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  • 1
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    The equivalent angle-of-attack concept for engineering analysis (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An account is given of methods for the estimation of a wing-body-tail missile configuration's aerodynamic performance by means of the 'component buildup' method, in which the overall aerodynamic loads for an airframe are built up from the assumed characteristics of isolated airframe components and then subjected to additional loads generated by component interference. Attention is given to the cases of missile airframes in steady flow at arbitrary angles of attack and bank; the unifying thread of the present treatment is slender body theory, together with its nonlinear extensions through the equivalent angle-of-attack concept. The estimation of the forces and moments acting on each of the fins is emphasized, so that control cross-coupling effects as well as longitudinal and lateral directional effects can be determined.
    Keywords: AERODYNAMICS
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  • 2
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    Extension of equivalent angle-of-attack method for nonlinear flowfields (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 304-308
    Format: text
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  • 3
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    Comprehensive missile aerodynamics programs for preliminary design (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 12, p. 1851, Accession no. A82-27106
    Keywords: AERODYNAMICS
    Type: (ISSN 0022-4560)
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  • 4
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    Equivalent angle-of-attack method for estimating nonlinear aerodynamics of missile fins (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2971, Accession no. A82-39113
    Keywords: AERODYNAMICS
    Type: (ISSN 0022-4560)
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  • 5
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    Similarity for high angle-of-attack subsonic/transonic slender-body aerodynamics (1988)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The work of Sychev (1960) is extended to sharp-edged wings and smooth bodies. A simple fit to the correlations based on the Polhamus (1966) suction analogy is shown for several affine families of bodies with elliptical cross sections. The results suggest that simple models for nonlinear subsonic/transonic flows over not-so-slender wings and bodies can be obtained from a combination of well-known linear-theory models for the attached flow and slender-body concepts for the vortical flow.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0216
    Format: text
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  • 6
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    Aerodynamic characteristics of missile control fins in nonlinear flow fields (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Recent experimental results show that the control effectiveness of a missile fin in supersonic flow at moderate-to-high angles of attack is a strong nonlinear function of free-stream Mach number, body incidence angle, fin bank angle and fin deflection angle. Analysis of the experimental results using an Euler finite-difference computer code with flow separation together with the equivalent angle-of-attack concept indicates that the observed nonlinearities are due to the variation of local dynamic pressure and local Mach number around the missile body alone. The nonlinearities are shown to be a strong source of control cross-coupling for high Mach number, high angle-of-attack combinations. The analysis suggests a relatively simple yet comprehensive approach for accurately accounting for these nonlinear effects.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-2083
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  • 7
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    Survey of engineering computational methods and experimental programs for estimating supersonic missile aerodynamic characteristics (1982)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: This paper presents a survey of engineering computational methods and experimental programs used for estimating the aerodynamic characteristics of missile configurations. Emphasis is placed on those methods which are suitable for preliminary design of conventional and advanced concepts. An analysis of the technical approaches of the various methods is made in order to assess their suitability to estimate longitudinal and/or lateral-directional characteristics for different classes of missile configurations. Some comparisons between the predicted characteristics and experimental data are presented. These comparisons are made for a large variation in flow conditions and model attitude parameters. The paper also presents known experimental research programs developed for the specific purpose of validating analytical methods and extending the capability of data-base programs.
    Keywords: AERODYNAMICS
    Type: Symposium on Missile Aerodynamics; Sept. 20-22, 1982; Trondheim; Norway
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  • 8
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    Uncertainty in Computational Aerodynamics (2003)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: An approach is presented to treat computational aerodynamics as a process, subject to the fundamental quality assurance principles of process control and process improvement. We consider several aspects affecting uncertainty for the computational aerodynamic process and present a set of stages to determine the level of management required to meet risk assumptions desired by the customer of the predictions.
    Keywords: Aerodynamics
    Type: AIAA Paper 2003-0409 , 41st AIAA Aerospace Sciences Meeting and Exhibit; Jan 06, 2003 - Jan 09, 2003; Reno, NV; United States
    Format: application/pdf
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  • 9
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    Comprehensive missile aerodynamics programs for preliminary design (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Two different classes of missile aeroprediction programs have been recently developed. The first class of programs provides rapid engineering predictions and includes MISSILE1 and MISSILE2 applicable to missile configurations with axisymmetric bodies. The second class of programs consists of the DEMON series, including a simplified version NSWCDM, designed to calculate detailed loadings acting on supersonic missiles which may have non-circular body cross sections. Both classes account for high angles of attack and track vortices from canard or wing section to the tail section. Extensive comparisons with experimental data are presented including nonlinear effects of canard control.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0375 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
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  • 10
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    Component aerodynamic characteristics of banked cruciform missiles with arbitrary control deflections (1977)
    In:  Other Sources
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    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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