In the present article, the effects of three important flow control techniques, i.e. control by strakes, jets, and flares, on the aerodynamic characteristics and performance of a number of body configurations at high speeds are reviewed. The results are based on previous studies conducted by the author in a hypersonic gun tunnel at a Mach number of 8.2 and a Re∞/m=9 200 000. Air was used as the working gas. The tests employed schlieren photography to study the overall flow field. Quantitative studies have been made by pressure measurements. The forces were measured with a three-component balance equipped with semiconductor strain gauges. The surface flow was studied using the oil-dot technique.
KontisK.StolleryJ. L.Incipient separation on flared bodies at hypersonic speeds. Aeronaut. J., 1999, 103, 405–414.
2.
BabinskyH.EdwardsJ. A.On the incipient separation of a turbulent hypersonic boundary layer. Aeronaut. J., 1996, 100, 209–214.
3.
AppelsC.RichardsB. E.Incipient separation of a compression turbulent boundary layer. AGARD CP-168 1975.
4.
SpaidF. W.FrishettJ. L.Incipient separation of a supersonic, turbulent boundary layer, including effect of heat transfer. AIAA J., 1972, 10, 915–922.
5.
Van DykeM. D.The elliptic cone as a model for nonlinear supersonic flow theory. J. Fluid Mech., 1956, 1(Part 1), 1–15.
6.
PalkoR. L.RayA. D.Pressure distribution and flow visualization tests of a 1.5 elliptic cone at Mach 10. Arnold Engineering Development Center, AEDC/TR-63/163, August 1963.
7.
GravesE. B.Aerodynamic characteristics of a monoplanar missile concept with bodies of circular and elliptical cross sections. NASA TM-74079, December 1977.
8.
KontisK.Hypersonic flow control effectiveness of a flare body combination at hypersonic speeds. Trans. Jpn. Soc. Aeronaut. Space Sci., 2004, 47(164), 116–123.
9.
Krasil'nikovA. V.ShmanenkovV. N.Investigation of dynamic stability regimes for axisymmetric bodies in supersonic flow. Fluid Dyn., 2000, 35(5), 756–760.
10.
ReggioriA.Lift and drag of wing-cone configuration in hypersonic flow. AIAA J., 1971, 9(4), 744–745.
11.
ChaudhryS. R.QinN.RichardsB. E.Hypersonic viscous flows around Waverider configurations. In Proceedings of the First International Hypersonic Waverider Symposium, University of Maryland, Maryland, USA, 1990, pp. 33–41.
12.
HouwinkR.RichardsB. E.Experimental study of a high lift reentry vehicle configuration. AIAA J., 1973, 11(5), 749–751.
13.
LevinskyE. S.WeiM. H. Y.Non-linear lift and pressure distribution of slender conical bodies with strakes at low speeds. NASA/CR-1202, October 1968.
14.
SpaidF. W.CasselL. A.Aerodynamic interference induced by reaction controls. AGARD AG-173, December 1973.
15.
PeakeD.TobakM.Three-dimensional interactions and vortical flows with emphasis on high speeds. AGARD AG-252, July 1980.
16.
QinN.RedlichA.Massively separated flows due to transverse sonic jet in laminar hypersonic stream. Shock Waves, 1999, 9(2), 87–93.
17.
KontisK.StolleryJ. L.Control effectiveness of a jet-slender body combination at hypersonic speeds. J. Spacecr. Rockets, 1997, 34, 762–768.
18.
KontisK.Jet control effectiveness studies on a flat-plate body at hypersonic speeds. Trans. Jpn. Soc. Aeronaut. Space Sci., 2004, 47(164), 131–137.
19.
InoueY.HayashiA. K.FujiwaraT.MiyakeS.KatsuraharaT.Numerical analysis of RCS jet in hypersonic flights. Trans. SAE, 1991, 100(2), no. 1, 2263–2270.
20.
MallinsonS. G.ReizesJ. A.HillierR.The interaction between a compressible synthetic jet and a laminar hypersonic boundary layer. Flow Turbul. Combust., 2001, 66(1), 1–21.
21.
SrinivasanR.BowersoxR. D. W.Characterization of flow structures and turbulence in hypersonic jet interaction flowfields. In 43rd AIAA Aerospace Sciences Meeting and Exhibit - Meeting Papers, Reno, Nevada, USA 2005, pp. 3431–3446.
KuehnD. M.Laminar boundary-layer separation induced by flares on cylinders with highly cooled boundary layers at a Mach number of 15. NASA TN D-2610, 1965.
24.
KuehnD. M.Turbulent boundary-layer separation induced by flares on cylinders at zero angle of attack. NASA TR-R-117, 1961.
25.
KuehnD. M.Laminar boundary-layer separation induced by flares on cylinders at zero angle of attack. NASA TR-R-146, 1962.
26.
GrayJ.Investigation of the effect of flare and ramp angle on the upstream influence of laminar and transitional reattaching flows from Mach 3 to 7. AEDC TR-66-190, 1967.
27.
GinouxJ. J.On some properties of reattaching laminar and transitional high speed flows. VKI TN-53 1969.
28.
NeedhamD. A.StolleryJ. L.Boundary layer separation in hypersonic flow. AIAA-66-455, 1966.
29.
IngerG. R.Scaling of incipient separation in high speed laminar flows. AIAA-93-3435, 1993.
30.
ColemanG. T.StolleryJ. L.Heat transfer from hypersonic turbulent flow at a wedge compression corner. J. Fluid Mech., 1972, 56(2), 741–752.
31.
ElfstromG. M.Turbulent separation in hypersonic flow. IC Aero Report 71–16 1971.
32.
ColemanG. T.A study of hypersonic boundary layers over a family of axisymmetric bodies at zero incidence. IC Aero Report 73–06 1973.
SimpkinsP.Hypersonic interactions about a slender cone induced by radial mass injection. In Hypersonic boundary layers and flow fields, AGARD CP-30, 1968 (NATO-AGARD, VKI, Brussels, Belgium).
35.
KumarD.StolleryJ. L.Hypersonic jet control effectiveness. AIAA-95-6066, 1995.
36.
VermeulenJ. P.SimeonidesG.Parametric studies of shockwave boundary layer interactions in two-dimensional compression corners at Mach 6. VKI TN-181, 1992.
37.
EdwardsC. L. W.AndersJ. B.Low density, leading edge bluntness and ablation effects on wedge induced laminar boundary layer separation at moderate enthalpies in hypersonic flows. NASA TN D-4829, 1968.
38.
CoetM. C.DeleryJ.ChanetzB.Experiments on shock wave-boundary layer interaction at high Mach number with entropy layer effect. In Aerothermochemistry of spacecraft and associated hypersonic flows, Proceedings of the IUTAM Symposium, Marseilles, France, 1992, pp. 234–239 (International Union of Theoretical and Applied Mechanics).
39.
TownsendJ. C.The effects of leading edge bluntness and ramp deflection angle on laminar boundary layer separation in hypersonic flow. NASA TN D-3290, 1966.
40.
HoldenM. S.MoselleJ. R.A database of aerothermal measurements in hypersonic flow for CFD validation. AIAA-92-4023, 1992.
41.
StolleryJ. L.MaullD. J.BelcherD. A.The Imperial College hypersonic gun tunnel. J. R. Aeronaut. Soc., 1960, 64, 634–641.
42.
NeedhamD. A.Progress report on the Imperial College hypersonic gun tunnel. IC Aero TN-118 1963.
43.
KontisK.QinN.StolleryJ. L.EdwardsJ. A.Hypersonic Performance of a lifting elliptic cone with and without strakes. J. Spacecr. Rockets, 2000, 37, 21–27.
44.
KontisK.Projectile aerodynamics: Measurement and computation. PhD Thesis, Cranfield University, 1997.
45.
OpatowskiT.An experimental study of the flow around and the forces developed by hypersonic lifting vehicles. PhD Thesis, University of London, 1967.
46.
ColemanG. T.Hypersonic boundary layer studies. PhD thesis, University of London, 1973.
47.
OsherS.ChakravathyS. R.Upwind schemes and boundary conditions with applications to Euler equations in general co-ordinates. J. Comput. Phys., 1983, 50, 447–481.
48.
BaldwinB. S.LomaxH.Thin-layer approximation and algebraic turbulence model for separated turbulent flows. AIAA 78–257, 1978.
49.
DeganiD.SchiffL. B.Computation of turbulent supersonic flows around pointed bodies having crossflow separation. J. Comput. Phys., 1986, 66, 173–196.
50.
QinN.ScribaK. W.RichardsB. E.Shock-shock, shock-vortex interaction and aerodynamic heating in hypersonic corner flow. Aeronaut. J., 1991, 95(945), 152–169.
51.
VigneronY. C.RakichJ. V.TannehillJ. C.Calculation of supersonic viscous flow over delta wings with sharp leading edges. AIAA 78–1137, 1978.
52.
BirchT. J.QinN.JinX.Computation of supersonic viscous flows around a slender body at incidence. AIAA 94–1938, 1994.
53.
EdwardsJ. A.RoperJ. J.A computational assessment of static and dynamic coefficients for the H3 hypervelocity projectile. AIAA 97–0640, 1997.
54.
EisemanP. R.Grid generation for fluid mechanics computations. Ann. Rev. Fluid Mech., 1985, 17, 487–522.
55.
KontisK.StolleryJ. L.EdwardsJ. A.Control effectiveness of strake-slender body combinations at hypersonic speeds. Trans. Jpn. Soc. Aeronaut. Space Sci., 2000, 43(139), 181–185.
56.
RoseW. C.PageR. J.ChildsM. E.Incipient separation pressure rise for a Mach 3.8 turbulent boundary layer. AIAA J., 1973, 11(5), 761–764.
57.
DruggeG.An experimental investigation of the influence of strong adverse pressure gradients on turbulent boundary layers at supersonic speeds. FFA Report 47 1953.
58.
KesslerW. C.ReillyJ. F.MockapetrisL. J.Supersonic turbulent boundary layer interaction with an expansion ramp and compression corner. McDonnell Douglas Report, MDC E0264 1970.
59.
LawH. C.Supersonic turbulent boundary layer separation measurements at Reynolds numbers of 107 to 108. AIAA-73-665, 1973.
SterrettJ. R.EmeryJ. C.Experimental separation studies for two-dimensional wedges and curved surfaces at Mach numbers of 4.8 to 6.2. NASA TN D-1014, 1962.
