with boundary layer calculations, permit a decrease in the null moment and an optimization of the lift characteristics of the wing. Trailing edge flap design is also improved. Wind tunnel tests are used to compare the conventional profiles, the NASA profile, and the improved design.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75323 , PAPER-77-027
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  • 186
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    Investigations of the influence of the profile thickness of the compressible plane flow through compressor cascades (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Flow-through cascade of an aircraft turbine compressor is studied experimentally over wide range of Reynolds numbers and subsonic Mach numbers; it was found that deterioration of flow properties due to decreasing Reynolds numbers is less noticeable on thin profiles than on thick ones; however, thick profiles are advantageous in compressors designed for efficient partial load behavior because thick profiles have a relatively large range of usable inlet flow angles.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75277
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  • 187
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    Wake Vortex Minimization (1977)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: A status report is presented on research directed at reducing the vortex disturbances of aircraft wakes. The objective of such a reduction is to minimize the hazard to smaller aircraft that might encounter these wakes. Inviscid modeling was used to study trailing vortices and viscous effects were investigated. Laser velocimeters were utilized in the measurement of aircraft wakes. Flight and wind tunnel tests were performed on scale and full model scale aircraft of various design. Parameters investigated included the effect of wing span, wing flaps, spoilers, splines and engine thrust on vortex attenuation. Results indicate that vortives may be alleviated through aerodynamic means.
    Keywords: AERODYNAMICS
    Type: NASA-SP-409 , Feb 25, 1976 - Feb 26, 1976; Washington
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  • 188
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    Flow-field in a vortex with breakdown above sharp edged delta wings (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The behavior of vortex-flow, accompanied with breakdown, formed above sharp-edged delta wings, was studied experimentally as well as theoretically. Emphasis is placed particularly on the criterion for the breakdown at sufficiently large Reynolds numbers
    Keywords: AERODYNAMICS
    Type: NASA-TM-75339 , NAL-TR-423
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  • 189
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    Formation and propagation of a shock wave from a concave boundary (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Formation of shock wave in two dimensional flow field and method for predicting shape and strength of shock wave
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6319 , E-6241
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  • 190
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    Aeronautical engineering - A special bibliography with indexes, announced January - August 1970 (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography on engineering aspects of design, construction, evaluation, testing, and performance of aircraft and associated components, equipment, and systems
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037
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  • 191
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    Aeronautical Engineering - A Special bibliography with indexes, supplement 6, May 1971 (1971)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - May 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(06)
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  • 192
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    An experimental study of the effects of bodyside compression on forward swept sidewall compression inlets ingesting a turbulent boundary layer (1993)
    In:  Other Sources
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    Publication Date: 2019-08-27
    Description: Forward swept sidewall compression inlets have been tested in the Mach 4 Blowdown Facility at the NASA Langley Research Center to study the effects of bodyside compression surfaces on inlet performance in the presence of an incoming turbulent boundary layer. The measurements include mass flow capture and mean surface pressure distributions obtained during simulated combustion pressure increases downstream of the inlet. The kerosene-lampblack surface tracer technique has been used to obtain patterns of the local wall shear stress direction. Inlet performance is evaluated using starting and unstarting characteristics, mass capture, mean surface pressure distributions and permissible back pressure limits. The results indicate that inlet performance can be improved with selected bodyside compression surfaces placed between the inlet sidewalls.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3125 , ; 16 p.|AIAA, Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
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  • 193
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    Numerical study of multi-element airfoil aerodynamics (1992)
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    Publication Date: 2019-08-27
    Description: Unsteady flowfields around oscillating Boeing VR7 airfoil with and without a leading-edge slat were numerically investigated by a novel zonal method using a conformal mapping technique. Numerical aero-dynamic hysteresis loops show that the leading-edge slat prevents the airfoil dynamic stall at reduced frequency of 0.15, Reynolds number of 1 million, and the oscillation range of 5 deg to 25 deg.
    Keywords: AERODYNAMICS
    Type: ; : Algorithmic trends
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  • 194
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    Supersonic jet control via point disturbances inside the nozzle (1993)
    In:  Other Sources
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    Publication Date: 2019-08-27
    Description: Experiments on supersonic jet control via point disturbances inside the nozzle were conducted using a pressure-matched converging-diverging nozzle with an exit diameter of 3.11 cm and an exit Mach number of 2.1. The disturbance generators are situated on the supersonic nozzle wall between the throat and the jet exit plane; the resulting fluid-mechanical disturbances are observed at the intersection of the disturbance cone and the jet lip. It is demonstrated that a single disturbance generator leads to a polygonal jet appearance, while two symmetric disturbances lead to a symmetric rectangular jet shape and two nonsymmetric disturbances lead to a star-like appearance. Significant cusps are formed in all cases.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 7; p. 1340, 1341.
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  • 195
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    Analysis of hypersonic nozzles including vibrational nonequilibrium and intermolecular force effects (1993)
    In:  Other Sources
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    Publication Date: 2019-08-27
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 7; p. 1243-1249.
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  • 196
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    High-alpha aerodynamic characteristics of crescent and elliptic wings (1989)
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    Publication Date: 2019-08-27
    Description: Static longitudinal and lateral-directional forces and moments were measured for elliptic- and crescent-wing models at high angles of attack in the NASA Langley 14-by-22-ft Subsonic Tunnel. The forces and moments were obtained for an angle-of-attack range including stall and post-stall conditions at a Reynolds number based on the average wing chord of about 1.8 million. Flow-visualization photographs using a mixture of oil and titanium-dioxide were also taken for several incidence angles. The force and moment data and the flow-visualization results indicated that the crescent wing model with its highly swept tips produced much better high-angle-of-attack aerodynamic characteristics than the elliptic model. Leading-edge separation-induced vortex flow over the highly swept tips of the crescent wing is thought to produce this improved behavior at high angles of attack. The unique planform design could result in safer and more efficient low-speed airplanes.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2240 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
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  • 197
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    Stability characteristics of a supersonic boundary layer and their relation to the position of the laminar-turbulent transition point (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: By comparing the calculated results with experimental data, it is demonstrated that the position of the laminar-boundary transition point of a boundary layer can be estimated by using the e-exp-n method. The effect of the Mach number, pressure gradient, and heat transfer on the laminar-turbulent transition is discussed. It is found that under conditions of strong cooling, the effect of the pressure gradient on the position of the transition point is less pronounced than in the absence of heat transfer.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88533 , NAS 1.15:88533
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  • 198
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    Aerodynamic characteristics of general aviation at high angle of attack with the propeller slipstream (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The aerodynamic characteristics of the FA-300 business aircraft at high angle of attack with the propeller stream are described. The FA-300 offers two types, FA-300-700 for 340 HP, and -710 for 450 Hp of the engine. The effects of the propeller slipstream on the high angle of the attack are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88503 , NAS 1.15:88503 , (ISSN 0021-4663)
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  • 199
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    Supersonic flow with feeding of energy (1985)
    In:  CASI
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    Publication Date: 2019-08-27
    Description: The present work discusses the results of some experimental studies on the possibility of attenuating shock waves in a supersonic flow. The shock waves were formed by an external source of electrical energy. An electromechanical method is described that permits partial recovery of the expended energy.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77912 , NAS 1.15:77912
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  • 200
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    NASA/HAA Advanced Rotorcraft Technology and Tilt Rotor Workshops. Volume 4: Flight Control Avionics Systems and Human Factors (1980)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Helicopter user needs, technology requirements and status, and proposed research and development action are summarized. It is divided into three sections: flight dynamics and control; all weather operations; and human factors.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84146 , Dec 02, 1980 - Dec 05, 1980; Palo Alto, CA; United States
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