Accession Number : ADA320214
Title : Volume 1. Performance Flight Testing. Annex 6B. NACA 1135. Equations, Tables, and Charts for Compressible Flow for Supersonic Aerodynamics.
Corporate Author : AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA
PDF Url : ADA320214
Report Date : JAN 1991
Pagination or Media Count : 73
Abstract : This report, which is a revision and extension of NACA TN 1428, presents a compilation of equations, tables, and charts useful in the analysis of high-speed flow of a compressible fluid. The equations provide relations for continuous one-dimensional flow, normal and oblique shock waves, and Prandtl-Meyer expansions for both perfect and imperfect gases. The tables present useful dimensionless ratios for continuous one-dimensional flow and for normal shock waves as functions of Mach number for air considered as a perfect gas. One series of charts presents the characteristics of the flow of air (considered a perfect gas) for oblique shock waves and for cones in a supersonic air stream. A second series shows the effects of caloric imperfection's on continuous one-dimensional flow and on the flow through normal and oblique shock waves.
Descriptors : *FLIGHT TESTING, *PERFORMANCE(ENGINEERING), *AERODYNAMIC CHARACTERISTICS, *TABLES(DATA), *CHARTS, *EQUATIONS, *SUPERSONIC CHARACTERISTICS, SHOCK WAVES, COMPRESSIBLE FLOW, COURSES(EDUCATION), MACH NUMBER, FLUID FLOW, ONE DIMENSIONAL FLOW, PRANDTL NUMBER, NORMALITY.
Subject Categories : Aerodynamics
Mfg & Industrial Eng & Control of Product Sys
Distribution Statement : APPROVED FOR PUBLIC RELEASE