ON THE FLOW OVER A CONE-CYLINDER BODY AT MACH NUMBER ONE
AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OH FLIGHT CONTROL LAB
Pagination or Media Count:
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.
- Fluid Mechanics