Author: Harris M. SchurmeierPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 304
Book Description
Design and Operation of a Continuous-flow Hypersonic Wind Tunnel Using a Two-dimensional Nozzle
Author: Harris M. SchurmeierPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 304
Book Description
Design and Operation of a Continous-flow Hypersonic Wind Tunnel Using a Two-dimensional Nozzle
Author: H. M. SchurmeierFluid Flow Analysis of a Hot-core Hypersonic-wind-tunnel Nozzle Concept
Author: John B. AndersPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Book Description
A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
NOL Hypersonic Tunnel No. 4
Author: James E. DanbergPublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 84
Book Description
NOL's Hypersonic Tunnel No. 4 is a continuous blow-down hypersonic tunnel designed for research and development testing of models, instrumentation, and wind tunnel components. It can operate at Mach numbers from 5 to 10 with supply pressures up to 52 atmospheres and supply temperatures up to 1700 R. This report summarizes the pertinent aerodynamic design criteria and operating experience compiled during its first eleven years of operation. Included are descriptions of the major components and their performance along with the flight simulation capability of the facility and a bibliography of previously published reports. (Author).
Investigation of the Flow Through a Single-stage Two-dimensional Nozzle in the Langley 11-inch Hypersonic Tunnel
Author: Charles H. McLellanPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 30
Book Description
The flow through a two-dimensional, 10.5- by 10-inch nozzle with a design Mach number of 7.08 was investigated. The nozzle was mounted in an intermittant type of tunnel and tested with stagnation conditions of 25 atmospheres and 1210 degrees R. The flow was reasonably uniform in a region approximately 5 inches square in the center of the test section. The Mach number in this region was about 6.86.
A Summary of Design Techniques for Axisymmetric Hypersonic Wind Tunnels
Author: Ying-Nien YuPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 186
Book Description
Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section
Author: Rudolf HermannPublisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 90
Book Description
In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects
Author: Ralph C. TollePublisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 274
Book Description
Design and Calibration of a Mach 2.5 Two Dimensional Wind Tunnel Nozzle
Author: Leon A. VorstPublisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 174
Book Description
Author: Harold N. Riise