**"Computational Aerodynamics and Aeroacoustics" ** on published by Springer Nature. __ __

Monograph titled **"High-Performance Computing of Big Data for Turbulence and Combustion" ** is published by Springer Nature Switzerland. __ https://www.springer.com/gp/book/9783030170110 __

**"DNS of Wall-Bounded Turbulent Flows: A First Principle Approach" ** is published by Springer Nature. __ https://www.springer.com/us/book/9789811300370 __

Symposium proceedings on **"Advances in Computation, Modeling and Control of Transitional and Turbulent Flows." ** is published by World Scientific Publishing Company, Singapore. __Link of Book.__

New Book titled **"Theoretical and Computational Aerodynamics" ** is published by John Wiley Press. __Book Review.__

**"High Accuracy Computing Methods: Fluid Flows and Wave Phenomena" ** is published by Cambridge University Press. __ http://www.cambridge.org/9781107023635 __

**"Instabilities of Flows and Transition to Turbulence" ** is published by CRC Press/ Taylor & Francis. __ http://www.crcpress.com/product/isbn/9781439879443 __

Monograph titled **"Instabilities of Flow: with and without Heat Transfer and Chemical Reaction" ** is published by Springer Wien-New York.

__ http://link.springer.com/book/10.1007%2F978-3-7091-0127-8 __

Textbook titled **"Fundamentals of CFD" ** published by Universities Press, Hyderabad, India. **"CFD Book Review"**

"International Conference On Metacomputing"

"National Symposium on HPC in Academia and Beyond"

TALK at BESU, Shibpur, Kolkata on March 4 2010 by Prof. T.K. Sengupta.

MIT PRESENTATIONS (click on the links below)

PLENARY TALK on DNS by Prof T.K. Sengupta at 5th M.I.T Conf. on Advances in CFD (2009).

ICOMEC-2011 Presentation on DNS in CFD by Prof. T. K. Sengupta, S. Bhaumik and Y. G. Bhumkar

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**Flow over SHM1 Airfoil**

•Flow over SHM1 airfoil is computed for zero angle of attack for cruise Reynolds number of 10.3 million.

The flow over SHM1 at zero angle of attack (Re=10.3 million) attains statistical steady state, separation bubbles are generated and convected near the trailing edge as shown in animation below.

Above two figures show stream function and vorticity contour plots, respectively.

Methods/Schemes used in computations

• Convective terms in VTE have been discretized using S-OUCS3 schemes of Dipankar & Sengupta.

• Diffusion terms in VTE are discretized using CD-2 scheme.

• Four stage Runge-Kutta (RK4) method is used to march forward in time

• BiCGSTAB algorithm is used to solve both the Poisson equations: SFE & PPE (solved explicitly to determine the load parameters).

• For high Re flows, a wide band of scales are excited. To control aliasing error arising out of convection terms, dominant at higher wave numbers, dissipation is added via upwinding the convection terms and by explicitly filtering the solution after every time step using sixth order composite filter [Sengupta et al. (2009)].

Effects on adding FST

Free-stream turbulence is omnipresent in all fluid flows, so its important to include its effects in simulations. Here FST is modelled as described by Sengupta et. al. (2006)

The figure below shows effect of FST in Cl vs time plot

Fluctuations in Cl increases with increase in FST and these fluctuations are present at all frequency levels which is shown in FFT of Cl data shown below.

FFT of Cl shows fluctuations increase with FST that has high amplitudes for low frequencies, which is shown below.

The figures below show effects of FST in Cd vs time plot

Fluctuations in Cd increase with FST and fluctuations are present at all frequencies, shown in FFT of Cd data.

FFT of Cd has high amplitude at low frequencies, shown in figure below.

Effect of FST on shedding pattern are shown below.

The figure (below) shows stream function contours near the trailing edge of SHM1 airfoil, plotted at similar stage of bubble formation and for the same psi (Ψ) contour levels.

From the figure it is noted that the size of bubble on lower surface of the airfoil is larger for all FST cases compared to without FST case.

The figure (below) shows instantaneous vorticity contours near the trailing edge of SHM1 airfoil, plotted for same vorticity contours and at approximately similar stage of shedding.

From the figure (vorticity contours) it is observed that the size of the vortex at the bottom of the airfoil is larger for the cases with FST as compared to without FST case.