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  • 1
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    DESIGN OF SUPERSONIC INLETS (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: This FORTRAN IV computer program which incorporates the method of characteristics was written to assist in the design of supersonic inlets. There were two objectives: (1) to study a greater variety of supersonic inlet configurations and (2) to reduce the time required for trial-and-error procedures to arrive at optimum inlet design. The computer program was written with the intention of being able to construct a variety of inlet configurations by interchanging specific subroutines. In this manner, greater flexibility of choice was attained, and the time required to program a specific inlet configuration was greatly reduced. The second objective was accomplished by a reformulation of the boundary value problem for hyperbolic equations. By this reformulation of the boundary data, the engineering design quantities, throat Mach number and flow angle, were introduced as direct input quantities to the computer program. As a consequence of introducing the engineering parameters as input, the computer program will calculate the surface contours required to satisfy the specific throat conditions. Inviscid flow is assumed and the method used to calculate the inlet contour results in minimum distortion to the flow in the throat. This program was developed on an IBM 7094.
    Keywords: AERODYNAMICS
    Type: LEW-10868
    Format: text
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  • 2
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    Optimization of supersonic inlets using the method of characteristics (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Method of characteristics for computerized design of optimal supersonic inlets
    Keywords: AERODYNAMICS
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 569-581
    Format: text
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  • 3
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    Improved interactive calculation procedure for supersonic flows (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: An interactive numerical procedure has been developed for supersonic viscous flows (either two-dimensional or axisymmetric configurations). The flow field is divided into two regions: (1) an inner region which is highly viscous and mostly subsonic, and (2) an outer region where the flow is supersonic and in which viscous effects are small, but not negligible. This paper presents a detailed description of: I. Outer Region - numerical solution obtained by applying the method of characteristics to a system of equations which includes viscous and conduction transport terms only normal to the streamlines; II. Inner Region - treated by a system of equations of the boundary-layer type that includes higher order effects, such as longitudinal and transverse curvature and normal pressure gradients (equations are coupled and solved simultaneously in physical coordinates, using an implicit finite-difference scheme); III. Interactive Procedure - in the interaction mode, the two regions are coupled iteratively along a matching line, where the Mach number is of the order of 1.2.
    Keywords: AERODYNAMICS
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  • 4
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    Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7
    Keywords: AERODYNAMICS
    Type: NACA-RM-E58E16
    Format: application/pdf
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  • 5
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    Investigation of Inlet Control Parameters for an External-internal-compression Inlet from Mach 2.1 to 3.0 (1958)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg. When the inlet was unstarted, an erroneous signal was obtained from the normal-shock control through most of the starting cycle that prevented the inlet from starting. Therefore, it was necessary to over-ride the normal-shock control signal and not allow the control to position the terminal shock until the spike was positioned.
    Keywords: AERODYNAMICS
    Type: NACA-RM-E58G08
    Format: application/pdf
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  • 6
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    Shuttle Space Suit: Fabric/LCVG Model Validation (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-11
    Description: A detailed space suit computational model is being developed at the Langley Research Center for radiation exposure evaluation studies. The details of the construction of the space suit are critical to estimation of exposures and assessing the risk to the astronaut on EVA. Past evaluations of space suit shielding properties assumed the basic fabric layup (Thermal Micrometeoroid Garment, fabric restraints, and pressure envelope) and LCVG could be homogenized as a single layer overestimating the protective properties over 60 percent of the fabric area. The present space suit model represents the inhomogeneous distributions of LCVG materials (mainly the water filled cooling tubes). An experimental test is performed using a 34-MeV proton beam and high-resolution detectors to compare with model-predicted transmission factors. Some suggestions are made on possible improved construction methods to improve the space suit s protection properties.
    Keywords: Man/System Technology and Life Support
    Type: Radiation Protection Studies of International Space Station Extravehicular Activity Space Suits; See also Doc ID 20040031719; 127-134; NASA/TP-2003-212051
    Format: application/pdf
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  • 7
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    Numerical calculation of transonic boattail flow (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A viscid-inviscid interaction procedure for the calculation of subsonic and transonic flow over a boattail was developed. This method couples a finite-difference inviscid analysis with an integral boundary-layer technique. Results indicate that the effect of the boundary layer is as important as an accurate inviscid method for this type of flow. Theoretical results from the solution of the full transonic-potential equation, including boundary layer effects, agree well with the experimental pressure distribution for a boattail. Use of the small disturbance transonic potential equation yielded results that did not agree well with the experimental results even when boundary-layer effects were included in the calculations.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7984 , E-8065
    Format: application/pdf
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  • 8
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    Correlation of boundary layer stability analysis with flight transition data (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Recently, NASA completed a boundary-layer transition flight test on an F-14 aircraft which has variable-sweep capability. Transition data were acquired for a wide variety of sweep angles, pressure distributions, Mach numbers, and Reynolds numbers. In this paper, the F-14 flight test is briefly described and N-factor correlations with measured transition locations are presented for one of two gloves flown on the F-14 wing in the flight program; a thin foam and fiberglass glove which provided a smooth sailplane finish on the basic F-14, modified NACA 6-series airfoil. For these correlations, an improved linear boundary-layer stability theory was utilized that accounts for compressibility and surface and streamline curvature effects for the flow past swept wings.
    Keywords: AERODYNAMICS
    Type: IUTAM Symposium on Laminar-Turbulent Transition; Sept. 11-15, 1989; Toulouse; France
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  • 9
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    Strong interaction associated with transonic flow past boattailed afterbodies (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The problem of transonic flow past boattails was studied with the aid of numerical relaxative schemes. Preliminary calculations were restricted to a particular model configuration which had been tested in an experimental program. It was found that the full potential equation must be considered in the study. The final results agreed very well with the experimental data. The investigation illustrates the strong interaction character of the transonic flow past a boattailed afterbody.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Jan. 197
    Format: text
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  • 10
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    Three-dimensional viscous design methodology for advanced technology aircraft supersonic inlet systems (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A broad program to develop advanced, reliable, and user oriented three-dimensional viscous design techniques for supersonic inlet systems, and encourage their transfer into the general user community is discussed. Features of the program include: (1) develop effective methods of computing three-dimensional flows within a zonal modeling methodology; (2) ensure reasonable agreement between said analysis and selective sets of benchmark validation data; (3) develop user orientation into said analysis; and (4) explore and develop advanced numerical methodology. Previously announced in STAR as N84-13190
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0194
    Format: text
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