A Novel Sensor for Fast Heat Flux Measurements

Knauss, H.; Roediger, Tim; Gaisbauer, U.; Kraemer, Ewald; Bountin, D. A.; Smorodsky, B. V.; Маслов, А. А.; Srulijes, J.; Seiler, F.

doi:10.2514/6.2006-3637

Cited by 21 publications

(10 citation statements)

References 21 publications

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“…Its working principle is based on temperature difference measurements in very thin films using the transverse Seebeck effect (Renk et al 1994;Knauss et al 2009). The advantages of the ALTP sensor arise from the very thin sensing element (down to 10-100 nm), giving bandwidths up to 1 MHz (Renk et al 1994).…”

Section: Measurement Techniquesmentioning

confidence: 99%

Transitional shock-wave/boundary-layer interactions in hypersonic flow

et al. 2014

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Strong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.

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Section: Measurement Techniquesmentioning

confidence: 99%

Transitional shock-wave/boundary-layer interactions in hypersonic flow

et al. 2014

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“…A thermoelectric field is created when a temperature gradient exist over the yttrium-barium-copper-oxide (YBCO) crystal via the transverse Seebec effect. (26) A spectral resolution up to several hundreds of kilohertz's is expected as a result of the small thickness of the crystal (1 µm) and small sensing area. The manufacturer quotes that a 100 kHz frequency response is obtainable with the ALTP sensor.…”

Section: B Test Matrix and Conditionsmentioning

confidence: 99%

Investigation of Hypersonic Laminar Heating Augmentation in the Stagnation Region

Marineau¹,

Lewis

Smith

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Laminar stagnation region heating augmentation is investigated in the AEDC Tunnel 9 at Mach 10 by performing high frequency surface pressure and heat transfer measurements on the Orion CEV capsule at zero degree angle-of-attack for unit Reynolds numbers between 0.5 and 15 million per foot. Heating augmentation increases with Reynolds number, but is also model size dependent as it is absent on a 1.25-inch diameter model at Reynolds numbers where it reaches up to 15% on a 7-inch model. Heat transfer space-time correlations on the 7-inch model show that disturbances convect at the boundary layer edge velocity and that the streamwise integral scale increases with distance. Therefore, vorticity amplification due to stretching and piling-up in the stagnation region appears to be responsible for the stagnation point heating augmentation on the larger model. This assumption is reinforced by the f -11/3 dependence of the surface pressure spectrum compared to the f -1 dependence in the free steam. Vorticity amplification does not occur on the 1.25-inch model because the disturbances are too large. Improved free stream fluctuation measurements will be required to determine if significant vorticity is present upstream or mostly generated behind the bow shock.

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“…In the current ALTP probes δ F ≈ 0.6-0.7 mm with an additional 1 mm protection layer (coating), and the bandwidth is restricted to a time constant of about τ ALTP ≈ 1ms. The amplitude-frequency response coefficients of the sensors were measured and showed that Fourier amplitude was reduced to 1/ √ 2 at frequency 500 kHz [20]. To obtain the maximum spatial resolution the active area has been reduced to the minimum possible length × width = 2 mm × 0.4 mm (Fig.…”

Section: System Of Measurement Control and Data Acquisitionmentioning

confidence: 99%

“…[20]. ALTP signal is digitized by PCI-9812 (© ADLINK Technology Inc.) PC data acquisition card with 5 MHz sampling rate and 524288 record lengths for angle of attack α = 0 • , 2 • .…”

Section: System Of Measurement Control and Data Acquisitionmentioning

confidence: 99%

Experimental study of compressible boundary layer on a cone at angles of attack

et al. 2009

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Experimental study was conducted for boundarylayers on a sharp 5 • half-angle cone of 400 mm length at angles of attack. The model was tested in the T-326 hypersonic wind tunnel (ITAM) at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0 • , 2 • , 3 • and 4 • angles of attack for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature distributions along the model are obtained, and transition beginning and end locations have been found. Boundary layer stabilization with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent to hypersonic boundary layer (second mode) have been detected.

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A Novel Sensor for Fast Heat Flux Measurements

Cited by 21 publications

References 21 publications

Transitional shock-wave/boundary-layer interactions in hypersonic flow

Transitional shock-wave/boundary-layer interactions in hypersonic flow

Investigation of Hypersonic Laminar Heating Augmentation in the Stagnation Region

Experimental study of compressible boundary layer on a cone at angles of attack

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