Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane

reportActive / Technical Report | Accession Number: ADA801415 | Open PDF

Abstract:

Wind-tunnel investigation was conducted to further the development of leading-edge wing inlets. Aerodynamic tests of the basic wing and the original inlet were also made. The original inlet was found to decrease the maximum lift coefficients and to have critical Mach numbers below those of the wing with the basic nose installed. The total pressure recovery in the oil cooler ducts was poor, regardless of the inlet installation. Two inlets were developed that should be satisfactory for a 4-engine airplane.

Author(s):
Bartlett, Jr., Walter A. ; Goral, Edwin B.
Author Organization(s):
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY
Descriptive Note:
Research memo.
Pagination:
0069

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
NACA-RM-L6L11
Monitor Series:
NACA
 Subject Terms
Joint Capability Areas:
JCA_7.2.1_Mitigate Lethal Effects; JCA_7.2_Mitigate; JCA_7_Protection
Modernization Areas:
Directed Energy
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*WING INLETS, TEST METHODS, COEFFICIENTS, DUCTS, WIND TUNNEL TESTS, MACH NUMBER, AERODYNAMIC LIFT, AERODYNAMICS, OIL COOLERS, AIRCRAFT, LEADING EDGES
Keyword(s):
ATI 12036, ATI COLLECTION
Report Date:
1947 Mar 11
Creation Date:
2011 Aug 29