Crossflow Instability on a Wedge-Cone at Mach 3.5

Beeler, George B.; Wilkinson, Stephen; Balakumar, Ponnampalam; McDaniel, Keith

doi:10.2514/6.2012-2825

Cited by 7 publications

(4 citation statements)

References 9 publications

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“…He noted that the effect of freestream turbulence on transition location decreased substantially with increasing crossflow. Recent experiments by Beeler et al [14] confirmed the presence of stationary crossflow vortices on a wedge-cone model in a Mach 3.5 quiet tunnel. Future experiments will focus on determining if traveling modes are also present.…”

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confidence: 71%

Traveling Crossflow Instability for the HIFiRE-5 Elliptic Cone

Borg

Kimmel

Stanfield

2015

Journal of Spacecraft and Rockets

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A 38.1%-scale model of the Hypersonic International Flight Research Experimentation Program's Flight Five 2:1 elliptic cone flight vehicle was used to investigate the traveling crossflow instability in a Mach 6 quiet wind tunnel. Traveling crossflow waves were detected with pressure sensors mounted flush with the model surface. The crossflow instability phase speed and wave angle were calculated from the cross spectra of the three pressure sensors. Both quantities showed good agreement with linear stability theory. Duplicate runs at the same initial conditions showed excellent repeatability in traveling crossflow wave properties. Traveling crossflow waves in quiet flow showed very low levels of nonlinear interactions. No traveling crossflow waves were observed for any Reynolds number for elevated freestream noise levels, but transition occurred for a much lower Reynolds number than in quiet flow. Due to the lack of nonlinear growth in quiet flow and the absence of traveling crossflow waves in noisy flow, it appeared that the traveling crossflow instability was not the primary transition mechanism on the model for quiet or noisy flow in this wind tunnel. Nomenclature c r = phase speed, m∕s E = expected value operator f = frequency, kHz I = imaginary part of complex number p 0 = fluctuating component of pressure, Pa R = real part of complex number Re = freestream unit Reynolds number, 1∕m S = cross spectrum s = Fourier transform of signal s T = temperature or record length, K or s x = Streamwise coordinate, mm y = spanwise coordinate, mm γ 2 = coherence η = circumferential coordinate ξ = axial coordinate σ = standard deviation τ = time delay, μs ϕ = phase of cross spectrum, deg Ψ = wave angle, angle between phase velocity and axial direction, deg Subscripts aw = evaluated at adiabatic wall conditions stat = static conditions w = evaluated at wall conditions Superscripts = complex conjugate 0 = rotated coordinate system

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confidence: 71%

Traveling Crossflow Instability for the HIFiRE-5 Elliptic Cone

Borg

Kimmel

Stanfield

2015

Journal of Spacecraft and Rockets

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“…He noted that the effect of freestream turbulence on transition location decreased substantially with increasing crossflow. Recent experiments by Beeler et al 12 confirmed the presence of stationary crossflow vortices on a wedge-cone model in a Mach 3.5 quiet tunnel. Future experiments will focus on determining if traveling modes are also present.…”

Section: Introductionmentioning

confidence: 92%

Simultaneous Infrared and Pressure Measurements of Crossflow Instability Modes for HIFiRE-5

Borg

Kimmel

2016

54th AIAA Aerospace Sciences Meeting

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“…More recently at NASA Langley Research Center, we have invested considerable effort to make calibrated off-body measurements in our Mach 3.5 Supersonic Low-Disturbance Tunnel on flat-plate, cone, and wedgecone models. We have acquired measurements that compare favorably with computational results (e.g., Kegerise et al, 16,17,18 Owens et al, 19 and Beeler et al 20 ). Details of our approach are given in Kegerise, Owens, and King.…”

Section: Introductionmentioning

confidence: 99%

Measurements in a Transitioning Cone Boundary Layer at Freestream Mach 3.5

King

Chou

Balakumar

et al. 2016

54th AIAA Aerospace Sciences Meeting

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An experimental study was conducted in the Supersonic Low-Disturbance Tunnel to investigate naturally-occurring instabilities in a supersonic boundary layer on a 7 • halfangle cone. All tests were conducted with a nominal freestream Mach number of M∞ = 3.5, total temperature of T0 = 299.8 K, and unit Reynolds numbers of Re∞ × 10 −6 = 9. 89, 13.85, 21.77, and 25.73 m −1 . Instability measurements were acquired under noisy-flow and quiet-flow conditions. Measurements were made to document the freestream and the boundary-layer edge environment, to document the cone baseline flow, and to establish the stability characteristics of the transitioning flow. Pitot pressure and hot-wire boundarylayer measurements were obtained using a model-integrated traverse system. All hotwire results were single-point measurements and were acquired with a sensor calibrated to mass flux. For the noisy-flow conditions, excellent agreement for the growth rates and mode shapes was achieved between the measured results and linear stability theory (LST). The corresponding N factor at transition from LST is N ≈ 3.9. The stability measurements for the quiet-flow conditions were limited to the aft end of the cone. The most unstable first-mode instabilities as predicted by LST were successfully measured, but this unstable first mode was not the dominant instability measured in the boundary layer. Instead, the dominant instabilities were found to be the less-amplified, low-frequency disturbances predicted by linear stability theory, and these instabilities grew according to linear theory. These low-frequency unstable disturbances were initiated by freestream acoustic disturbances through a receptivity process that is believed to occur near the branch I locations of the cone. Under quiet-flow conditions, the boundary layer remained laminar up to the last measurement station for the largest Re∞, implying a transition N factor of N > 8.5.

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Crossflow Instability on a Wedge-Cone at Mach 3.5

Abstract: As a follow-on activity to the HyBoLT flight experiment, a six degree half angle wedge-cone model at zero angle of attack has been employed to experimentally and computationally study the boundary layer crossflow instability at Mach 3.5 under low disturbance freestream conditions.

Cited by 7 publications

References 9 publications

Traveling Crossflow Instability for the HIFiRE-5 Elliptic Cone

Traveling Crossflow Instability for the HIFiRE-5 Elliptic Cone

Simultaneous Infrared and Pressure Measurements of Crossflow Instability Modes for HIFiRE-5

Measurements in a Transitioning Cone Boundary Layer at Freestream Mach 3.5

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