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  • Other Sources  (1,256)
  • AERODYNAMICS  (1,256)
  • 1970-1974  (1,256)
Collection
  • Other Sources  (1,256)
Source
Keywords
Years
Year
  • 1
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    Astronautics and aeronautics, 1969 Chronology on science, technology, and policy (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Statistical mechanics for wall shear turbulence in Couette flow based on Brownian motion and comparison with stochastic theory based on Navier-Stokes equation
    Keywords: AERODYNAMICS
    Type: NASA-SP-4014
    Format: application/pdf
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  • 2
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    Aeronautical Engineering A special bibliography with indexes, supplement 7 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - July 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(07)
    Format: application/pdf
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  • 3
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    Analytic Methods in Aircraft Aerodynamics (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Analyses of aircraft aerodynamic characteristics
    Keywords: AERODYNAMICS
    Type: NASA-SP-228 , A Symposium Held at Ames Research Center; Oct 28, 1969 - Oct 30, 1969; MOFFETT FIELD, CA; United States
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  • 4
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    Aeronautical Engineering - A special bibliography with indexes /supplement 1/ (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated reference bibliography on aeronautical engineering documents
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(01)
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  • 5
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    Aeronautical engineering - A special bibliography, supplement 2 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - Jan. 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(02)
    Format: application/pdf
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  • 6
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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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  • 7
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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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  • 8
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    Aeronautical engineering: A special bibliography, supplement 45, June 1974 (1974)
    In:  CASI
    Details
    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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  • 9
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    Aeronautical engineering: A special bibliography with indexes, supplement 42, March 1974 (1974)
    In:  CASI
    Details
    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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  • 10
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    Aeronautical engineering: A special bibliography with indexes, supplement 41, February 1974 (1974)
    In:  CASI
    Details
    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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  • 11
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    Aeronautical Engineering: A special bibliography with indexes, supplement 37 (1973)
    In:  CASI
    Details
    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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  • 12
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    Aeronautical engineerng: A special bibliography with indexes, supplement 36 (1973)
    In:  CASI
    Details
    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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  • 13
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    Aeronautical engineering: A special bibliography with indexes, supplement 34 (1973)
    In:  CASI
    Details
    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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  • 14
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    Aeronautical Engineering: A special bibliography, supplement 31, May 1973 (1973)
    In:  CASI
    Details
    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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  • 15
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    Aeronautical engineering: A special bibliography, supplement 29, March 1973 (1973)
    In:  CASI
    Details
    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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  • 16
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    Aeronautical Engineering: A special bibliography with indexes, supplement 28, February 1973 (1973)
    In:  CASI
    Details
    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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  • 17
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    Aeronautical engineering: A special bibliography with indexes, supplement 26 (1973)
    In:  CASI
    Details
    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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  • 18
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    Aeronautical Engineering: A special bibliography with indexes, supplement 22, September 1972 (1972)
    In:  CASI
    Details
    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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  • 19
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    Aeronautical engineering: A special bibliography with indexes, supplement 21, August 1972 (1972)
    In:  CASI
    Details
    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)
    Format: application/pdf
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  • 20
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    Aeronautical Engineering: A special bibliography with indexes, supplement 19, June 1972 (1972)
    In:  CASI
    Details
    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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  • 21
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    A cumulative index to the 1971 issues of Aeronautical Engineering (1972)
    In:  CASI
    Details
    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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  • 22
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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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  • 23
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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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  • 24
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    Aeronautical Engineering, a special bibliography with indexes, supplement 15 (1972)
    In:  CASI
    Details
    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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  • 25
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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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  • 26
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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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  • 27
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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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  • 28
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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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  • 29
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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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  • 30
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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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  • 31
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    Aeronautical Engineering - A Special bibliography with indexes, supplement 6, May 1971 (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(06)
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  • 32
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    A cumulative index to the 1972 issues of aeronautical engineering: A special bibliography (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: A cumulative index to the abstracts contained in NASA SP-7037 (15) through NASA SP-7037 (26) of Aeronautical Engineering: A Special Bibliography. NASA SP-7037 and its supplements has been complied 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, contract, and report number indexes.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(27)
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  • 33
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    Aeronautical Engineering: A special bibliography with indexes, supplement 24, November 1972 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 399 reports, articles, and other documents introduced into the NASA scientific and technical information system in October 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(24)
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  • 34
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    Aeronautical engineering: A special bibliography with indexes, supplement 20 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 437 reports, articles, and other documents introduced into the NASA scientific and technical information system in June 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(20)
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  • 35
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    Aeronautical Engineering: A special bibliography, supplement 25 December 1972 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 373 reports, articles, and other documents introduced into the NASA scientific and technical information system in November 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(25)
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  • 36
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    Aerodynamic problems of the San Marco 2 (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: Aerodynamic problems of San Marco 2 satellite
    Keywords: AERODYNAMICS
    Type: SAN MARCO PROJ. JAN. 1970; P 71-80
    Format: text
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  • 37
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    A cumulative index to the 1973 issues of Aeronautical engineering: A special bibliography (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This publication is a cumulative index to the abstracts contained in NASA SP-7037 (28) through NASA SP-7037 (39) of Aeronautical Engineering: A Special 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, contract, and report number indexes.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(40) , NASA-SP-7037(28) , NASA-SP-7037(40)
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  • 38
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    Aeronautical Engineering: A special bibliography with indexes, supplement 13 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 283 reports, articles, and other documents introduced into the NASA scientific and technical information system in December, 1971. 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(13)
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  • 39
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    Aeronautical engineering: A special bibliography with indexes, supplement 12, December 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics Dec. 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(12)
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  • 40
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    Aeronautical Engineering: A special bibliography with indexes, supplement 23, October 1972 (1972)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 378 reports, articles, and other documents introduced into the NASA scientific and technical information system in September, 1972.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(23)
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  • 41
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    Aeronautical Engineering: A special bibliography with indexes, supplement 9, September 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - September, 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(09)
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  • 42
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    Aeronautical Engineering: A special bibliography with indexes, Supplement 35, September 1973 (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 614 reports, articles, and other documents introduced into the NASA scientific and technical information system in August 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(35)
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  • 43
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    Aeronautical Engineering: A special bibliography, supplement 33 (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This special bibliography lists 419 reports, articles, and other documents introduced into the NASA scientific and technical information system in June 1973.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(33)
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  • 44
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    Aeronautical Engineering - A special bibliography, supplement 3, February 1971 (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Bibliography of aeronautical engineering with abstracts
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(03)
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  • 45
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    Analysis of the Flow About Delta Wings with Leading Edge Separation at Supersonic Speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A research program was conducted to develop an improved theoretical flow model for the flow about sharp edge delta wings with leading-edge separation at supersonic speeds. The flow model incorporates a representation of the secondary separation region which occurs just inboard of the leading edge on such wings and is based on a slender-wing theory whereby the full three-dimensional problem is reduced to a quasi two-dimensional problem in the cross-flow plane. The secondary separation region was modeled by a surface distribution of singularities or a linearized type of cavity representation. The primary vortex and separation were modeled by a concentrated vortex and cut in the cross-flow potential which represents its feeding sheet. The cross-flow solutions for the cavity model were obtained, but these solutions have physical significance only in a very restricted range of angle of attack. The reasons for the failure of the flow model are discussed. The analysis is presented so that other interested researchers may critically review the work.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132358
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  • 46
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    Nonplanar Method for Predicting Incompressible Aerodynamic Coefficients of Rectangular Wings with Circular-Arc Camber (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The development of a nonplanar lifting surface method having a continuous distribution of singularities and satisfying the tangent flow boundary condition on the mean camber surface is given. The method predicts some incompressible longitudinal aerodynamic coefficients of rectangular wings which have circular-arc camber. The solution method is of the integral-equation type and the resulting surface integrals are evaluated by either using numerical or analytical techniques, as are appropriate. Applications are made and the results compared with those from an exact two-dimensional circular-arc camber solution, a three-dimensional flat-wing solution which represents the camber by a projected slope onto the flat surface, and a flat-wing experiment. From these comparisons, the present method is found to predict well the flat-wing experiment and limiting values, in addition to the center of pressure variation at an angle of attack of zero for any camber. For wings having camber ratios larger than about 1.25% and moderate to high aspect ratios, the results deterioriate due to the inadequacy of lifting pressure modes employed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-67791
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  • 47
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    Acoustic Tests of a Flexible Spacecraft Model (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Acoustic tests of flexible spacecraft model
    Keywords: AERODYNAMICS
    Type: NASA-CR-1618
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  • 48
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    Design and Two-Dimensional Cascade Test of Turbine Stator Blade with Ratio of Axial Chord to Spacing of 0.5 (1970)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Design and performance of very low-solidity turbine stator blades for first stage jet engine turbine with velocity and pressure diagrams
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-1991 , E-5490
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  • 49
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    Supercritical aerodynamics - Worthwhile over a range of speeds. (1972)
    In:  Other Sources
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    Publication Date: 2019-08-13
    Description: Supercritical flow exists whenever a high enough forward speed causes local flow over a lifting surface or body to exceed the sonic or critical value. The principal difference between conventional subsonic aerodynamic technology and supercritical technology lies in the cross-sectional profile of lifting surfaces. The characteristics of the supercritical airfoil suggests three potential benefits from applications to civil aircraft. For aircraft designed to operate at moderate subsonic speeds the supercritical airfoil may permit the reduction of structural weight. Supercritical technology would have a second application in permitting efficient high subsonic speed cruise by delaying the transonic drag rise. Another advantage of the thick supercritical wing shows up at low speeds.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 10; Aug. 197
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  • 50
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    Aircraft wake turbulence minimization by aerodynamic means (1974)
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    Publication Date: 2019-08-13
    Description: The paper reviews NASA's efforts on wake vortex turbulence minimization by aerodynamic design or retrofit modifications to large transport aircraft. Theoretical and experimental (ground-based and flight) results are presented which show that the adverse effects of a vortex wake produced by a large aircraft on a small following aircraft can be reduced significantly.
    Keywords: AERODYNAMICS
    Type: American Meteorological Society and American Institute of Aeronautics and Astronautics, Conference on Aerospace and Aeronautical Meteorology; Nov 12, 1974 - Nov 14, 1974; El Paso, TX
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  • 51
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    Technical evaluation report on AGARD Flight Mechanics Panel Symposium on Flight in Turbulence (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The proceedings of a conference on the effects of atmospheric turbulence on flight characteristics are presented. The subjects discussed include the following: (1) turbulent environment, (2) operational problems, (3) design criteria, and (4) artificial aids for flight improvement. One conclusion is that there is a critical need for cross correlation measurements between various low atmosphere turbulence components. Additional discussion were held concerning wake vortex research for wake vortex detection and avoidance.
    Keywords: AERODYNAMICS
    Type: AGARD-AR-67 , May 14, 1973 - May 18, 1973; Woburn Abbey
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  • 52
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    Unsteady rotor aerodynamics at low inflow and its effect on flutter. (1972)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A comprehensive flutter analysis has been developed utilizing compressible unsteady aerodynamics for a helicopter rotor at a low inflow condition. The rotor is treated as a nonuniform rotating beam with finite bending and torsional stiffness. The unsteady aerodynamic representation incorporates the effects of spanwise variations in Mach number and reduced frequency by applying available two-dimensional theories in a strip theory fashion. The results are characterized by an oscillation of the apparent aerodynamic damping with decreasing frequency ratio (oscillation frequency/rotational frequency) which suggests a new flutter criteria for rotors. These results are correlated with available experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 72-959 , American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference; Sept. 11-13, 1972; Palo Alto, CA
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  • 53
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    Installation caused flow distortion and its effect on noise from a fan designed for turbofan engines. (1972)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Use of a ground test stand to obtain acoustic data on a full-scale prototype fan designed for quiet subsonic-aircraft engines. The fan was installed in three different ways in the test stand. In two of the installations the fan was driven by a shaft in the inlet; in the third installation the fan was driven from the rear. These three installations, and the structures associated with them, resulted in various amounts of inlet flow distortion to the fan. The rear-drive installation had less inlet flow distortion than the two front drive installations. Differences in blade passage sound pressure levels of more than 10 dB were measured between the rear-drive and front-drive versions, with the rear-drive installation producing less noise. Perceived noise levels were computed and the influence of the distortion on these levels was determined.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 72-1006 , American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference; Sept. 13-15, 1972; Palo Alto, CA
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  • 54
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    Actuator disk theory for incompressible highly rotating flows. (1971)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A solution has been obtained for a stator-rotor pair operating in an annulus with constant hub and tip radii. The stator and rotor are represented as actuator discs, and perfect fluid flow is assumed. The solutions are exact within these limitations, no linearization being required. The forms of blade loadings considered allow the introduction of large vorticity by either the rotor or stator. As a result, the rotor may be a ?nonconstant-work' row. The solutions obtained are of summational form, but many of the summations are obtained in closed form, the resultant formulas allowing rapid calculation of desired examples. An example numerical result is included.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 71-WA/FE-18
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  • 55
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    Aerodynamics of slender bodies and wing-body combinations at a free-stream Mach number equal to one - Theory and experimental evaluation (1970)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Aerodynamics of steady, inviscid transonic flows around slender bodies and wing-body combinations at free stream Mach number one
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-798
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  • 56
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    A method for computing the nonequilibrium radiant emission from near-equilibrium shock layers (1970)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Near equilibrium shock layers nonequilibrium radiant emission calculation, noting application to Mars entry conditions
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-773
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  • 57
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    Comparison of theoretical and flight-measured ionization in a blunt body reentry flow field (1970)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Plasma diagnostic data from onboard Langmuir probes, reflectometers, antenna VSWR and beacon and telemetry attenuation for blunt body reentry flow field
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-756
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  • 58
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    Prediction of far flow field in trailing vortices. (1972)
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    Publication Date: 2019-07-27
    Description: A finite-difference machine code is brought to bear on the wake-vortex problem in the quasi-cylindrical boundary-layer approximation. A turbulent-energy model containing new features is developed. Parameters of the model are evaluated by comparison of calculated velocities and turbulent intensities with measurements in an axisymmetric wake. Comparisons are made with a previous calculation of the decay of an isolated vortex and with wind tunnel and flight measurements in trailing vortices. A self-similar solution develops at large axial distance that decays with the square root of distance. A slower decay occurs in the preceding transition region.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 72-989 , American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference; Sept. 11-13, 1972; Palo Alto, CA
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  • 59
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    Aerodynamics of high-performance Ludwieg tubes. (1972)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A small perturbation analysis of the flow in a Ludwieg tube supply is described which includes both the growing turbulent boundary-layer and axial pipe nonuniformities. Measured pressure time histories are used to check the theory and its extension to high pipe Mach numbers and large flow perturbations. The nonsteady coupling of this flow to a nozzle is investigated. Calculations are made of the effects on the nozzle boundary layer, while a separate analysis is carried out for the case of complete mixing in a nozzle plenum. The double expansion nozzle is shown to extend Ludwieg-tube capability. Analytical and experimental studies are made of the aerodynamic problems that can arise in these nozzles.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 72-994 , American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference; Sept. 13-15, 1972; Palo Alto, CA
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  • 60
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    Flow and acoustic characteristics of subsonic and supersonic jets from convergent nozzle (1970)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Aerodynamic and acoustic characteristics of subsonic and supersonic jets from convergent nozzles with room temperature air supply
    Keywords: AERODYNAMICS
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  • 61
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    Atmospheric Flight Mechanics Conference, 2nd, Palo Alto and Moffett Field, Calif., September 11-13, 1972, Informal Papers. (1972)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Limitations in the acquisition of nonlinear aerodynamic coefficients from free-oscillation data by means of the Chapman-Kirk technique, SAM-D control test vehicle trajectory plannning and flight test analysis, and determination of aerodynamic drag from radar data are among the topics covered in papers concerned with atmospheric flight mechanics. Other areas covered include fixed and rotary-wing aircraft, ordnance and reentry vehicles, and analysis and measurement techniques. Individual items are announced in this issue.
    Keywords: AERODYNAMICS
    Type: Atmospheric Flight Mechanics Conference; Sept. 11-13, 1972; Palo Alto, CA*Moffett Field, CA
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  • 62
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    Investigation of the stall-induced shock wave /hammershock/ at the inlet to the engine (1974)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The peak static pressures measured at the inlet to the engine during stall are presented for a turbojet and two turbofan engines. It is shown for one turbofan and the turbojet that the static pressure ratio across the hammershock does not exceed significantly the normal shock pressure ratio necessary to stop the flow. The second turbofan engine did not follow this rule. Possible reasons for the departure are discussed. For the two turbofan engines, the influence of the stall method on the hammershock intensity has been investigated. Data related to the spatial distribution of pressure in the hammershock are also presented.
    Keywords: AERODYNAMICS
    Type: Symposium on Propulsion System Structural Integration and Engineering Integrity; Sept. 3-6, 1974; Monterey, CA
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  • 63
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    Reynolds number effects on boattail drag of exhaust nozzles from wind tunnel and flight tests (1974)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: A family of nacelle-mounted high-angle boattail nozzles was tested to investigate Reynolds number effects on drag. The nozzles were flown on a modified F-106B and mounted on scale models of an F-106 in a wind tunnel. A 19-to-1 range of Reynolds number was covered as a result of the large size differences between models and by flying over a range of altitude. In flight the nozzles were mounted behind J-85 turbojet engines. Jet boundary simulators and a powered turbojet engine simulator were used on the wind tunnel models. Data were taken at Mach numbers of 0.6 and 0.9. Boattail drag was found to be affected by Reynolds number. The effect is a complex relationship dependent upon boundary layer thickness and nozzle boattail shape. As Reynolds number was increased from the lowest values obtained with scale models, boattail drag first increased to a maximum at the lowest flight Reynolds number and then decreased.
    Keywords: AERODYNAMICS
    Type: Fluid Dynamics Panel Specialists Meeting on Airframe/Propulsion Interference; Sept. 3-6, 1974; Rome; Italy
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  • 64
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    Methods for the wind-tunnel measurement of unsteady non-linear aerodynamic forces (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Unsteady nonlinear aerodynamic loads measurements in wind tunnel, using linearized mathematical analog
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-573 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AERODYNAMIC TESTING CONFERENCE, 5TH; May 18, 1970 - May 20, 1970; TULLAHOMA, TN
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  • 65
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    Comparison of free-flight experimental results with theory on the nonlinear aerodynamic effects of bluntness for slender cones at Mach number 17 (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Aerodynamic effects of bluntness on slender cones in free flight tests at Mach 17
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-554 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, ATMOSPHERIC FLIGHT MECHANICS CONFERENCE; May 13, 1970 - May 15, 1970; TULLAHOMA, TN
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  • 66
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    A theory for base pressures on multinozzle rocket configurations (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Turbulent base flowfields in multinozzle configurations, considering adiabatic flow and determining base pressure distribution from reverse jet impingement
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 69-570 , ; ACE(|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, PROPULSION JOINT SPECIALIST CONFERENCE, 5TH, U.S. AIR FORCE ACADEMY; Jun 09, 1969 - Jun 13, 1969; COLORADO SPRINGS, CO
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  • 67
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    A method for extracting aerodynamic coefficients from free-flight data (1970)
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    Publication Date: 2019-07-13
    Description: Aerodynamic coefficients from observed motion of body in flight, eliminating need for closed form solutions by employing numerical solutions to equations of motion
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 69-134 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 7TH; Jan 20, 1969 - Jan 22, 1969; NEW YORK, NY|; ACE(
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  • 68
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    Supersonic jet penetration /up to Mach 4/ into a Mach 2 airstream (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Helium injection Mach number effect on supersonic jet penetration into Mach 2 air stream from flat plate determined from concentration measurements
    Keywords: AERODYNAMICS
    Type: ; ACE(|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 69
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    A study of rotor blade-vortex interaction (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Surface pressure and lift measurement on model lifting rotor blade as function of vortex interaction, using flush mounted pressure transducers
    Keywords: AERODYNAMICS
    Type: AMERICAN HELICOPTER SOCIETY, ANNUAL NATIONAL FORUM, 26TH; Jun 16, 1970 - Jun 18, 1970; WASHINGTON, DC
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  • 70
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    A study of the relative merits of three axisymmetric inlets for a hypersonic cruise mission (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Turboramjet powered hypersonic aircraft axisymmetric inlet systems using forward translating cowl and centerbody for various air flow characteristics
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-687 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, PROPULSION JOINT SPECIALIST CONFERENCE, 6TH; Jun 15, 1970 - Jun 19, 1970; SAN DIEGO, CA
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  • 71
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    An experiment to determine density variations in the earth's atmosphere and other atmospheric and aerodynamic information (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Atmospheric density variations and functional dependence of aerodynamic moment coefficient on incident angle from Saturn Workshop flight experiment
    Keywords: AERODYNAMICS
    Type: NATIONAL CONFERENCE ON AEROSPACE METEOROLOGY, 4TH; May 04, 1970 - May 07, 1970; LAS VEGAS, NV
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  • 72
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    Transonic static- and dynamic-stability characteristics of two large-angle spherically blunted high-drag cones (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Transonic static and dynamic stability of large angle spherically blunted high-drag cones
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-564 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, ATMOSPHERIC FLIGHT MECHANICS CONFERENCE; May 13, 1970 - May 15, 1970; TULLAHOMA, TN
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  • 73
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    The influence of initial flow direction on the turbulent base pressure in supersonic axisymmetric flow (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Turbulent base pressure on conical afterbodies in supersonic axisymmetric flow, including initial direction effect
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-555 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, ATMOSPHERIC FLIGHT MECHANICS CONFERENCE; May 13, 1970 - May 15, 1970; TULLAHOMA, TN
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  • 74
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    Cone drag in rarefied hypersonic flow (1970)
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    Publication Date: 2019-07-13
    Description: Drag coefficients for spheres and sharp cones in rarefied hypersonic air flow obtained in shock tunnel using free flight technique
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 69-140 , ; RO(|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 7TH; Jan 20, 1969 - Jan 22, 1969; NEW YORK, NY
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  • 75
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    On the calculation of static and dynamic stability derivatives for bodies of revolution at subsonic and transonic speeds (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Stability derivatives for bodies of revolution at subsonic and transonic speeds
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-190 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 76
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    Massive blowing effects on viscous, radiating, stagnation-point flow (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Massive blowing effect on stagnation point radiative energy transfer of ablative heat shield during planetary entry at hypersonic velocities
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-203 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 77
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    An approximate method for predicting pressure distributions on blunt bodies at angle of attack (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Pressure distributions prediction on blunt bodies at angle of attack, considering bodies of revolution and large angle cones
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-208 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 78
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    Unsteady airfoil stall review and extension (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Unsteady airfoil stall in incompressible flow, including pitch rate induced accelerated flow effect on leading edge and trailing edge stall
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-77 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 79
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    Generalized aerodynamic forces on a flexible plate undergoing transient motion in a shear flow with an application to panel flutter (1970)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Aerodynamic forces for boundary layer profiles of flexible plate under transient motion in shear flow using computer programs
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-76 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 8TH; Jan 19, 1970 - Jan 21, 1970; NEW YORK, NY
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  • 80
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    Increasing the stable operating range of a Mach 2.5 inlet (1970)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Wind tunnel tests to increase stable operating range of supersonic mixed compression inlet
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-52799 , PROPULSION JOINT SPECIALIST CONF.; Jun 15, 1970 - Jun 19, 1970; SAN DIEGO, CA; UNITED STATES
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  • 81
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    Review of propulsion-induced effects on aerodynamics of jet V/STOL aircraft (1970)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Propulsion device-induced effects on V/STOL aircraft aerodynamics in hover and transition flight
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-5617 , L-6565 , TENN. UNIV. SPACE INST. SHORT COURSE ON V/STOL; Nov 01, 1968; KNOXVILLE, TN; UNITED STATES
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  • 82
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    Low-speed aerodynamic characteristics of a 13.1-percent-thick, high-lift airfoil (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Low speed sectional characteristics of a high lift airfoil are studied and a comparison is made of those characteristics with the predictions of the theoretical methods used in the airfoil's design. The 13.1 percent-thick, UI-1720 airfoil was found to achieve the predicted maximum lift coefficient of nearly 2.0. No upper-surface, flow separation was found below the stall angle of attack of 16 degrees; it appeared that stall was due to an abrupt leading edge flow separation.
    Keywords: AERODYNAMICS
    Type: NASA-CR-153937 , SAE-740366 , Business Aircraft Meeting; Apr 02, 1974 - Apr 05, 1974; Wichita, KS; United States
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  • 83
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    A computing method for sound propagation through a nonuniform jet stream (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The classical formulation of sound propagation through a jet flow was found to be inadequate for computer solutions. Previous investigations selected the phase and amplitude of the acoustic pressure as dependent variables requiring the solution of a system of nonlinear algebraic equations. The nonlinearities complicated both the analysis and the computation. A reformulation of the convective wave equation in terms of a new set of dependent variables is developed with a special emphasis on its suitability for numerical solutions on fast computers. The technique is very attractive because the resulting equations are linear in nonwaving variables. The computer solution to such a linear system of algebraic equations may be obtained by well-defined and direct means which are conservative of computer time and storage space. Typical examples are illustrated and computational results are compared with available numerical and experimental data.
    Keywords: AERODYNAMICS
    Type: Acoustical Society of America, Meeting; Nov 04, 1974 - Nov 08, 1974; St. Louis, MO
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  • 84
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    Aerodynamic drag reduction tests on a full-scale tractor-trailer combination with several add-on devices (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic drag tests were performed on a conventional cab-over-engine tractor with a 45-foot trailer and five commercially available or potentially available add-on devices using the coast-down method. The tests ranged in velocity from approximately 30 miles per hour to 65 miles per hour and included some flow visualization. A smooth, level runway at Edwards Air Force Base was used for the tests, and deceleration measurements were taken with both accelerometers and stopwatches. An evaluation of the drag reduction results obtained with each of the five add-on devices is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-56028 , Reduction of Aerodynamic Drag of Trucks Conf.; Oct 10, 1974 - Oct 11, 1974; Pasadena, CA; United States
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  • 85
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    Three dimensional flows around airfoils with shocks (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The present work describes a mathematical model and numerical scheme for the computer-aided calculation of two- and three-dimensional transonic flow over an isolated yawed wing with oblique shock waves and a trailing vortex sheet. The flow is modeled by the potential equation for irrotational flow which is hyperbolic at supersonic points and elliptic at subsonic points. A coordinate-invariant difference scheme is used in which retarded difference formulas are constructed to conform with the local flow direction. The resulting 'rotated' difference scheme allows complete flexibility in the choice of a coordinate system. Shock waves are located automatically in the form of compression bands spread over a few mesh widths. The scheme has proven to be stable and convergent throughout the transonic range. Calculations have been performed for Mach number up to 1.2 and yaw angles up to 60 deg, the likely operating range of a yawed-wing transport designed to fly at supersonic speeds. Calculations becomes less accurate towards upper end of range, because the difference scheme is first-order accurate in the supersonic range.
    Keywords: AERODYNAMICS
    Type: International Symposium on Computing methods in applied sciences and engineering; Dec 17, 1973 - Dec 21, 1973; Versailles; France
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  • 86
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    Supercirculation effects induced by vectoring a partial-span rectangular jet (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Thrust-induced supercirculation effects from thrust vectoring have indicated a potential for not only increasing maneuverability of fighter aircraft but also as a means of improving cruise performance. The current study investigated a partial-span rectangular jet-exhaust nozzle located at the wing trailing edge that acts similar to a jet flap by increasing lift due to supercirculation. This paper summarizes experimental studies including the effects of nozzle deflection angle, wing camber, and nozzle shape and exit location on lift, drag and load distributions. The results indicate that significant increases in thrust-induced lift along with substantial decreases in drag are possible.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 74-971 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
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  • 87
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    Investigation of acoustic radiation from supersonic turbulent jets by double-pulse holographic interferometry (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new experimental method was used to optically investigate the acoustic field radiated from supersonic jets. The method utilizes a pulse ruby laser to obtain double exposure holograms of the sound field of a supersonic jet. The jet remains on during both exposures thus eliminating the no-flow exposure. The time separation between the pulses can be varied depending on the spectral component of the radiation to be observed. Optical records were obtained for supersonic jets with exit Mach number 1.0, 1.5 and 2.0. It was found that high frequency acoustic radiation mainly originates from the regions near the nozzle exit, whereas the low frequency noise is generated from regions further downstream. These findings are consistent with the acoustic data obtained by other investigators.
    Keywords: AERODYNAMICS
    Type: Meeting of the Acoustical Society of America; Apr 23, 1974 - Apr 26, 1974; New York, NY
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  • 88
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    Theoretical considerations of some nonlinear aspects of hypersonic panel flutter (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A research project to analyze the effects of hypersonic nonlinear aerodynamic loading on panel flutter is reported. The test equipment and procedures for conducting the tests are explained. The effects of aerodynamic linearities on stability were evaluated by determining constant-initial-energy amplitude-sensitive stability boundaries and comparing them with the corresponding linear stability boundaries. An attempt to develop an alternative method of analysis for systems where amplitude-sensitive instability is possible is presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-140896 , SU-DAAR-491
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  • 89
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    Investigation of the Kline-Fogleman airfoil section for rotor blade applications (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Wind tunnel tests of a wedgeshaped airfoil with sharp leading edge and a spanwise step were conducted. The airfoil was tested with variations of the following parameters: (1) Reynolds number, (2) step location, (3) step shape, (4) apex angle, and (5) with the step on either the upper or lower surface. The results are compared with a flat plate and with wedge airfoils without a step having the same aspect ratio. Water table tests were conducted for flow visualization and it was determined that the flow separates from the upper surface at low angles of attack. The wind tunnel tests show that the lift/drag ratio of the airfoil is lower than for a flat plate and the pressure data show that the airfoil derives its lift in the same manner as a flat plate.
    Keywords: AERODYNAMICS
    Type: NASA-CR-141282 , AE-74-1054-1
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  • 90
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    The response of an axial compressor to unsteady disturbances (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The disturbances of flow in a uniform duct are examined, taking into account a disturbance which is sinusoidal in time. The equations of motion for a plane disturbance with blade forces represented by body forces are considered along with the stage configuration of the compressor and the temperature rise for two-dimensional flow through the stage. An investigation is conducted for the case in which the disturbances are restricted to small amplitudes about the design operating condition for all points within the compressor. The three independent solutions of the disturbance equations obtained for the system of compressor and associated inlet and exit ducts can be used with three arbitrary constants to satisfy three external conditions.
    Keywords: AERODYNAMICS
    Type: Interagency Symposium on University Research in Transportation Noise; Jun 05, 1974 - Jun 07, 1974; Raleigh, NC
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  • 91
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    A new technique for inducing a turbulent boundary layer in a supersonic flow (1973)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The feasibility of using slot injection to establish a turbulent boundary layer corresponding to a known Reynolds number is experimentally investigated. The basic concept consists of injecting secondary air through a slot. The air is injected at the same local static pressure and at a selected stagnation temperature to simulate a given upstream condition. The mass of the injected air can be controlled to match a desired Reynolds number. In the present experiment, secondary air was injected through a supersonic nozzle over a flat plate model. Heat transfer rates were measured at about 50 to 100 slot heights behind the slot, and the results were compared with theoretical estimates. Static pressure measurements were made over the surface in the streamwise direction. Velocity and Mach number profiles were obtained at a selected position downstream of the slot. Laminar and turbulent profiles were calculated from the Crocco method and the 1/7 power law respectively to compare with the results of measurements.
    Keywords: AERODYNAMICS
    Type: International Symposium on Space Technology and Science; Sep 03, 1973 - Sep 08, 1973; Tokyo; Japan
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  • 92
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    Aerodynamic and acoustic performance of ejectors for engine-under-the-wing concepts (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Subsonic thrust augmentation, exhaust plume velocity contours and acoustic characteristics of a small-scale, 6-tube mixer nozzle with ejector were obtained with and without a wing. Thrust augmentation up to 30 percent was achieved. Aerodynamic results showed that at a given location, greater downstream velocities are obtained with an ejector than with the baseline nozzle. Ejectors reduce high frequency noise; however, low-frequency noise amplification also occurs. Acoustic reflections off the wing increase the noise level to a ground observer. With an ejector, the acoustic benefits of forward velocity may be significantly reduced compared with the baseline nozzle.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 74-950 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
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  • 93
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    An experimental and theoretical study of low-aspect ration swept and oblique wings at Mach numbers between 0.6 and 1.4 (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Experimental forces and moments for two wing-body combinations having (a) a swept wing and (b) an oblique wing are compared. At all Mach numbers, the oblique wing (at its optimum sweep angle) had higher maximum lift-to-drag ratios than the fixed, swept wing. At high angles of attack, the direction of the pitching or rolling tendencies of the oblique wing was a function of the spanwise distribution of wing bend or washout for the two bends being investigated. At low angles of attack, linear theory gave satisfactory predictions of the subsonic lift-curve slope, the aerodynamic-center travel with Mach number, and the maximum lift-to-drag ratio.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 74-771 , Mechanics and Control of Flight Conference; Aug 05, 1974 - Aug 09, 1974; Anaheim, CA
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  • 94
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    Cross-correlation methods for studying near- and far-field noise characteristics of several flow-surface interaction problems (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Systematic methods based on cross-correlation techniques are presented for experimental studies of near- and far-field noise characteristics of airflow-surface interaction problems. By cross-correlating any two of three-kinds of microphone measurements: one flush-mounted on the surface, one located in the near field, and one placed in the far field, far-field noise intensities and near-field acoustic energy fluxes can be determined. In both near and far fields, the noise characteristics due to the flow turbulence and surface fluctuating pressure contributions can be evaluated separately. Specific applications to the noise field generated by impinging jets, by surface blowing jets, and by turbulent flow over trailing edges are discussed.
    Keywords: AERODYNAMICS
    Type: Meeting of the Acoustical Society of America; Apr 23, 1974 - Apr 26, 1974; New York, NY
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  • 95
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    Propagation of plane waves in a variable area duct carrying a compressible subsonic flow (1974)
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    Publication Date: 2019-07-13
    Description: A complete numerical solution is obtained for plane wave propagation in a variable-area duct which carries a mean compressible flow. The equation solved is a matrix formulation of the equations first derived by Tsien in 1952. Sample calculations are presented for four particular flow configurations: (1) a duct-nozzle-duct combination with the acoustic wave traveling with the flow, (2) a duct-nozzle-duct combination with the acoustic wave traveling against the flow, (3) an inlet-nozzle-duct configuration with the acoustic wave traveling against the flow, and (4) a duct-nozzle-exit configuration with the acoustic wave traveling with the flow. For each of these cases, the variation of energy flux with frequency is shown for particular geometry and flow condition.
    Keywords: AERODYNAMICS
    Type: Meeting of the Acoustical Society of America; Apr 23, 1974 - Apr 26, 1974; New York, NY
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  • 96
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    An experimental and analytical study of slip and catalytic boundary conditions applied to spheres in low Reynolds number arc jet flows (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Measurements of low-density dissociated arc-heated flows around low and high surface catalycity spheres are compared with numerical solutions to the full Navier-Stokes equations for reacting gas flow fields, taking into account slip and finite surface catalytic boundary conditions. A time-dependent finite difference solution technique developed by Li (1973, 1974) is used in the investigation and a simple transport model is employed for the flows considered. The correctness of the solution approach is demonstrated by the very good agreement obtained between experimental and computational data.
    Keywords: AERODYNAMICS
    Type: International Symposium on Rarefied gas dynamics; Jul 15, 1974 - Jul 20, 1974; Goettingen; Germany
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  • 97
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    Development of inverse inviscid transonic solution methods (1974)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: A numerical method suitable for the analysis and/or design of supercritical transonic airfoils is reported. In order to achieve accuracy, the method utilizes the full inviscid potential flow equations; and in order to remain simple it solves the problem in a stretched Cartesian grid system. The resulting computer program has several advantages over others of its type -- its use in either the direct analysis mode in which the airfoil shape is prescribed and the flow field and surface pressures are determined, or in the inverse mode in which the surface pressures are given and the airfoil shape and flow field are computed. Other advantages of the program include its use in a design program, the rotated finite difference scheme and its determination of the airfoil shape simultaneously with the flow field relaxation solution.
    Keywords: AERODYNAMICS
    Type: NASA-CR-142016 , TAMRF-3033-7403
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  • 98
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    NASA flight research on aircraft wake vortices and minimization concepts (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 74-953 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
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  • 99
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    Review of NASA supercritical airfoils (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: NASA supercritical airfoils are characterized by a substantially reduced curvature of the midcord region of the upper surface together with increased camber near the trailing edge. The basic aerodynamic phenomena associated with the airfoils and representative wind tunnel results are discussed. The results indicate that the drag rise Mach numbers for NASA supercritical airfoils are 0.1 higher than for comparable NACA 6-series airfoils. A recent analytic method for predicting the aerodynamic characteristics of supercritical airfoils is described. The flight demonstration programs of three applications of supercritical airfoils utilizing the F-8, T-2C and F-111 as test beds are summarized.
    Keywords: AERODYNAMICS
    Type: ICAS PAPER 74-10 , International Council of the Aeronautical Sciences Congress; Aug 25, 1974 - Aug 30, 1974; Haifa; Israel
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  • 100
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    Experimental and analytical sonic nozzle discharge coefficients for Reynolds numbers up to 8,000,000 (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Sonic discharge coefficients are presented for two different geometry flow nozzles using nitrogen gas at high pressures where real-gas corrections are significant. Throat Reynolds number range extended up to 8,000,000. Experimentally obtained coefficients for a nozzle with a continuous and finite radius of curvature agreed with those obtained analytically to within 0.2 per cent. Experimental coefficients for a long-radius ASME nozzle agreed to within 0.25 per cent to an empirical equation representing the most probable subsonic discharge coefficient.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 74-WA/FM-8 , American Society of Mechanical Engineers, Winter Annual Meeting; Nov 17, 1974 - Nov 22, 1974; New York, NY
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