Accession Number : ADA258058


Title :   Flowfield Computations Over the Space Shuttle Orbiter with a Proposed Canard at a Mach Number of 5.8 and 50 Degrees Angle of Attack


Descriptive Note : Master's thesis


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : Reuter, William H


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a258058.pdf


Report Date : Jun 1993


Pagination or Media Count : 47


Abstract : Advances in computational fluid dynamics (CFD) capabilities in the last decade have allowed engineers to better analyze cases of hypersonic flight The Space Shuttle Orbiter has increased over 30,000 pounds in weight since its initial design in 1974, resulting in limitations on its operational capability. One of these limitations is the allowable forward center of gravity location resulting from lateral-directional and longitudinal controllability constraints. One method to relax this limitation is to employ the use of a canard. A canard can produce the additional nose-up pitching moment to relax the center of gravity constraint as well as alleviate the need for large , lift-destroying elevon deflections required to maintain the high angles of attack required for effective hypersonic flight. A configuration is developed using known Orbiter aerodynamic data and a canard computational grid is generated. The Orbiter- Canard configuration is analyzed at a Mach number of 5.8 and angle of attack of 50 degrees using flowfields generated by the OVERFLOW three-dimensional computer code. Comparison is made with a baseline solution and results are presented. Space Shuttle, CFD, Canard, Hypersonic Aerodynamics, Computational Fluid Dynamics.


Descriptors :   *COMPUTATIONS , *FLOW FIELDS , *SPACE SHUTTLES , *CANARD CONFIGURATIONS , *HYPERSONIC FLIGHT , ANGLES , COMPUTERS , COMPARISON , GRIDS , MOMENTS , FLIGHT , CONFIGURATIONS , NOSES , LIFT , NUMBERS , FLUID DYNAMICS , MACH NUMBER , ENGINEERS , FLUIDS , GRAVITY , WEIGHT , DIRECTIONAL , HIGH ANGLES , AERODYNAMICS , ELEVONS , LIMITATIONS , THREE DIMENSIONAL , ANGLE OF ATTACK , DEFLECTION , ATTACK , DYNAMICS , CENTER OF GRAVITY


Subject Categories : Spacecraft Trajectories and Reentry
      Manned Spacecraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE