2 Matching Results

Search Results

Results: 1 - 2
open access

An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98

Description: Report presenting an investigation in the supersonic wind tunnel to determine some of the base pressure characteristics of related bodies of revolution at zero angle of attack. Results regarding variation of pressure over the base, variation of base pressure with Reynolds number, effect of nose and afterbody shapes, variation of base pressure with Mach number, and correlation of base pressure data are provided.
Date: March 17, 1955
Creator: Reller, John O., Jr. & Hamaker, Frank M.
Partner: UNT Libraries Government Documents Department
open access

Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen