Last edited by Kezilkree
Friday, July 17, 2020 | History

3 edition of Computational aeroheating predictions for X-34 found in the catalog.

Computational aeroheating predictions for X-34

# Computational aeroheating predictions for X-34

Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English

Subjects:
• Aerothermodynamics.,
• Aerodynamic heating.,
• Surface temperature.,
• Heat transfer.,
• Flow distribution.,
• Computational fluid dynamics.,
• Reynolds averaging.,
• Hypersonic flow.,
• Navier-Stokes equation.

• Edition Notes

The Physical Object ID Numbers Statement William L. Kleb, William A. Wood, and Peter A. Gnoffo. Series NASA/TM -- 1998-206289, NASA technical memorandum -- 206289.. Contributions Wood, William A., Gnoffo, Peter A., Langley Research Center. Format Microform Pagination 1 v. Open Library OL17134588M

A hypersonic aeroheating calculation method based on inviscid outer edge of boundary layer parameters The engineering method is widely used to make fast aeroheating prediction, especially at the initial stage of the aircraft design. The engineering method is applied to the boundary layer to reduce the computational cost and the Author: ZhuXuan Meng, Hu Fan, Ke Peng, WeiHua Zhang, HuiXin Yang. An overview of basic aeroheating design issues for Reusable Launch Vehicles (RLV), which addresses the application of hypersonic ground-based testing, and computational fluid dynamic (CFD) and engineering codes, is presented. Challenges inherent to the prediction of aeroheating environments required for the successful design of the RLV Thermal Protection .

Abstract. Disturbance level measurements are carried out in the Hypersonic Ludwieg Tube Braunschweig (HLB) at $$\text{ Ma } =$$ considering three shapes of stagnation point probes (SPP) and two different types of high speed surface sensors. Navier Stokes mean-flow solutions are produced for the flow around the front shapes to increase the understanding Cited by: 1. BibTeX @MISC{Kleb98aeroheatingpredictions, author = {William L. Kleb and Steven J. Alter and Christopher J. Riley and Christopher J. Riley and William L. Kleb Y and Steven J. Alter Z}, title = {Aeroheating Predictions for X Using an InviscidBoundary Layer Method," AIAA Paper }, year = {}}.

The aero-thermal analysis of a hypersonic vehicle is of fundamental interest for designing its thermal protection system. The aero-thermal environment predictions over several critical regions of the hypothesized lifting body vehicle, including the stagnation region of the nose-cap, cylindrically swept leading edges, fuselage-upper, and fuselage-lower surfaces, are by: 8. The X program seeks to demonstrate an autonomously returned orbital test flight vehicle to support the development of an operational Crew Return Vehicle for the International Space Station. The test flight, anticipated in , is intended to demonstrate the entire mission profile of returning Space Station crew members safely back to earth in the event of medical or .

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(tifl'erent v(,hiele, also (tesignate(] X ()SC was awar(h_d this contra('t of The ue, X is to I)e a sut)orl)ital teehnoh)gy (temonstrat()r, (:al)al)le of flying to Ma(:h 8, reaching an altitude ofIt, and landing autonomously on a ('onventional runway.

A tyt)i('al mission l)rofile is shown in Fig. Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; The Aerospace Press; Browse All Books; Meeting Papers; Standards; Other Publications.

Software/Electronic Products; Aerospace America ; Public Policy Papers ; ed by: Computational Aeroheating Predictions for X William L.

Kleb.* Willianl A. Wood.* and Peter A. Gnofl'o t NASA Langley Research Center, Hampton, Vi_yinia 2, Stephen Alter t Lockheed Martin Enqineerin9 (4 Scienc_:s.

Hampton, ViTyiuia 2, Radiative equilibrium surface temperatures, heating rates, streamlines, surface pres. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: As part of the development of this TPS system, the aeroheating environment of the X is being defined through conceptual analysis, ground-based wind-tunnel testing and computational fluid dynamics (CFD).

Reentry Air Data for a Sub-orbital Spacecraft Based on X Design. Joel Ellsworth and Computational aeroheating predictions for X William Kleb, Aeroheating predictions for X using an inviscid-boundary layer method.

Christopher Riley. The nominal × × point grid was used for all laminar wind-tunnel aeroheating and aerody- namic GASP computations. For turbulent wind-tunnel computations with GASP, the File Size: 4MB. This report details a computational fluid dynamics study conducted in support of the phase II development of the X vehicle.

Aerodynamic and aeroheating predictions were generated for. A rapid approach to hypersonic aeroheating predictions in the stagnation region and downstream is developed in the present paper.

The engineering method is used to calculate inviscid hypersonic flowfields to reduce time cost, and a combination of the mass flow balance technique and the axisymmetric analog is proposed to account for the entropy swallowing by: Computations were performed for Mach numbers of to at angles-of-attack from 10 deg to 48 deg with body flap deflections of 0, 10 and 20 deg.

Comparisons between predictions. Get this from a library. Computational aeroheating predictions for X [William L Kleb; William A Wood; Peter A Gnoffo; Langley Research Center.]. Get this from a library. Computational aeroheating predictions for X [William L Kleb; Stephen J Alter; United States. National Aeronautics and Space Administration.].

Study on the aerothermodynamic characters of hypersonic small nose cone with local rarefied gas effects. Chinese Journal of Computational Physics,27(1). Wang Zhihui Bao Lin Tong Binggang, On the characteristics and physical mechanism of aeroheating to hypersonic pointed bodies with local rarefied gas effects.

COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle.

Aeroheating Predictions for X Using an Inviscid-Boundary Layer Method Article (PDF Available) in Journal of Spacecraft and Rockets 36(2).

computational aerodynamic research and additional computational aeroheating results are presented in this reference and in the companion paper by Murphy In the present paper, aerodynamic performance predictions from an inviscid Euler code and two Navier-Stokes codes will be presented and compared with data from several hypersonic wind Size: 4MB.

Computational Aeroheating Predictions for X The work presented in this report is part of a larger effort to define the X aerothermal environment, including the application of engineering codes and wind-tunnel studies Topics: Fluid Mechanics and Heat Transfer.

Aeroheating and Aerodynamic CFD Validation And Prediction for The X Program. AEROHEATING AND AERODYNAMIC CFD VALIDATION AND PREDICTION FOR THE. X where the computational predictions.

Computational Aeroheating Predictions for X By William L. Kelb, Peter A. Gnoffo, (Laura) are presented for the X Technology Demonstrator. Results for two trajectory points corresponding to entry peak heating and two control surface deflections are discussed.

This data is also discussed in context of Thermal Protection System (TPS Cited by: 3. An overview of basic aeroheating design issues for Reusable Launch Vehicles (RLV), which addresses the application of hypersonic ground-based testing, and computational .THEORETICAL & APPLIED MECHANICS LETTERS 2, () Aeroheating CFD analysis of missile slots Kai Yanga) and Xiaowei Gaob) State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology, DalianChina (Received 25 July ; accepted 16 November ; published online 10 January ) Cited by: 2.The proposed Mars Science Laboratory (MSL) mission is intended to deliver a large rover to the Martian surface within 10 km of the target site.

This paper presents computational fluid dynamics (CFD) predictions of forebody heating rates for two MSL entry configurations with fixed aerodynamic trim tabs.