Accession Number:

AD0263197

Title:

AERODYNAMIC CHARACTERISTICS, TEMPERATURE, AND NOISE MEASUREMENTS OF A LARGE-SCALE EXTERNAL FLOW JET-AUGMENTED-FLAP MODEL WITH TURBOJET ENGINES OPERATING

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-09-01

Pagination or Media Count:

1.0

Abstract:

An investigation was conducted in the Langley full-scale tunnel on a large-scale model powered by turbojet engines with flattened rectangular nozzles. The wing had 35 degrees sweep of the leading edge, an aspect ratio of 6.5, a taper ratio of 0.31, and NACA 651-412 and 65-408 airfoils at the root and tip. The investigation included measurements of the longitudinal aerodynamic characteristics of the model with halfspan and full-span flaps and measurements of the sound pressure and skin temperature on the portions of the lower surface of the wing immersed in the jet flow. The tests were conducted over a range of angles of attack from -8 to 16 degrees for Reynolds numbers from 1.8 x 10 to the 6th power to 4.4 x 10 to the 6th power and a range of momentum coefficients from 0 to 2.0. In general, the aerodynamic results of this investigation made with a large-scale hotjet model verified the results of previous investigations with small models powered by compressed-air jets. Although blowing was only done over the inboard portion of the wing, substantial amounts of induced lift were also obtained over the outboard portion of the wing. Random acoustic loadings on the wing surface were high enough to indicate that fatigue failure from this source would require special consideration in the design of an external-flow jet flap system for an airplane. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE