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Wind-tunnel calibration of a combined pitot-static tube and vane-type flow-angularity indicator at Mach numbers of 1.61 and 2.01A limited calibration of a combined pitot-static tube and vane-type flow-angularity indicator has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01. The results indicated that the angle-of-yaw indications were affected by unsymmetric shock effects at low angles of attack.
Document ID
19930084583
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Sinclair, Archibald R
Mace, William D
Date Acquired
August 29, 2013
Publication Date
October 1, 1956
Report/Patent Number
NACA-TN-3808
Report Number: NACA-TN-3808
Accession Number
93R13873
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
INSTRUMENTS, FLIGHT
RESEARCH EQUIPMENT, FREE-FLIGHT

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