2 edition of Hypersonic boundary-layer transition for X-33 phase II vehicle found in the catalog.
Hypersonic boundary-layer transition for X-33 phase II vehicle
by American Institute of Aeronautics and Astronautics, National Aeronautics and Space Administration, National Technical Information Service, distributor in Reston, Va, [Washington, DC, Springfield, Va
Written in English
|Other titles||Hypersonic boundary layer transition for X-33 phase 2 vehicle.|
|Statement||R.A. Thompson ... [et al.].|
|Series||[NASA technical memorandum] -- 207316., NASA technical memorandum -- 207316.|
|Contributions||Thompson, R. A., United States. National Aeronautics and Space Administration.|
|The Physical Object|
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,
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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 shock 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 .
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.