Accession Number : ADA320217
Title : Volume 1. Performance Flight Testing. Chapter 6. Supersonic Aerodynamics.
Corporate Author : AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA
PDF Url : ADA320217
Report Date : JAN 1991
Pagination or Media Count : 94
Abstract : Some basic concepts of Aerodynamics and Thermodynamics have previously been covered. These related to determination of fluid flow around various shapes and the resultant forces acting upon these shapes. Fluids previously studied were assumed to be incompressible. This assumption, among others, reduced the number of variables involved and allowed relatively simple solutions to previously complex sets of equations. Making assumptions to eliminate some variables is an everyday activity of the engineer, but care needs to be taken to ensure assumptions made to provide an idealized solution to a given physical system are still valid if the idealized solution is applied to a related, but different, physical system.
Descriptors : *FLIGHT TESTING, *PERFORMANCE(ENGINEERING), *AERODYNAMIC CHARACTERISTICS, *SUPERSONIC FLOW, VELOCITY, SHOCK WAVES, THEORY, GASES, COMPRESSIBLE FLOW, WAVE PROPAGATION, APPROXIMATION(MATHEMATICS), SOUND, CLASSIFICATION, COURSES(EDUCATION), MACH NUMBER, EQUATIONS, PITOT TUBES, STAGNATION TEMPERATURE, TRANSONIC FLOW, THREE DIMENSIONAL FLOW, ONE DIMENSIONAL FLOW, THIN WINGS, CONVERGENT DIVERGENT NOZZLES.
Subject Categories : Aerodynamics
Mfg & Industrial Eng & Control of Product Sys
Distribution Statement : APPROVED FOR PUBLIC RELEASE