Accession Number:

AD0669353

Title:

A TUBE WIND TUNNEL FOR HIGH REYNOLDS NUMBER SUPERSONIC TESTING,

Descriptive Note:

Corporate Author:

CORNELL AERONAUTICAL LAB INC BUFFALO N Y

Personal Author(s):

Report Date:

1968-02-01

Pagination or Media Count:

47.0

Abstract:

A modified Ludwieg tube wind tunnel which offers the possibility of high i.e., full-scale Reynolds number supersonic testing for the supersonic transport at relatively low cost is described. The modifications, consisting of a revised diaphragm location and a large downstream vacuum tank, are intended to reduce the starting time and starting loads found to exist in the basic Ludwieg tunnel. The operating characteristics of a short flow duration tunnel of this type are discussed along with the problems of instrumentation for a minimum design flow duration equal to one-twentieth of a second. It is anticipated that pressure, heat transfer, and skin friction data can be obtained with instrumentation similar to that now in use. Force data of the precision required for SST tests, however, are expected to be more difficult to obtain. Author

Subject Categories:

  • Civilian Aircraft
  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE