Wind Tunnel Force And Pressure Tests Of Rocket Engine Nozzle Extensions On The 00667 Scale X 15 2 Model At Supersonic And Hypersonic Speeds PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Wind Tunnel Force And Pressure Tests Of Rocket Engine Nozzle Extensions On The 00667 Scale X 15 2 Model At Supersonic And Hypersonic Speeds PDF full book. Access full book title Wind Tunnel Force And Pressure Tests Of Rocket Engine Nozzle Extensions On The 00667 Scale X 15 2 Model At Supersonic And Hypersonic Speeds.
Author | : John B. Anders |
Publisher | : |
Total Pages | : 36 |
Release | : 1972 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download Fluid Flow Analysis of a Hot-core Hypersonic-wind-tunnel Nozzle Concept Book in PDF, ePub and Kindle
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.
Author | : William C. Moseley (Jr.) |
Publisher | : |
Total Pages | : 76 |
Release | : 1970 |
Genre | : Aerodynamic load |
ISBN | : |
Download Wind-tunnel Investigation of the Aerodynamic Pressures on the Apollo Launch Escape Vehicle Configuration Book in PDF, ePub and Kindle
Author | : Rudolf Hermann |
Publisher | : |
Total Pages | : 90 |
Release | : 1950 |
Genre | : Wind tunnels |
ISBN | : |
Download Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section Book in PDF, ePub and Kindle
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.
Author | : Frank K. Lu |
Publisher | : AIAA |
Total Pages | : 694 |
Release | : 2002 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : 9781600864483 |
Download Advanced Hypersonic Test Facilities Book in PDF, ePub and Kindle
Author | : Stephen A. Whitmore |
Publisher | : |
Total Pages | : 24 |
Release | : 1999 |
Genre | : Drag (Aerodynamics) |
ISBN | : |
Download A Base Drag Reduction Experiment on the X-33 Linear Aerospike SR-71 Experiment (LASRE) Flight Program Book in PDF, ePub and Kindle
Drag reduction tests were conducted on the LASRE/X-33 flight experiment. The LASRE experiment is a flight test of a roughly 20-percent scale model of an X-33 forebody with a single aerospike engine at the rear. The experiment apparatus is mounted on top of an SR-71 aircraft. This paper suggests a method for reducing base drag by adding surface roughness along the forebody. Calculations show a potential for base drag reductions of 8 to 14 percent. Flight results corroborate the base drag reduction, with actual reductions of 15 percent in the high-subsonic flight regime. An unexpected result of this experiment is that drag benefits were shown to persist well into the supersonic flight regime. Flight results show no overall net drag reduction. Applied surface roughness causes forebody pressures to rise and offset base drag reductions. Apparently the grit displaced streamlines outward, causing forebody compression. Results of the LASRE drag experiments are inconclusive and more work is needed. Clearly, however, the forebody grit application works as a viable drag reduction tool.
Author | : Naval Ordnance Laboratory (White Oak, Md.). |
Publisher | : |
Total Pages | : 70 |
Release | : 1971 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Download NOL Hypervelocity Wind Tunnel Book in PDF, ePub and Kindle
Author | : James E. Danberg |
Publisher | : |
Total Pages | : 84 |
Release | : 1964 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Download NOL Hypersonic Tunnel No. 4 Book in PDF, ePub and Kindle
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).
Author | : Earl H. Andrews |
Publisher | : |
Total Pages | : 52 |
Release | : 1961 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Investigation of Net-thrust and Base-pressure Characteristics of Cylindrical Afterbodies with Clustered Supersonic Nozzles at Transonic Mach Numbers Book in PDF, ePub and Kindle
A wind-tunnel investigation was conducted at Mach numbers from 0.9 to 1.4. Design Mach numbers of the nozzles were 2.0 and 2.5 and the number of clustered nozzles ranged from two to six. The nozzles had throat-to-base diameter ratios of 0.155, 0.225, 0.278, and 0.320. Some models were tested with various configurations of extended, shrouded, flush, and canted nozzles. The nozzles discharged unheated air from the base at ratios of jet total pressure to free-stream static pressure ranging from 1 to approximately 20. Results showed that both the ratio of total exit area to base area and the number of jets affect the netthrust factor to a significant degree for the extended-nozzle configurations. Good net-thrust factors were obtained with all the model configurations near the design jet total-pressure ratio; however, the extended-nozzle configuration had the highest net-thrust factor over the test jet total-pressure-ratio range. Canting the twin nozzles outward resulted in a favorable thrust factor over a limted jet total-pressureratio range. (Author).
Author | : |
Publisher | : |
Total Pages | : 62 |
Release | : 1976 |
Genre | : |
ISBN | : |
Download Low-speed Wind-tunnel Tests of a Large Scale Blended Arrow Advanced Supersonic Transport Model Having Variable Cycle Engines and Vectoring Exhaust Nozzles Book in PDF, ePub and Kindle
Author | : Paul Czysz |
Publisher | : |
Total Pages | : 116 |
Release | : 1963 |
Genre | : Hypersonic wind tunnels |
ISBN | : |
Download The High-Temperature Hypersonic Gasdynamics Facility Estimated Mach Number 6 Through 14 Performance Book in PDF, ePub and Kindle
The High Temperature Gas Dynamics Facility was developed as a result of the Aeronautical Systems Division's effort to extend the state-of the-art in hypersonic aerodynamic simulation. The facility is a hypersonic wind tunnel supplied with high pressure air, heated from a zirconia dioxide pebble heater. The maximum stagnation pressure and temperature is 40 atres and 4700 R, respectively. This facility is one of four of its kind in this hemisphere and the only Air Force facility of its type. This report discusses the modification of the facility to a two foot diameter test section with a Mach number range of 6 through 14 and its expected performance. This facility is scheduled to be operational in the Fall of 1963.