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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
- 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