Author: Malcom GreenPublisher:
ISBN:
Category :
Languages : en
Pages : 78
Book Description
An Experimental Investigation of Supersonic Flow in Long Channels
Author: Malcom GreenExperimental Investigation of the Sudden Expansion of Supersonic Flow Into a 90 ̊vee Shaped Channel
Author: Gary L. BarrPublisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 118
Book Description
An Experimental Investigation of Supersonic Flow
Author: Joseph Francis Madden (Jr.)Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
Experimental Investigation of Supersonic Flow in the Neighborhood of a Forward-facing Step
Author: Edward Malcolm Harvey NewtonPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 100
Book Description
An Experimental Investigation of Separated Turbulent Supersonic Flow at M
Author: Robert Earl WilsonAn Experimental Investigation of the Laminar Boundary Layer on a Spinning Ogive Cylinder in Supersonic Flow
Author: William C. RagsdalePublisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 160
Book Description
Pitot pressure surveys were made of the laminar boundary layer on an ogive-cylinder model at Mach 3.02 and 4.10. Surveys were made at five stations along the model, at angles of attack of zero and four degrees, with and without spin. Tests with spin were performed at Mach 3.02. The pitot pressure data has been used to compute boundary-layer velocity profiles, and results from two data-reduction procedures are presented. Some comparisons are made with theoretical velocity profiles for the zero spin, zero angle-of-attack case. (Author).
Experimental Investigation of Skin Friction and Heat Transfer at the Wall of a Supersonic Flow Channel
Author: Frederic Alan GruenichPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 88
Book Description
Experimental Investigation of Supersonic Flow with Detached Shock Waves for Mach Numbers Between 1.8 and 2.9
Author: W. E. MoeckelPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 56
Book Description
Results of an experimental investigation of the flow near the nose of plane and axially symmetric bodies in the presence of detached shock waves are compared with predictions of theory. The location of the detached shock wave was determined from schlieren photographs for a variety of nose shapes over a range of free-stream Mach numbers from 1.8 to 2.9. At a Mach number of 1.9, the form of the detached wave and the pressure distribution over the body were investigated for each nose shape. In addition, the relation between shock location and flow spillage was determined for several axially symmetric nose inlets.
An Analytical and Experimental Investigation of Supersonic Flow Over an Electrostatically Charged Wedge
Author: H. Ronald MillerExperimental Investigation of Supersonic Flow Separation Over a Rearward Facing Step
Author: Jain-Ming WuPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 10
Book Description