Numerical Solution of Three-Dimensional Unsteady Transonic Flow over Swept Wings

Borland, C. J.; Rizzetta, Donald P.; Yoshihar, H.

doi:10.2514/3.51079

Cited by 25 publications

(2 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…(1)(2)(3) and by the boundary conditions at the airfoil and wake. $| 0) should be known from a previous steady calculation.…”

Section: Iem Formulationmentioning

confidence: 99%

Calculation of unsteady transonic flows with shocks by field panel methods

Hounjet

1982

AIAA Journal

View full text Add to dashboard Cite

Fig. 2 Design chart to determine K B KB(W) f°r no afterbody. for negative afterbody from Fig. 3 K B(Hr} for negative afterbody as a function of afterbody length. (If you relabel the abscissa as R = P+2 9 this figure is applicable for all P and D with 0 " = 1, £/C r = -0.2, andB-+.Variation of K B(W) with respect to afterbody length is illustrated in Fig. 3 for the full range of B values. Note that for a fixed B the dependence of K B( W) on R is linear if R is less than or equal to unity. ConclusionClosed-form formulas have been presented for the interference factors K B(]V) for a body in the presence of a wing at supersonic speeds when a finite afterbody is introduced. In addition, formulas for K B(W) 's have been obtained for situations when the base of the body is forward of the trailing edge of the exposed root chord (negative afterbody). These formulas are valid subject to the restrictions inherent in the formulation of Ref. 2. RemarksSimilar to K B( W} , the body longitudinal center-of-pressure location can be determined in closed form. This work is currently in progress and will be reported later.

show abstract

“…(1)(2)(3) and by the boundary conditions at the airfoil and wake. $| 0) should be known from a previous steady calculation.…”

Section: Iem Formulationmentioning

confidence: 99%

Calculation of unsteady transonic flows with shocks by field panel methods

Hounjet

1982

AIAA Journal

View full text Add to dashboard Cite

show abstract

“…The following card statements (7)(8)(9)(10)(11) are optional and need only be input if values other than the default values are to be input.…”

Section: ) Boundary-layer Solutionmentioning

confidence: 99%

Numerical solution of three-dimensional unsteady transonic flow overwings including inviscid/viscous interactions

Rizzetta

Borland

1982

20th Aerospace Sciences Meeting

View full text Add to dashboard Cite

Two‐dimensional transonic aeroservoelastic computations in the time domain

Djayapertapa

Allen

Fiddes

2001

Numerical Meth Engineering

View full text Add to dashboard Cite

SUMMARYA computational method to perform transonic aeroelastic and aeroservoelastic calculations in the time domain is presented, and used to predict stability ( utter) boundaries of 2-D wing sections. The aerodynamic model is a cell-centred ÿnite-volume unsteady Euler solver, which uses an e cient implicit time-stepping scheme and structured moving grids. The aerodynamic equations are coupled with the structural equations of motion, which are derived from a typical wing section model. A control law is implemented within the aeroelastic solver to investigate active means of utter suppression via control surface motion. Comparisons of open-and closed-loop calculations show that the control law can successfully suppress the utter and results in an increase of up to 19 per cent in the allowable speed index. The e ect of structural non-linearity, in the form of hinge axis backlash is also investigated. The e ect is found to be strongly destabilizing, but the control law is shown to still alleviate the destabilizing e ect.

show abstract

Numerical Solution of Three-Dimensional Unsteady Transonic Flow over Swept Wings

Cited by 25 publications

References 16 publications

Calculation of unsteady transonic flows with shocks by field panel methods

Calculation of unsteady transonic flows with shocks by field panel methods

Numerical solution of three-dimensional unsteady transonic flow overwings including inviscid/viscous interactions

Two‐dimensional transonic aeroservoelastic computations in the time domain

Contact Info

Product

Resources

About