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Results of Flight Tests at Supersonic Speeds to Determine the Effect of Body Nose Fineness Ratio on Body and Wing Drag

Results of Flight Tests at Supersonic Speeds to Determine the Effect of Body Nose Fineness Ratio on Body and Wing Drag

Authors :
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
Katz, Ellis R.
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
Katz, Ellis R.
Source :
DTIC
Publication Year :
1947

Abstract

Supersonic rocket-powered, winged, and wingless models were tested to Mach 1.4 to determine effect of nose fineness ratio on total and component drag. Winged models with and without sweepback were tested. Results show that increased nose fineness ratio increased wing-body drag near Mach 1.0 but decreased total drag at higher Mach. Increased fineness ratio decreased drag of wingless bodies. Wing drag values change with installation on different body shapes.

Details

Database :
OAIster
Journal :
DTIC
Notes :
text/html, English
Publication Type :
Electronic Resource
Accession number :
edsoai.ocn832052723
Document Type :
Electronic Resource