On The Flow Over A Cone-cylinder Body At Mach Number One

Item

Title
On The Flow Over A Cone-cylinder Body At Mach Number One
Date
1952
Index Abstract
Coming Soon
Photo Quality
Undetermined
Report Number
WADC TR 52-295
Corporate Author
Aircraft Laboratory, Wright Air Development Center
Extent
33
NTRL Accession Number
AD003244
Identifier
AD0003244
AD Number
3244
Access Rights
Unknown
Distribution Classification
1
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
AFAL ltr
Distribution Change Action Date
11/7/2002
Abstract
The flow over a cone-cylinder body at Mach number one and zero angle of attack is computed by a niimerical method in which the subsonic region is coriputed by the relaxation method while the supersonic region is constructed by the niethod of characteristics. The sonic line is then determined by an iterative process. The results indicate that transonic similarity law proposed by von Karman and Oswatitsch and Berndt based upon slender body theory can be extended to cover cone-cylinder bodies of practical slenderness ratios.
Report Availability
Not available via Contrails
Date Issued
1952-01
Index In
DTIC
Type
report
Creator
Yoshihara, Hideo