4 edition of Experimental and computational aerothermodynamics of a Mars entry vehicle found in the catalog.
Experimental and computational aerothermodynamics of a Mars entry vehicle
by Aerospace Engineering Hypersonic Aerothermodynamics, [National Aeronautics and Space Administration, National Technical Information Service, distributor] in Raleigh, N.C, Springfield, Va
Written in English
|Statement||by Brian R. Hollis.|
|Series||NASA contractor report -- 201633., NASA contractor report -- NASA CR-201633.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Get this from a library. Experimental and computational aerothermodynamics of a Mars entry vehicle. [Brian R Hollis; United States. National Aeronautics and Space Administration.]. obtaining high-fidelity data for computational model development and validation for such phenomena has become one of the primary roles of wind tunnel testing, in addition to its customary role of producing data for vehicle design, development, and performance evaluation.
Therefore, the discipline of experimental aerothermodynamicsFile Size: 7MB. The Mars Science Laboratory (MSL) mission (Ref. 2), to be launched inwill deliver the largest (> kg) rover ever to Mars. The MSL vehicle (Figure 1) will fly a controlled, lifting trajectory (α = 16 deg) to deliver the payload to within 10 km of the target location.
The entry vehicle is comprised of a m diameter spherically. An experimental investigation of turbulent aeroheating on the Mars Science Laboratory entry vehicle heat shield has been conducted in the Arnold Engineering Development Center Hypervelocity Wind.
Analysis of Entry Vehicle Aerothermodynamics Using the Direct Simulation Monte Carlo Method accurately computed by using free molecular flow analysis.1 The properties of interest in entry vehicle analysis are those that affect the vehicle’s performance.
These include the Cited by: 6. Entry Aerothermodynamics ENAE - Launch and Entry Vehicle Design U N I V E R S I T Y O F MARYLAND Approximating H aw 8 Ho = He + u2 e 2 (= total enthalpy at edge of boundary layer H aw = H e +r u2 e 2 r ⌘ recovery factor Haw = He +r(Ho He) for incompressible ﬂow, r ⇡ p Pr = for std.
air r decreases only % from M=0 to M=16 File Size: 7MB. The mars science laboratory (MSL) spacecraft is being designed to carry a large rover (> kg) to the surface of Mars using a blunt-body entry capsule as the primary decelerator.
This book gives an introduction to the basics of aerothermodynamics, as applied in particular to winged re-entry vehicles and airbreathing cruise and acceleration vehicles.
Beginning with a broad vehicle classification and a discussion of the flight environment, Basics of Aero-thermodynamics focuses on flight in the earth's atmosphere at speeds.
The present research focuses on both Aerodynamics and Aerothermodynamics of a re-entry vehicle. The objective is to provide an optimized model in both respects by analyzing local properties like heat flux, pressure distribution and global parameters like mono stability and lift-drag characteristics by: 3.
Challenges to Computational Aerothermodynamic Simulation and Validation for Planetary Entry Vehicle Analysis Peter A. Gnoffo, Christopher O. Johnston, Bil Kleb NASA Langley Research Center Hampton, VA USA @ ABSTRACT Challenges to computational aerothermodynamic (CA) simulation and validation of hypersonic ﬂow Cited by: 4.
This paper presents a literature survey on supersonic retropropulsion technology as it applies to Mars entry, descent, and landing (EDL). The relevance of this technology to the feasibility of Mars EDL is shown to increase with ballistic coefficient to the point that it is likely required for human Mars exploration.
The use of retropropulsion to decelerate an entry vehicle from hypersonic or Hollis, B.R.: Experimental and Computational Aerothermodynamics of a Mars Entry Vehicle. PhD thesis, Aerospace Engineering, North Carolina State University, An overview of the NASA technology program in planetary entry aerothermodynamics is presented.
Bounds on the technology requirements of the program are set by considering a broad range of solar system exploration mission categories and by allowing great flexibility in choice of entry Applied Computational Fluid Dynamics. Fig. Vehicle configurations with quotes. Freestream conditions.
The flight scenario considered so far is summarized in Table 1. They refer to entry. conditions compatible with a vehicle entering the Mars atmosphere both from a hyperbolic 6.
Viviani, G. Pezzella, “Non-Equilibrium Computational Flowfield Analysis for the Design of Mars Manned Entry Vehicles”. Book title: EUCASS Flight Physics Book (Volume 5). ISBN: 7.
Viviani, G. Pezzella, “Aerodynamics and Aerothermodynamics Assessment of a Mars Sample Return Mission” This banner text can have markup. web; books; video; audio; software; images; Toggle navigation Full text of "NASA Technical Reports Server (NTRS) Computational Aerothermodynamic Design Issues for Hypersonic Vehicles" See other formats Obtaining local experimental data in internal rarefied gas flows is still a challenge.
Most of the current data are relative to mass flow rates and inlet/outlet pressures for channel flows, or to local temperature and pressure measurements at the wall by microsensors or sensitive paints, but there is a crucial need for investigating velocity and temperature fields directly within the gas in a rgdorg/ Afterbody Heating Predictions for a Mars Science Laboratory Entry Vehicle.
Karl Edquist; Computational Aerothermodynamics • Monday, 06 June • hrs. Experimental and Computer Modeling and Study of Carbon Combustion in Low Pressure Laminar H2 + O2 :// Re-entry vehicle • Re-entry vehicle as part of Europe’s access to space program, • detailed experimental and numerical data for for the whole Mach number range, • no demonstration ﬂight, • project: begin incancelled• aerodynamic data of steady motion (longitudi- nal and lateral) available, • dynamic stability data.