by National Aeronautics and Space Administration, Langley Research Center in Hampton, Va .
Written in English
|Statement||Leroy C. Baranowski and H.W. Kipp.|
|Series||NASA contractor report -- NASA CR-172361.|
|Contributions||Kipp, H. W., Langley Research Center., McDonnell Douglas Astronautics Company-St. Louis.|
|The Physical Object|
On the computation of the transonic perturbation flow field around two- and three-dimensional oscillating wings. A survey of leeside flow and heat transfer on delta planform configurations. Effects of surface temperature and Reynolds number on heat transfer to the Shuttle Orbiter leeward fuselage. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Full text of "Aerodynamic design of the space shuttle orbiter" See other formats AERODYNAMIC DESIGN OF THE SPACE SHUTTLE ORBITER by W.E. Bornemann Manager, Space Shuttle Aerodynamics Rockwell International Corporation Space Systems Group Lakewood Boulevard Downey, CA T.E. Surber Supervisor, Orbiter Aerodyanmics and Rockwell International . FLOW-FIELD SURVEYS ON THE WINDWARD SIDE OF THE NASA A SPACE SHUTTLE ORBITER AT 31° ANGLE OF ATTACK AND MACH 20 IN HELIUM George C. Ashby, Jr., and Vernon T. Helms III Langley Research Center SUMMARY Pitot-pressure and flow-angle distributions in the windward flow field of the NASA A space shuttle orbiter configuration and surface.
study, separation of the space shuttle orbiter from a carrier vehicle was shown to be feasible for a range of dynamic-pressure and flight-path-angle conditions. By using an autopilot, the vehicle attitudes were held constant which ensured separation. Carrier-vehicle engine thrust, landing gear, and spoilers provide. Shuttle Infrared Leeside Temperature Sensing. the infrared camera system is mounted in such a way that it rotates to view the orbiter leeside surfaces through either of two windows-one offering a view of the orbiter fuselage and the other a view of the left wing. The camera is . (ii) The Shuttle's enters the atmosphere at such a high velocity that the air under its path does not have an opportunity to disperse and is compressed. Compressing a gas causes it to heat. The radiant heat from the air that has been heated (by the compression) begins to . The evaluated average heat transfer coefficients α f are listed in Table 3. By using equation Q = α f ⋅Δt⋅A, the total heat transfer rates Q on the plate are obtained and listed in Table 3. Comparison of heat transfer coefficient predicted by the optimal formalized equations with .
space shuttle main engines. pogo suppression system. space shuttle main engine controllers. malfunction detection. orbiter hydraulic systems. mps thrust vector control. helium, oxidizer and fuel flow sequence. orbiter/external tank separation system. inch disconnect. external tank separation system. orbiter umbilical doors. orbital. Finite-Element Reentry Heat-Transfer Analysis of Space Shuttle Orbiter Author: Ko, William L., Robert D. Quinn, and Leslie Gong Subject: NASA TP Keywords: Heat-transfer analysis, Reentry heating, Space Shuttle orbiter, Space t ransportation system data Created Date: 7/2/ AM. Experimental assessment of a computer program used in space shuttle orbiter entry heating analyses (NASA technical memorandum) Unknown Binding – January 1, by William L Wells (Author) See all formats and editions Hide other formats and editions. Enter your mobile number or email address below and we'll send you a link to download the Author: William L Wells. Convective heat transfer enhancement can be achieved by generating secondary flow structures that are added to the main flow to intensify the fluid exchange between hot and cold regions. One method involves the use of vortex generators to produce streamwise and transverse vortices superimposed to the main flow. This study presents numerical computation results of laminar convection heat.