Accession Number:

AD0261196

Title:

TRANSITION OF THE LAMINAR BOUNDARY LAYER ON A DELTA WING WITH 74 DEGREE SWEEP IN FREE FLIGHT AT MACH NUMBERS FROM 2.8 TO 5.3

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-08-01

Pagination or Media Count:

1.0

Abstract:

The test were conducted at Mach numbers from 2.8 to 5.3, with model surface temperatures small compared to boundary-layer recovery temperature. The effects of Mach number, unit Reynolds number, leading-edge diameter, temperature ratio,AND ANGLE OF ATTACK WERE INVESTIGATED IN AN EXPLORATORY FASHION. The results were compared to results of wind-tunnel tests of swept wings and to results f free-flight tests for unswept leading edges. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE