Richard H. Sawyer, Fred L. Daum
Static-pressure measurements were made through the speed of sound by the NACA wing- flow method at the rear of two unswept circular cylinders of different length-diameter ratio, and one 45 degree sweptback circular cylinder. Additional measurements were made at the rear and sides of a wedge. A Mach number range from about 0.7 to about 1.2 was covered in the tests.
An Adobe Acrobat (PDF) file of the entire report: