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Accession Number:
AD0102312
Title:
INVESTIGATION OF THE AIR-FLOW-REGULATION CHARACTERISTICS OF A TRANSLATING-SPIKE INLET WITH TWO OBLIQUE SHOCKS FROM MACH 1.6 TO 2.0
Corporate Author:
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH GLENN RESEARCH CENTER
Report Date:
1956-07-24
Abstract:
The air-flow regulation and pressure recovery of a translating-cone inlet with a 15 deg conical half-angle and a 10 deg additional compression was investigated for a range of spike positions at Mach numbers of 0.6 and 1.6 to 2.0 at zero angle of attack.
Descriptive Note:
Research memo.
Pages:
0019
Distribution Statement:
Approved for public release; distribution is unlimited.
File Size:
0.80MB
