Hypersonic boundary-layer transition for X-33 phase II vehicle

Publisher: American Institute of Aeronautics and Astronautics, Publisher: National Aeronautics and Space Administration, Publisher: National Technical Information Service, distributor in Reston, Va, [Washington, DC, Springfield, Va

Written in English
Published: Downloads: 250
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  • Boundary layer transition.,
  • Hypersonics.,
  • Flow distribution.,
  • Wind tunnel tests.,
  • Finite volume method.,
  • Flow visualization.

Edition Notes

Other titlesHypersonic boundary layer transition for X-33 phase 2 vehicle.
StatementR.A. Thompson ... [et al.].
Series[NASA technical memorandum] -- 207316., NASA technical memorandum -- 207316.
ContributionsThompson, R. A., United States. National Aeronautics and Space Administration.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL15539952M

Hypersonic Boundary Layer Transition for the X Phase II Vehicle A Thompson Richard, Ii H. Harris Hamilton, Alan B. Scott, Jamael Thomas, J Nowak Robert Engineering. Finally, the nonlinear interaction of disturbance leads to a relatively quiet zone, which further breaks down, resulting in the transition of the boundary layer. Our results show that transition is determined by the second by: For a vehicle in hypersonic flight, the natural transition of a boundary layer from laminar to turbulent flow depends on multiple factors including the free-stream conditions, the noise level and frequency spectrum of free-stream disturbances, the geometry of the vehicle and the vehicle surface predict boundary layer transition for flow over a given vehicle, one or more of these Location: Vickors Xing, Brooklyn Park, MN,   Zuchowski, B.: Predictive capability for hypersonic structural response and life prediction: phase ii - detailed design of hypersonic cruise vehicle hot-structure. Technical Report AFRL-RQ-WP-TR, May Google ScholarAuthor: Zachary B. Riley, Jack J. McNamara.

EXPERIMENTAL STUDIES OF HYPERSONIC BOUNDARY-LAYER TRANSITION AND EFFECTS OF WIND-TUNNEL DISTURBANCES 5. Report Date March 6. Performing Organization Code 7. Author(s) P. Calvin Stainback and Richard D. Wagner Langley Research Center F. Kevin Owen and Clifford C. Horstman Ames Research Center 8. Performing Organization Report No. L by: Observation of transition of the hypersonic boundary layer on a cone continued with experiments at M,» = Transition independent of the unit Reynolds number was obtained. This is dramatically different from the results obtained earlier. Blunt cone transition with a wide range of nose radii was Size: 2MB. boundary layer transition by placing them relatively upstream with relatively large heights at hypersonic speeds. 3-D roughness is most effective in tripping. Meanwhile, a few past experiments reported that roughness can also have the opposite effects by delaying transition under some circumstances. But the mechanisms and theFile Size: 2MB. A typical challenge for re-entry vehicles during flight is an effective control of hypersonic transition and the laminar/turbulent state of the boundary layer. The state of the boundary layer is of high importance since skin friction drag and heat transfer rates in a turbulent boundary layer can be several times higher than those of a laminar File Size: 1MB.

Experiment Objectives The objective of the Infrared Sensing Aeroheating Flight Experiment is to identify, monitor, and quantify hypersonic boundary layer transition for the X vehi- cle during flight. This includes, specifically, the global mapping of the transition movement over the windward surface. Laminar-turbulent transition of boundary layer ows can have a strong impact on the performance of hypersonic vehicles because of its in uence on the surface skin friction and aerodynamic heating. Therefore, the prediction and control of transition onset and the associated variation in aerothermodynamic parameters in high-speedFile Size: 1MB. Characterization of Structural Response to Hypersonic Boundary Layer Transition Rohit Deshmukh Ph.D. Candidate on the structural response of hypersonic vehicle surface panels 1. Enhance existing aerothermoelastic framework with Hypersonic Boundary Layer Transition. Aerothermoelastic framework 8 Aerothermodynamics Mean FlowFile Size: 2MB.

Hypersonic boundary-layer transition for X-33 phase II vehicle Download PDF EPUB FB2

A status review of the experimental and computational work performed to support the X program in the area of hypersonic boundary-layer transition is presented.

Global transition fronts are visualized using thermographic phospor measurements. Transition Issues for X Laminar-to-turbulent transition on any hypersonic vehi-cle influences the thermal protection system (TPS) and the allowable flight trajectories.

As a result, vehicle weight, payload capacity, and mission are directly affected. Unfor-tunately, the uncertainty in predicting transition onset is. Hypersonic boundary layer transition for X Phase II vehicle.

Richard Thompson, Roles of Engineering Correlations in Hypersonic Entry Boundary Layer Transition Prediction. Charles Campbell, X hypersonic boundary layer transition.

Scott Berry. Get this from a library. Hypersonic boundary-layer transition for X phase II vehicle. [R A Thompson; United States. National Aeronautics and Space Administration.;]. X Hypersonic Boundary-Layer Transition. Scott A. Berry, Interaction Between Aerothermally Compliant Structures and Boundary Layer Transition in Hypersonic Flow.

Zachary B. Riley and Hypersonic boundary layer transition for X Phase II vehicle. Richard Thompson, Cited by: CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): Boundary layer and aeroheating characteristics of several X configurations have been experimentally examined in the Langley Inch Mach 6 Air Tunnel.

Global surface heat transfer distributions, surface streamline patterns, and Hypersonic boundary-layer transition for X-33 phase II vehicle book shapes were measured on scale models at Mach 6 in air. Boundary layer and aeroheating characteristics of several X configurations have been experimentally examined in the Langley Inch Mach 6 Air Tunnel.

Global surface heat transfer distributions, surface streamline patterns, and shock shapes were measured on scale models at Mach 6 in air. Parametric variations include angles-of-attack of deg, deg, and deg; Reynolds numbers.

X Hypersonic Aerodynamic Characteristics. Kelly J. Murphy, NASA Langley Experimental Aerothermodynamic Contributions to Slender and Winged Hypersonic Vehicles. Scott A. Berry and Hypersonic boundary layer transition for X Phase II vehicle.

Richard Thompson, Cited by: Phase II and toward construction and flight of the X vehicle. The X program (Phase I and Phase II) had ambitious, fast-paced sched-ules with a total time from development to flight of years. Development of VentureStar, the full-scale operational RLV, progressed in parallel with the X program [2].

Figure 1. The Lockheed-Martin X andCited by: Hypersonic boundary layer transition and control 7 Fig. 5 Instantaneous density fluctuations in the shock layer (a,b,c) and rms density fluctuations in the cross section x = 0. 8 (e,f,g) for M. Abstract. Boundary-layer transition is a problem that has plagued several generations of aerodynamicists.

There are very few things about transition that are known with certainty, other than the fact that it happens if the Reynolds number is large by: Boundary-Layer Transition on XA. Efficient Prediction of the Temperature History of a Hypersonic Vehicle Throughout the Mission Trajectory with an Aerodynamic Thermal Load Element.

6 November | International Journal of Aeronautical and Space Sciences, Vol. 47 Hypersonic boundary layer transition for X Phase II by:   Transition and turbulence production in hypersonic boundary layers have recently received considerable attention owing to their fundamental importance and strong relevance to the safety of hypersonic vehicle flight, including significant increase in aerodynamic heating, entropy production, and drag.

1,2 1. Fedorov, Annu. Rev. Fluid Mech. 43, 79 ().Cited by: approaches. 9 – 14 These tools have enabled broad study on hypersonic boundary layer transition, including geometry changes, 10, 11, 15, 16 operating conditions, 10, 11, 15, 17 mass.

Measurement techniques Temperature-sensitive paint. Temperature-sensitive paint (TSP) is commonly used for the detection of boundary layer transition in hypersonic flows.Under the irradiation of incident light with specific wavelength, the TSP can emit luminescent light with wavelength differs from that of incident light, and the luminescent intensity is decreased as the Author: Shiyong Yao, Yi Duan, Pan Yang, Lei Wang, Xiaoli Zhao, Changwan Min.

Roughness induced boundary layer transition has been one of the main research topics for the hypersonic community over the last half- century. The major interest into the understanding of this phenomenon relies in the key role played by transition prediction methods on hypersonic vehicles thermal protection system (TPS) by: Experimental measurement of the aerodynamic heating via the global thermographic phosphor technique and development of a hypersonic boundary-layer transition correlation for X is described.

Based on recent progress in the study of transition in the hypersonic boundary layer [37,50,53], a similar transition scenario for the hypersonic boundary layer is proposed in the conclusion. Receptivity. As mentioned above, the receptivity process determines the initial flow conditions, which strongly affect the transition by: 1.

HYPERSONIC BOUNDARY LAYER FLOW AROUND A SHARP CORNER Thesis by Andreas Puhl II. EXPERIMENTAL APPARATUS AND PROCEDURES PAGE i i iii iv v vii 1 4 1. Facilities II. Model Pressure Measurements data on the interaction of hypersonic laminar boundary layer with anFile Size: 3MB. Hypersonic Boundary-Layer Transition: Application to High-Speed Vehicle Design Article in Journal of Spacecraft and Rockets 45(2) March with 30 Reads How we measure 'reads'.

Hypersonic boundary-layer transition is afiected by many factors, including Mach number, Reynolds number, geometry, roughness, and tunnel noise. The efiect of ablation or surface blowing is reviewed by summarizing the experimental data. Blowing gener-ally moves transition upstream, with larger mass°ow rates or lighter gases causing a larger efiect.

This Boundary Layer Transition II wedge will be launched on a sounding rocket sometime in from NASA’s Wallops Flight Facility in Virginia. The elongated BOLT II wedge is designed to create more hypersonic turbulent flows than the original BOLT wedge that in May will soar over a test range in Sweden, if all goes as planned.

Fig. 1 shows the results of velocity profiles and temperature profiles at three different locations of x = L, L, L. η is the dimensionless coordinate with Illingworth transform which is defined as η = (ρ e U e μ e x) 1 / 2 ∫ 0 y ρ ρ e d ed symbols represent the values obtained from the self-similar solution and three lines stand for current numerical simulation by: 9.

hypersonic boundary layer transition, which highl ights some of the challenges with conducting fl ight te sts. This document is intended to provide recommend ations fo r conducti ng a future.

hypersonic boundary layer undergoing laminar-to-turbulent transition requires a flow that is at higher Reynolds numbers. To achieve higher Reynolds numbers in the Inch Mach 10 facility, either the facility stagnation pressure, model angle-of-attack (AoA), or both must be increased.

Either change results in higher post-shock static. Hypersonic Boundary-Layer Transition on Reusable Launch Vehicles Steven P. Schneider, Purdue University, School of Aeronautics and Astronautics (Also On-Call Employee, TRW) Presented at the RLV/SOV Airframe Technology Review, NASA Langley, November Meeting is ITAR restricted.

This version edited to remove ITAR-controlled Size: 2MB. hypersonic boundary layer transition in a controlled and predictable manner. A wind tunnel program was II. Hyper-X and Trip Design The Hyper-X (XA) program recently means for control of the boundary layer on the flight vehicle.

To minimize susceptibility of File Size: 6MB. In hypersonic flows, the location and extent of transition is a major issue particularly for applications such as aerospace planes, re-entry vehicles, and space shuttles.

Therefore, the understanding and prediction of transition at hypersonic speeds is of both fundamental and practical by: A. Hypersonic Boundary-Layer Transition Hypersonic laminar-to-turbulent transition is important for prediction and control of heat transfer, skin friction, separation and other boundary-layer properties.

Vehicles that spend extended periods at hypersonicCited by:   Prediction of Boundary Layer Transition on Hypersonic Vehicles in Large-Scale Wind Tunnels and Flight.

Printer-friendly version. PHASE II: Develop a computational model to predict boundary layer transition in large scale hypersonic wind tunnels and extrapolate ground test measurements to flight conditions, and validate the model against.

The prediction of laminar-turbulent transition of hypersonic boundary layers is critically important to the development of hypersonic vehicles that are to be used for rapid global access. Boundary layer transition has first-order impacts on aerodynamic heating, as well as drag and control of hypersonic on: Hunters Ridge Blvd, Dayton, OH, Laminar-turbulent transition in hypersonic bound-ary layers is important for prediction and control of heat transfer, skin friction, and other boundary layer properties.

Vehicles that spend extended periods at hypersonic speeds may be critically afiected by the uncertainties in transition prediction, depend-ing on their Reynolds numbers.The important transition regions are coupled through a closed optimization loop that is used to determine the extent of the transition region based on available input free-stream turbulence levels and acoustic power spectra.

The predictions for each regime will be validated against existing and newly generated DNS databases and experimental on: E Via Cotorra, Tucson, AZ,