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  • 1
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    Prediction of vortex shedding from circular and noncircular bodies in supersonic flow (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An engineering prediction method and associated computer code NOZVTX to predict nose vortex shedding from circular and noncircular bodies in supersonic flow at angles of attack and roll are presented. The body is represented by either a supersonic panel method for noncircular cross sections or line sources and doublets for circular cross sections, and the lee side vortex wake is modeled by discrete vortices in crossflow planes. The three-dimensional steady flow problem is reduced to a two-dimensional, unsteady, separated flow problem for solution. Comparison of measured and predicted surface pressure distributions, flow field surveys, and aerodynamic characteristics is presented for bodies with circular and noncircular cross-sectional shapes.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3754 , NAS 1.26:3754 , NEAR-TR-307
    Format: application/pdf
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  • 2
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    Prediction of the vortex wake for noncircular missiles in supersonic flow (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Engineering prediction methods with the capability to calculate induced effects of lee-side separation vorticity associated with circular and noncircular missiles at high angles of attack in supersonic flow are compared. Methods of interest include a discrete vortex cloud technique, concentrated vortex models, and solutions of Euler's equations with specified separation. Comparison of measured and predicted surface pressure distributions and flow field surveys are presented for bodies with circular and elliptic cross sections. Two flow models for computing lee-side vortex-induced effects on control fins in the vicinity of the vortex field are examined, and suggestions regarding the appropriate flow model for specific situations are included.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0504
    Format: text
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  • 3
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    A correlation method to predict the surface pressure distribution on an infinite plate from which a jet is issuing (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A correlation method to predict pressures induced on an infinite plate by a jet issuing from the plate into a subsonic free stream was developed. The complete method consists of an analytical method which models the blockage and entrainment properties of the jet and a correlation which accounts for the effects of separation. The method was developed for jet velocity ratios up to ten and for radial distances up to five diameters from the jet. Correlation curves and data comparisons are presented for jets issuing normally from a flat plate with velocity ratios one to twelve. Also, a list of references which deal with jets in a crossflow is presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152160 , NEAR-TR-160
    Format: application/pdf
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  • 4
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    Data base for the prediction of inlet external drag (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented from a study to define and evaluate the data base for predicting an airframe/propulsion system interference effect shown to be of considerable importance, inlet external drag. The study is focused on supersonic tactical aircraft with highly integrated jet propulsion systems, although some information is included for supersonic strategic aircraft and for transport aircraft designed for high subsonic or low supersonic cruise. The data base for inlet external drag is considered to consist of the theoretical and empirical prediction methods as well as the experimental data identified in an extensive literature search. The state of the art in the subsonic and transonic speed regimes is evaluated. The experimental data base is organized and presented in a series of tables in which the test article, the quantities measured and the ranges of test conditions covered are described for each set of data; in this way, the breadth of coverage and gaps in the existing experimental data are evident. Prediction methods are categorized by method of solution, type of inlet and speed range to which they apply, major features are given, and their accuracy is assessed by means of comparison to experimental data.
    Keywords: AERODYNAMICS
    Type: AGARD Subsonic(Transonic Configuration Aerodyn.; 23 p
    Format: text
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  • 5
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    Computer programs to predict induced effects of jets exhausting into a crossflow (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A user's manual for two computer programs was developed to predict the induced effects of jets exhausting into a crossflow. Program JETPLT predicts pressures induced on an infinite flat plate by a jet exhausting at angles to the plate and Program JETBOD, in conjunction with a panel code, predicts pressures induced on a body of revolution by a jet exhausting normal to the surface. Both codes use a potential model of the jet and adjacent surface with empirical corrections for the viscous or nonpotential effects. This program manual contains a description of the use of both programs, instructions for preparation of input, descriptions of the output, limitations of the codes, and sample cases. In addition, procedures to extend both codes to include additional empirical correlations are described.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166591 , NAS 1.26:166591 , NEAR-TR-328
    Format: application/pdf
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  • 6
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    Data base for the prediction of airframe/propulsion system interference effects (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Supersonic tactical aircraft with highly integrated jet propulsion systems were investigated. Primary attention was given to those interference effects which impact the external aerodynamics of the aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-152316 , NEAR-TR-187
    Format: application/pdf
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  • 7
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    A correlation method to predict the surface pressure distribution of an infinite plate or a body of revolution from which a jet is issuing (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A correlation method to predict pressures induced on an infinite plate by a jet exhausting normal to the plate into a subsonic free stream was extended to jets exhausting at angles to the plate and to jets exhausting normal to the surface of a body revolution. The complete method consisted of an analytical method which models the blockage and entrainment properties of the jet and an empirical correlation which accounts for viscous effects. For the flat plate case, the method was applicable to jet velocity ratios up to ten, jet inclination angles up to 45 deg from the normal, and radial distances up to five diameters from the jet. For the body of revolution case, the method was applicable to a body at zero degrees angle of attack, jet velocity ratios 1.96 and 3.43, circumferential angles around the body up to 25 deg from the jet, axial distances up to seven diameters from the jet, and jet-to-body diameter ratios less than 0.1.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152345 , NEAR-TR-211
    Format: application/pdf
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  • 8
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    Evaluation of methods for prediction of propulsion system drag (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of a study directed toward compilation of a theoretical and experimental data base covering inlet/airframe and nozzle/afterbody integration are described, with the major emphasis on the evaluation of the adequacy for preliminary design purposes of the data base for afterbody/propulsion system interference effects. Prediction methods that exist for afterbody/airframe interference effects are evaluated with respect to the requirements of breadth, ease of application and accuracy that are important for preliminary design.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-1148 , AIAA, SAE, and ASME, Joint Propulsion Conference; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV
    Format: text
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  • 9
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    Component aerodynamic characteristics of banked cruciform missiles with arbitrary control deflections (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A comprehensive computer code has been developed for the prediction of the static aerodynamic characteristics of cruciform wing-body combinations with one or two sets of fins. The code may be used for subsonic, transonic, and supersonic speeds. Arbitrary bank angles and control deflections are allowed. The present version of the code may be used for angles of attack up to 20 deg. The code computes the forces and moments acting on each component of the missile including the effects of vortices shed by the body and fins. Comparisons between experiment and theory indicate good agreement for longitudinal characteristics and fair to good agreement for lateral characteristics.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 77-1153 , Atmospheric Flight Mechanics Conference; Aug 08, 1977 - Aug 10, 1977; Hollywood, FL
    Format: text
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  • 10
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    User's Manual for Space-shuttle Computer Programs (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Keywords: GENERAL
    Type: NASA-CR-137862 , NEAR-TR-110
    Format: application/pdf
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