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  • AERODYNAMICS  (44)
  • ASTROPHYSICS
  • 1970-1974  (44)
  • 1940-1944
  • 1973  (44)
  • 1
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 6: IPAD system development and operation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The strategy of the IPAD implementation plan presented, proposes a three phase development of the IPAD system and technical modules, and the transfer of this capability from the development environment to the aerospace vehicle design environment. The system and technical module capabilities for each phase of development are described. The system and technical module programming languages are recommended as well as the initial host computer system hardware and operating system. The cost of developing the IPAD technology is estimated. A schedule displaying the flowtime required for each development task is given. A PERT chart gives the developmental relationships of each of the tasks and an estimate of the operational cost of the IPAD system is offered.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132396 , D6-60181-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Feasibility study of an Integrated Program for Aerospace vehicle Design (IPAD). Volume 4: IPAD system design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The computing system design of IPAD is described and the requirements which form the basis for the system design are discussed. The system is presented in terms of a functional design description and technical design specifications. The functional design specifications give the detailed description of the system design using top-down structured programming methodology. Human behavioral characteristics, which specify the system design at the user interface, security considerations, and standards for system design, implementation, and maintenance are also part of the technical design specifications. Detailed specifications of the two most common computing system types in use by the major aerospace companies which could support the IPAD system design are presented. The report of a study to investigate migration of IPAD software between the two candidate 3rd generation host computing systems and from these systems to a 4th generation system is included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-132394 , D6-60181-4
    Format: application/pdf
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  • 3
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    Airfoil wake vortex characteristics in the far field (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tangential and axial velocity profiles were measured in the far field wake vortices of several different airfoils. The results are summarized and discussed. A scanning laser velocimeter was used to obtain data up to 1000 chord lengths behind airfoils with rectangular, diamond-shaped, and swept wing planforms at several different angles of attack. The results show general agreement with wind tunnel measurements made in the near field. The results identify two separate flow regions for the dependence of vortex maximum tangential velocity on downstream distance; an inviscid region where the velocity remains constant after rollup to downstream distances of 200 chord lengths, and then a decay or viscous region that persisted to the limit of the test distance. The decay rates appear to be sensitive to both angle of attack and span loading. The maximum tangential velocity for downstream distances to 40 span lengths was reduced by a factor of 2 by changing from an elliptic (swept wing) or rectangular span loading to a triangular-like span loading (diamond-shaped planform wing). Measured axial velocity defects are shown to agree with those predicted by laminar theory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62318 , A-5262
    Format: application/pdf
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  • 4
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    Effect of exhaust nozzle configuration on aerodynamic and acoustic performance of an externally blown flap system with a quiet 6:1 bypass ratio engine (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A highly suppressed TF-34 engine was used to investigate engine and flap interaction noise associated with an externally blown flap STOL powered lift system. Noise, efficiency, and velocity decay characteristics of mixed and separate flow exhaust systems including convergent, co-annular, and lobed designs were determined with the engine operating alone. Noise data were then obtained for several of the exhaust configurations with the engine blowing a wing-flap segment. Noise for both the engine alone and the engine with blown flaps showed substantial differences for the various exhaust configurations tested. The differences in observed noise are related primarily to nozzle effective exhaust velocity, flap impingement velocity, and noise spectral shape.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 73-1217 , Propulsion Conference; Nov 05, 1973 - Nov 07, 1973; Las Vegas, NV; US
    Format: text
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  • 5
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    Externally blown flap dynamic loads (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Some of the principal results obtained in three series of measurements of fluctuating surface pressures induced on externally blown flaps by jet impingment are presented. Large- and small-scale models and hot- and cold-flow tests are considered. The discussion sets forth scaling parameters and consistent features of the root-mean-square values and spectra of the loading. Implications of these results with regard to sonic fatigue are indicated.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 131-142
    Format: text
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  • 6
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    Reference temperature method for predicting turbulent compressible skin-friction coefficient. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Feb. 197
    Format: text
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  • 7
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    Estimation of aerodynamics for slender bodies alone and with lifting surfaces at alpha's from 0 deg to 90 deg. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Expressions are derived, according to a method developed by the author (1972), for bodies in which the cross-sectional shape (but not necessarily the area) is constant along the longitudinal axis. For the more general case of a body alone or with lifting surfaces where the cross-sectional shape varies along the length, a similar procedure is suggested. The specific case for an elliptic cone with a triangular wing is considered, and formulas for winged elliptic cross sections are developed. For the limited test conditions shown, the agreement between computed and experimental results is very good.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 11; Mar. 197
    Format: text
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  • 8
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    Streamline curvature design procedure for subsonic and transonic ducts (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A procedure for designing ducts for subsonic and transonic speeds is described. Examples discussed are a wind-tunnel contraction cone, a supersonic nozzle, and a diffuser. A listing of the computer program is included. The streamline curvature equations represent a form of the exact, compressible, inviscid flow equations. The method is applicable from low subsonic to supersonic speeds.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7368 , L-8963
    Format: application/pdf
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  • 9
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    Canard-wing lift interference related to maneuvering aircraft at subsonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted at Mach numbers of 0.7 and 0.9 to determine the lift interference effect of canard location on wing planforms typical of maneuvering fighter configurations. The canard had an exposed area of 16.0 percent of the wing reference area and was located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. In addition, the canard could be located at two longitudinal stations. Two different wing planforms were tested: one with a leading-edge sweep angle of 60 deg and the other with a leading-edge sweep angle of 44 deg. The results indicated that although downwash from the canard reduced the wing lift at angles of attack up to approximately 16 deg, the total lift was substantially greater with the canard on than with the canard off. At angles of attack above 16 deg, the canard delayed the wing stall. Changing canard deflection had essentially no effect on the total lift, since the additional lift generated by the canard deflection was lost on the wing due to an increased downwash at the wing from the canard.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2897 , L-9096
    Format: application/pdf
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  • 10
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    Research on the sonic boom problem. Part 2: Flow field measurement in wind tunnel and calculation of second order F-function (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation has been carried out in a wind tunnel to test some of the results of Landahl's second order theory. The slender models consisted of a parabolic spindle, tested at M = 3, and a wing body configuration, suggested by Ferri, and tested at M = 2.7. The theory indicates that shock position and strength at an arbitrary distance can be calculated by means of near field measurements. The results show that this method is an appropriate one for simple bodies and for bodies with complicated geometries as well.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2340 , FFA-AU-621-PT-2
    Format: application/pdf
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