A planar nonlinear missile aeroprediction code for all Mach numbers

Moore, Frank G.; Hymer, T.; McInville, R. M.

doi:10.2514/6.1994-26

Cited by 8 publications

(5 citation statements)

References 4 publications

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“…The high-AOA canard or wing-shed vortex and control-deflection effects can be approximately modeled with empirical experiments compared to other databases. 1 Note at the outset, however, that by extending the flow computations into the highly nonlinear, may-not-be-well-behaved region of Fig. 1, the accuracy available in the AP93 for the a < 30-deg cases may be somewhat degraded.…”

Section: Discussion Of Nonlinear Missile Aerodynamicsmentioning

confidence: 95%

“…For Mach numbers approaching 2 and greater, past attempts have shown the methods used in AP93 to be directly applicable at higher AOA with few changes. 1 However, these methods were based on empirical approximations to the nonlinearities occurring to the wing, body, and wing-body interference based on a component buildup database. 8 ' 9 This database had various size wings with a single body.…”

Section: Discussion Of Nonlinear Missile Aerodynamicsmentioning

confidence: 99%

“…1. The center of pressure of the interference force on the body is assumed to occur at the same point as computed by linear theory or slender-body theory (dependent on Mach number and aspect ratio primarily), also as done in Ref.…”

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confidence: 99%

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Aeroprediction code for angles of attack above 30 degree

Moore

McInville

Hymer

1996

Journal of Spacecraft and Rockets

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The U.S. Naval Surface Warfare Center Dahlgren Division aeroprediction code has been extended to angles of attack greater than 30 deg. To accomplish this, several databases were used to approximate the nonlinearities in individual missile component aerodynamics. Theoretical aerodynamic methods were used at small angles of attack. The new semiempirical model was then applied to several configurations and the empirical constants fine tuned so as to minimize some of the errors associated with wind-tunnel measurements of component aerodynamics at high angles of attack. New and improved technology developed includes 1) extension of the wing-body and body-wing interference factor methodology above angle of attack of 30 deg for both zero and nonzero control deflections and 2) refinements in body-alone normal force and center-of-pressure prediction to account for Reynolds number, and transonic and asymmetrically shed body vortices. All methodology is developed for the * = 0-deg (or fins in plus) roll orientation. Comparison of the new methodology to several cases outside the databases on which the methodology was developed appears to indicate the average accuracy goals of ±10% on normal force and ±4% of body length on center of pressure were maintained for the higher angles of attack. NomenclatureA P = planform area of the body or wing in the crossflow plane, ft 2 A re f = reference area (maximum cross-sectional area of body, if a body is present, or planform area of wing, if wing alone), ft 2 A w , S w = planform area of wing in crossflow plane, ft 2 A wetted = area of body or wing that flow touches 0o, 0i, 02,03,04 = constants used in nonlinear wing-alone model b = wing span (not including body), ft CA = axial force coefficient CA B , CA F , CA W = base, skin-friction, and wave components, respectively, of axial force coefficient CD C = crossflow drag coefficient C F£ , CF T -laminar and turbulent skin friction coefficients, respectively CM = pitching moment coefficient (based on reference area and body diameter, if body present, or mean aerodynamic chord, if wing alone) C N = normal force coefficient C Ns -normal force coefficient of body alone Cff L = linear component of normal force coefficient CN NL = nonlinear component of normal force coefficient CN T(V) = negative normal force coefficient component on tail due to wing or canard-shed vortex C Nw = normal force coefficient of wing alone C Na = normal force coefficient derivative d = body diameter, ft = rate at which K W ( B ) or K B ( W ) decreases = dimensionless empirical factors used in nonlinear models of k W ( B ) and C# r(v) to approximate effects resulting from high angle of attack or control deflection fw, fr = lateral location of wing or tail vortex (measured in feet from body centerline) : = tail interference factor

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Section: Discussion Of Nonlinear Missile Aerodynamicsmentioning

confidence: 95%

Section: Discussion Of Nonlinear Missile Aerodynamicsmentioning

confidence: 99%

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Aeroprediction code for angles of attack above 30 degree

Moore

McInville

Hymer

1996

Journal of Spacecraft and Rockets

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“…The interactions between canard and other elements are also hard to predict well in initial design. Although some corrected theoretical and semi-empirical methods developed by previous studies [4][5][6][7] can successfully predict canard-wing and canard-body interaction effect on static aerodynamic force and moment increment for some axisymmetric canard configurations, it has difficulty in expanding to predict some nonaxisymmetric configurations and has to depend on specific experiment data at some speeds. Those methods also fail to predict the stability and control characteristics variation well when canard reflects, which is very important to the control system design.…”

Section: Introductionmentioning

confidence: 99%

Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

2009

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This paper presents an aerodynamic study for a target unmanned air vehicle with controlled canard, at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The results of semi-empirical method (DATCOM), computational fluid dynamics (CFD) were compared with wind tunnel tests to evaluate perdition accuracy. Here DATCOM shows big discrepancy in pitching-moment coefficient; the CFD estimation of static aerodynamic force and moment agree well with wind tunnel data. An analysis was focused on the longitudinal data for complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a thick canard (NACA0012) and the final improved configuration with a thin canard (NACA0007) were reviewed. It is proved that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated.

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“…The interactions between canard and other elements are also hard to predict well in initial design. Although some previous corrected theoretical and semi-empirical methods [4][5][6][7][8] can successfully predict canard-wing and canard-body interaction effect on static aerodynamic force and moment increment for some axisymmetric canard configurations, it has difficulty in expanding to predict some non-axisymmetric configurations and has to depend on specific experiment data at some speeds. Those methods also fail to predict the stability and control characteristics variation well when canard reflects, which is very important to the control system design.…”

Section: Introductionmentioning

confidence: 99%

An experimental study of controlled canard for a solid rocket motor based unmanned air vehicle

Xie

Liu

2010

2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics

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An aerodynamic study is presented for controlled canard configuration of a target unmanned air vehicle (TUAV) at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The analysis was focused on the longitudinal wind tunnel test data for learning complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a NACA0012 canard and the improved configuration with a NACA0007 canard were reviewed and discussed. The experiments prove that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated. The flight experiment shows that the final improved controlled canard configuration satisfies the request of the control system.

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A planar nonlinear missile aeroprediction code for all Mach numbers

Cited by 8 publications

References 4 publications

Aeroprediction code for angles of attack above 30 degree

Aeroprediction code for angles of attack above 30 degree

Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

An experimental study of controlled canard for a solid rocket motor based unmanned air vehicle

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