Investigation of the flow over simple bodies at Mach numbers of the order of 20 /
| Data(s) |
31/12/1969
|
|---|---|
| Resumo |
"It is shown that adequate means are available for calculating inviscid direct and induced pressures on simple axisymmetric bodies at zero angle of attack. The extent to which viscous effects can alter these predictions is indicated. It is also shown that inviscid induced pressures can significantly affect the stability of blunt, two-dimensional flat wings at low angles of attack. However, at high angles of attack, the inviscid induced pressure effects are negligible." Prepared at the Langley Research Center, Langley Field, VA. Cover title. "August 1960."--Cover. Includes bibliographical references. "It is shown that adequate means are available for calculating inviscid direct and induced pressures on simple axisymmetric bodies at zero angle of attack. The extent to which viscous effects can alter these predictions is indicated. It is also shown that inviscid induced pressures can significantly affect the stability of blunt, two-dimensional flat wings at low angles of attack. However, at high angles of attack, the inviscid induced pressure effects are negligible." Mode of access: Internet. |
| Identificador | |
| Idioma(s) |
eng |
| Publicador |
Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce, |
| Direitos |
Items in this record are available as Public Domain, Google-digitized. View access and use profile at http://www.hathitrust.org/access_use#pd-google. Please see individual items for rights and use statements. |
| Palavras-Chave | #Fluid dynamics. #Aerodynamics, Supersonic. #Aerodynamics. |
| Tipo |
text |
