Accession Number : AD0875491

Title :   Transonic Wind Tunnel Tests of a Base Drag Research Missile Model. Volume I.

Descriptive Note : Technical rept.,

Corporate Author : CORNELL AERONAUTICAL LAB INC BUFFALO NY

Personal Author(s) : Gorin, B. F.

Report Date : 25 SEP 1970

Pagination or Media Count : 583

Abstract : Tests were conducted in order to obtain data describing the effects of various simulated rocket exhaust plumes on the model's external flow field. Data describing the flow in the nozzle exit plane and in the model boundary layer were also obtained. Model external static pressure measurements were made and Schlieren, shadowgraph and tuft photographs were taken. The tests were conducted at Mach numbers from 0.000 to 1.200 at angles of attack from -2 to +2 degrees. The report presents details of the test program, an outline of the test procedure and the results of the investigation in tabular form. (Author)

Descriptors :   *DRAG), (*GUIDED MISSILE MODELS, (*BASE FLOW, EXHAUST GASES), MODEL TESTS, FLOW FIELDS, PRESSURE, BOUNDARY LAYER, NOZZLE GAS FLOW, ANGLE OF ATTACK, TABLES(DATA).

Subject Categories : Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE