2 edition of Transonic pressure and load distributions for a group of simulated launch vehicles found in the catalog.
Transonic pressure and load distributions for a group of simulated launch vehicles
Thomas C Kelly
by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||Thomas C. Kelly|
|Series||NASA technical memorandum -- 80195|
|Contributions||United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Langley Research Center|
|The Physical Object|
|Pagination|| p. :|
|Number of Pages||214|
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Pressure and load distributions for a related group of simulated launch vehicle configurations are presented. The configurations were selected so that the nose cone and interstage transition flare components were relatively close to one another and subject to mutual interference effects.
Get this from a library. Transonic pressure and load distributions for a group of simulated launch vehicles. [Thomas C Kelly; United States.
National Aeronautics and Space Administration. Scientific and Technical Information Office.; Langley Research Center.]. TRANSONIC PRESSURE DISTRIBUTIONS OVER PROTUBERANCES AND ADJACENT AREAS IN PROXIMITY TO THE NOSE OF A LAUNCH VEEICLLE By James A.
Blackwell, Jr. Langley Research Center A wind-tunnel investigation was conducted over a Mach number range from to to determine the pressure distributions over protuberances and adjacent areas in proximity to the nose of a launch.
Transonic flow in the wake of a generic space launch vehicle is investigated using Improved Delayed Detached-Eddy simulations on quasi-structured, partially unstructured and hybrid grids.
It is shown that a 90 segment of the full domain can already capture the main afterbody flow dynamics and give a good agreement with experimental by: 2. Typical levels (dB) of surface pressure fluctuations on launch vehicles Loud Rock Concert Max Level inside Crew cabin cs Tip of Vehicle Base of Vehicle Level inside cargo compt, payload fairing cs Transonic Oscillating shock Smooth parts of vehicle cs Shock-plume interaction Pad/low altitude abort High altitude abort.
In Situ Distribution Guided Analysis and Visualization of Transonic Jet Engine Simulations among a group of GMM distributions. have similar pressure value distributions and hence the y. PDF | The Transonic Research Vehicle (TRV-1) is a project currently being developed by a group of Delft Aerospace Rocket Engineering (DARE) students | Find, read and cite all the research you.
Hybrid RANS-LES study of transonic flow in the wake of a generic space launch vehicle Tim Horchler, Kai Oßwald, Volker Hannemann and Klaus Hannemann German Aerospace Center (DLR), Institute of Aerodynamics and Flow Technology, Spacecraft Department Introduction Strong dynamical loads on the nozzle structure of space launch vehicles.
Launch vehicles are typically designed to fly at very low angles of attack. Nevertheless, even at such low angles of attack, the lateral (CFD) group (Basso, Antunes and Azevedo, a), together with additional computational resources available in the country, have made possible the analysis of almost realistic E.
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only published load results available for Mach numbers between and are in reference 4. As part of an investigation being made at transonic speeds of a cambered and twisted wing swept back some data were obtained on fuselage load distribution, the results of which are presented in this : Maurice D.
White, Bonne C. Look. dynamic pressure. However, at the outboard station there are distinct variations with both Reynolds number and dynamic pressure.
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Features discussion forums, blogs, videos and classifieds. flight-test-data-derived load indicates a significant over-prediction in the magnitude and duration of the buffet load. Note To Readers The predicted performance and certain other features and characteristics of the Ares I and Ares I-X launch vehicles are defined by the U.S.
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/5(). The LAIOP (Launch Vehicle Ignition Overpressure and Liftoff Acoustic Environments) program predicts the external pressure environment generated during liftoff for a large variety of rocket types. These environments include ignition overpressure, produced by the rapid acceleration of exhaust gases during rocket-engine start transient, and launch acoustics, produced by turbulence in the rocket Author: Marshall Space Flight Center.Wind Load Calculator.
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