Effects of angle of attack and nose bluntness on the hypersonic flowover cones

Cleary, J. W.

doi:10.2514/6.1966-414

Cited by 13 publications

(2 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The isothermal computation assumed a 1000R wall temperature, which is near the mean The measurements show an overshoot in the pitot pressure which is not present in the computations. Such an overshoot has been observed before for blunt cones or at angle of attack [61], but the author is not aware of any reliable experimental data showing such an overshoot for a sharp cone at zero angle of attack. The obvious experimental causes might include small residual angles of attack or a bent cone tip.…”

Section: Previous Computational Comparisonsmentioning

confidence: 65%

Hypersonic laminar instability on round cones near zero angle of attack

Schneider

2001

39th Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

Reliable predictions for hypersonic laminarturbulent transition will have to be based on simulation of the transition mechanisms. Accurate simulation of the second-mode instability-wave growth on a round cone at zero angle of attack would be a significant step toward this goal. Hypersonic stability experiments in this geometry are reviewed, and three are selected. Extensive and previously unpublished data from Stetson's sharp and blunt cone experiments are reported. Approximate computations were carried out using inviscid-boundary-layer and e N methods. The experimental results are compared to previous high-accuracy computations and to the present approximate computations. Quantitative agreement is at present insufficient for reliable e N predictions. The difficulties with both experiment and computation are described.

show abstract

Section: Previous Computational Comparisonsmentioning

confidence: 65%

Hypersonic laminar instability on round cones near zero angle of attack

Schneider

2001

39th Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

show abstract

“…Even in the more sophisticated computations of the entropy swallowing, an effect such as the change in shear due to the dynamic pressure overshoot on a cone, described by Cleary,22 is not considered. The predictions are based solely on edge unit Reynolds number and Mach number.…”

Section: Effect Of Small Nose Bluntness On Transitionmentioning

confidence: 99%

Correlation of Attitude Effects on Slender Vehicle Transition

Ericson

1974

AIAA Journal

View full text Add to dashboard Cite

The effects of boundary-layer transition on the motion of a slender re-entry body are large. In order to predict how transition can cause these large effects on slender vehicle stability and trim characteristics, one has to know how the vehicle attitude influences the transition geometry. Contrary to general expectations, a correlation study has shown that the percentage change from the a = 0 transition geometry can be defined simply as a function of the relative vehicle attitude (oc/0 c ). The windward side forward transition movement on a blunted cone is guided by entropy impingement (and associated entropy swallowing effects) in a manner that can be predicted using transition measurements at a = 0 in combination with embedded Newtonian theory. The leeward side forward transition movement is completely dictated by boundary layer crossflow effects and can be defined using slender cone data obtained in different ground facilities.= axial body coordinate from sharp cone apex x 0 = start of conic frustum on blunted cone a = angle of attack A = difference 9 C = cone half-angle v = kinematic viscosity p = air density X = hypersonic similarity parameter (see Fig. 4) Subscripts AW = adiabatic wall B, N = base and nose, respectively EW = entropy wake impingement = inviscid flow = entropy swallowing = transition = wall condition i SW TR W 0 oo = freestream conditions IntroductionT HE effect of boundary-layer transition on high-performance re-entry bodies has been studied by the missile industry for a long time. The early concern was with the increased aft body ablation when transition moves forward of the base, 1 as it could be shown experimentally 2 and theoretically 3 that the associated increased ablation rates adversely affect the vehicle damping and can lead to dynamic instability. Later it was shown both experimentally 4 and theoretically 5 that in addition to the above effect of symmetric transition, the effect of asymmetric transition on vehicle dynamics is possibly even stronger.During recent times a great volume of experimental results has become available for the combined effects of crossflow and Presented as Part I of AIAA Paper 73-126 at the AIAA llth

show abstract

Numerical investigation of the three-dimensional laminar boundary layer with coupled heat transfer

Zinchenko

Fedorova

1988

J Appl Mech Tech Phys

View full text Add to dashboard Cite

Effects of angle of attack and nose bluntness on the hypersonic flowover cones

Cited by 13 publications

References 0 publications

Hypersonic laminar instability on round cones near zero angle of attack

Hypersonic laminar instability on round cones near zero angle of attack

Correlation of Attitude Effects on Slender Vehicle Transition

Numerical investigation of the three-dimensional laminar boundary layer with coupled heat transfer

Contact Info

Product

Resources

About