Accession Number:

ADA101494

Title:

Finite Span Effects on Flap Heating and Effectiveness in a Turbulent Boundary Layer.

Descriptive Note:

Final technical rept. May 78-Dec 80,

Corporate Author:

SCIENCE APPLICATIONS INC IRVINE CA AERONAUTICAL SYSTEMS TECHNOLOGY DIV

Personal Author(s):

Report Date:

1980-08-01

Pagination or Media Count:

74.0

Abstract:

An experiment was conducted in the NASA Langley Continuous Flow Hypersonic Tunnel to measure the heat transfer and pressure distributions on finite span flaps subjected to turbulent boundary layer conditions. Data were obtained for three span widths at deflection angles below that required to induce separation at the compression corner. The results are compared with other experimental data and theoretical predictions. Author

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE