Author: Emory Vanoy MobleyPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 262
Book Description
Charts for the Analysis of Supersonic Flow Around Cones at Large Angles of Attack
Author: Emory Vanoy MobleyPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 262
Book Description
Supersonic Flow about Cones at Large Angles of Attack
Author: Clive Allen John FletcherPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 294
Book Description
A numerical method is presented which is applicable to the supersonic inviscid flow about cones inclined at such angles of attack that a substantial region of supersonic crossflow exists (M sub cr 1). The method is based partly on the method of Gilinskii, Telenin and Tinyakov and partly on the method of characteristics. The method produces results that compare favorably with experimental data and with the results of other numerical methods. The numerical method has produced results in the range: free stream Mach number =3 to 16; incidence, alpha = 10 to 50 deg, nose cone angles, theta sub b = 5 to 30 deg. These results demonstrate similar trends with free stream Mach number, alpha and theta sub b as obtained for subsonic crossflow Mach numbers (m sub cr
Tables for Supersonic Flow Around Right Circular Cones at Small Angle of Attack
Author: Joseph L. SimsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 440
Book Description
Tables for Supersonic Flow Around Right Circular Cones at Zero Angle of Attack
Author: Joseph L. SimsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 462
Book Description
Computation of the Inviscid Supersonic Flow about Cones at Large Angles of Attack by a Floating Discontinuity Approach
Author: James Edward DaywittPublisher:
ISBN:
Category :
Languages : en
Pages : 100
Book Description
Supersonic Flow Around Right Circular Cones, Tables for Zero Angle of Attack
Author: Joseph L. SimsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 882
Book Description
Tables for Supersonic Flow of Helium Around Right Circular Cones at Zero Angle of Attack
Author: Joseph L. SimsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
Book Description
The results of the calculation of supersonic flow of helium about right circular cones at zero angle of attack are presented in tabular form. The calculations were performed using the Taylor-Maccoll theory. Numerical integrations were performed using a Runge-Kutta method for second-order differential equations. Results were obtained for cone angles from 2.5 to 30 degrees in regular increments of 2.5 degrees. In all calculations the desired free-stream Mach number was obtained to five or more significant figures.
Supersonic Flow Around Cones at Large Yaw
Author: G. B. W. YOUNGPublisher:
ISBN:
Category :
Languages : en
Pages : 43
Book Description
Equations were developed for the flow properties in the region bounded by a supersonic cone body at large angle of attack and its attached shock wave, for use with the tabulations of Kopal. A comparison of the theoretical results is made with the experimental data of Cronvich. A slight discrepancy which increases with increasing Mach number was found in the value of K sub DYH, the yawing head drag as tabulated by Kopal. (Author).
Laminar Boundary Layer on Cone in Supersonic Flow at Large Angle of Attack
Author: Franklin K. MoorePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 13
Book Description
The laminar-boundary-layer flow about a cone at large angles of attack to a supersonic stream has been analyzed in the plane of symmetry. At the bottom of the cone, velocity profiles were obtained showing the expected tendency of the boundary layer to become thinner on the under side of the cone as the angle of attack is increased. At the top of the cone, the analysis failed to yield unique solutions, except for small angles of attack. Beyond a certain critical angle of attack, boundary-layer flow does not exist in the plane of symmetry, thus indicating separation.
Author: Abdollah Modavi