Accession Number : AD0607611

Title :   EXTERNAL DRAG OF DUCTED BODIES CONSISTING OF CONE FRUSTUMS AND CONE FRUSTUMS FOLLOWED BY CYLINDERS MOVING AT SUPERSONIC SPEEDS,

Corporate Author : UNITED AIRCRAFT CORP EAST HARTFORD CONN

Personal Author(s) : Greber,Isaac

Report Date : 12 JAN 1953

Pagination or Media Count : 68

Abstract : The linearized theory is here applied to the determination of the wave drag of ducted cones of lip angles 1 to 12 degrees moving at supersonic speeds, M = 1.2 to 4.0, and at zero angle of attack. The results are presented as graphs of wave drag coefficient based on maximum frontal area versus ratio of maximum frontal area to inlet area, a family of constant Mach number curves being drawn for each lip angle. It will be noted that the range of calculated results exceeds the limits of validity of linearized theory. Therefore the use of the curves for the higher Mach numbers, say above 2.5, and larger lip angles, say greater than 6 degrees is advised only in the absence of more accurate data. In order to make the use of this report more convenient for total external drag calculations, curves are presented of turbulent skin friction coefficient based on total surface area versus the product of total body length and Mach number, with altitude as a parameter. A conversion chart is given to convert the coefficient based on surface area to one based on maximum frontal area, and a method is shown for calculating the total drag coefficient based on maximum frontal area of a ducted body consisting of a conical nose and a cylindrical afterbody, essentially a power plant nacelle configuration. (Author)

Descriptors :   (*DUCTED BODIES, DRAG), (*DRAG, DUCTED BODIES), CYLINDRICAL BODIES, CONICAL BODIES, ENGINE NACELLES, SUPERSONIC FLOW, AERODYNAMIC CHARACTERISTICS, MATHEMATICAL ANALYSIS, GRAPHICS

Distribution Statement : APPROVED FOR PUBLIC RELEASE