SR-72 Confirmed: Mach 6 Project Blackswift

a reply to: mightmight
The big question is when we will see it in the white , I think if the tech is ready for civilian use , surely the military will have it soon.

Investigation on gaseous jet in forebody/inlet for shock-induced combustion ramjet (shcramjet) engines

www.sciencedirect.com...

a reply to: darksidius
I think its the case of the Military having it for quite a while and the tech slowly trickling out to the white..

a reply to: Blackfinger
Specifically a case of being allowed to use the tech for the civilian market since the military is moving on from turboramjet solutions to true hypersonics.

An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles

www.sciencedirect.com...

Investigations on flowfield behavior and resistance backpressure characteristics of supersonic cascade with boundary layer suction

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Numerical investigation on behaviors of shock train in a hypersonic inlet with translating cowl

www.sciencedirect.com...

Note: This is all white world for the Chinese. I am sure their classified stuff is further along. This is just want they are willing to show the world.

More White World Chinese Hypersonics:

Effect of the heat release on the component coordination in the rocket-based combined cycle engine

www.sciencedirect.com...

Flame stabilization with a rear-wall-expansion cavity in a supersonic combustor

www.sciencedirect.com...

And India's:

Optimization of scramjet performance with different fuel injection techniques and flame holder cavities

www.sciencedirect.com...

a reply to: anzha

Performance uncertainty propagation analysis for control-oriented model of a turbine-based combined cycle engine

Uncertainty sources in an integrated turbine-based combined cycle propulsion system considered in this study are located at the air intake system, containing a forebody, a splitter and a cowl. These components endure aerothermodynamic loading and variational pressure distribution due to oblique shocks, which cause them to deform and vibrate. Those deformations and vibrations are largely determined by the local flow field and structural characteristics of the propulsion system in real time, which are hardly to be modeled. The unanticipated uncertainties bring in fluctuations on performance, and may even lead to inlet unstart, compressor surge, or combustor overtemperature, and bring about difficulties in designing control systems that can meet certain requirements on performance. Therefore, uncertainty propagation is made to figure out the effects of uncertainties associated with the three components on control-oriented performance analysis of a turbine-based combined cycle engine. A control-oriented loosely coupled aircraft/propulsion integrated turbine-based combined cycle engine model is built. Monte Carlo Method is utilized to propagate the uncertainties. The results reveal that uncertain sources may bring about failure in mode transition because of the possibility that the gross thrust with uncertainties exceeds the limits. Further analyses indicate that the principal contributor to the uncertainties of outputs in low speed flow path varies from the forebody to the splitter as transition process goes on.

www.sciencedirect.com...

Control-oriented modeling and real-time simulation method for a dual-mode scramjet combustor

Authors:

Ma et al

Abstract:

The control-oriented modeling and real-time simulation method for a dual-mode scramjet combustor has been conducted in this paper. The 1-D unsteady model coupled with isolator shock train model and oblique shock wave modification can treat variable area, fuel addition, combustion heat release, variable specific heat, inflow air vitiation component, wall friction and mixing efficiency. Combustion is simplified into mass and heat addition process. So this paper discusses heat release distribution obtaining method which can be applied in scramjet combustor 1-D flowfield simulation in detail. It is fit for certain scramjet combustor configuration and acceptable over a wide range of inflow conditions. By mixed programming of C and Matlab, the code of model solving is capsuled into S-Function which can be used in SIMULINK. The control-oriented model is built on SIMULINK platform. When the model runs in a single-core 3.6 GHz Intel Core i7-4790 processor, computation time-consuming is found to require 5–10 ms within a control period. The computing speed indicates very promising, because model is compact enough to run in real time, and it can be used as an embedded model in control system research. This model can also be used to analyze unsteady and steady flowfield characteristic. The safety boundary codetermined by unstart and over-temperature is conducted using this model.

www.sciencedirect.com...

Thank you for what you do Anzha

I know Ben Rich did a lot of work getting the Sr71,s engines to work properly with unstarts and variable inlet shockwaves.Took him a year to figure out the variable aerospike intake.Nothing is new just relearnt.

a reply to: Blackfinger

There's a lot that's new. Many things that weren't even thought of in his time.

a reply to: Masisoar

You're welcome.

I know this isnt the thread for it and im a little of topic, but i came across the covair kingfish by accident the other night on the web, rival to the A-12 entry for reconasance aircraft. What do you senior members think? She looks a beuty i think.

a reply to: Rhombus101

That's actually a favorite of mine. She was a beast and I wish they had gone with her.

originally posted by: Zaphod58
a reply to: Rhombus101

That's actually a favorite of mine. She was a beast and I wish they had gone with her.

Didn't the Kingfish eventually evolve into something else?..

More applicable to hypersonic missiles, but this is our generalist hypersonics thread:

Preliminary experimental study on solid rocket fuel gas scramjet

Authors:

Liu et al

Abstract:

In this paper, a new scramjet configuration using solid fuel as propellant is proposed, namely, the solid rocket fuel gas scramjet. The ignition and combustion characteristics and performance of the engine were evaluated by the experimental and numerical methods. The experiment simulated a flight environment of Mach 5.3 at a 21 km altitude. Solid oxygen-poor propellant containing boron was used in this study. The experiment results show that primary rich fuel gas can be reliably ignited in the supersonic combustor and can maintain stable combustion, which demonstrates the feasibility of the solid rocket fuel gas scramjet configuration. The numerical simulation results show that the combustion efficiency of the combustor is 0.56 and the total pressure recovery coefficient is 0.44, which further demonstrates the feasibility of the solid rocket fuel gas scramjet configuration proposed in this paper.

www.sciencedirect.com...

LES of primary breakup of pulsed liquid jet in supersonic crossflow

Authors:

Zhu et al

Abstract:[/b]

The injection of a pulsed liquid jet into supersonic air flow is a promising approach to improving the fuel atomization performance in a Scramjet engine. Therefore, the primary breakup of a pulsed liquid jet in supersonic crossflow is numerically investigated in the present paper. A two-phase flow Large Eddy Simulation (LES) algorithm is developed for simulations of liquid jet atomization in supersonic gas flow. A coupled Level Set and Volume of Fluid (VOF) method is used to track the interface deformation and disintegration. The supersonic gas flow is solved using a compressible flow solver while the liquid phase is solved by an incompressible flow solver. Appropriate boundary conditions are specified at the interface for both solvers to correctly capture the interaction between the gas and liquid phases. The primary atomization of a steady liquid jet with the same average mass flow rate as the pulsed jet is also simulated as a benchmark test case. The liquid velocity pulsation produces a very different primary atomization morphology in comparison with the steady liquid jet, which significantly enhances the primary breakup process. It is observed that Rayleigh-Taylor instability dominates the development of surface waves for the steady liquid jet. For the pulsed liquid jet, the liquid column deformation induced by the liquid velocity pulsation determines the wavelength of the surface waves and thus the liquid jet breakup location. In comparison with the steady liquid jet, the penetration of the pulsed liquid jet increases by 20%, and the width of the wake zone expands by 25%, resulting in improved atomization and mixing performance.

Interesting sighting tonight south of Denver. I was outside around 6 pm (just after dark) helping my friend move a couch up some narrow external stairs (terrible) and I saw what looked like a bright satellite heading west southwest in retrograde.

It was moving a little slower than most satellites appear and I could swear turned ever so slightly. I tried to mark it’s path between some stars to verify this. Anyways, I pointed it out to my friend who easily saw it too. I explained that it was weird as satellites typically move from west to east, north to south, etc., and it looked pretty slow for a satellite. I tried video recording it on my iPhone but it didn’t come out. I also opened my satellite tracking app and nothing there, and nothing moving in that direction anywhere in the vicinity.

Using my map it appeared to be headed nearly straight toward the Vegas area. Reminded me of the old U2 UFO sightings in the 50s. Wonder what it was...