Volume 14 (2021)
Volume 13 (2020)
Volume 12 (2019)
Volume 11 (2017)
Volume 10 (2013)
Volume 9 (2012)
Volume 8 (2011)
Volume 7 (2010)
Volume 6 (2009)
Volume 5 (2008)
Volume 4 (2007)
Volume 3 (2006)
Volume 2 (2005)
Volume 1 (2004)
1. Effect of Wing Sweep Angle on the Vortex Interaction of a Tail-Wing Configuration

Bahman Jahromi; M.R. Soltani; M. Masdari

Volume 9, Issue 1 , Winter and Spring 2012

  The goal of this investigation is to study the effect of wing sweep angle on the horizontal wing-body- tail configurations in subsonic flow. For this purpose, a series of wind tunnel tests were conducted on a model having a moveable horizontal tail and a wing planform with different sweep angles. Tests ...  Read More

2. Wind Tunnel Investigation of Pressure Distribution and Transition Position of a Swept 3D Wing

Mohammad Reza Dr. Soltani; M. Masdari; M. Seidjafari; Kaveh Ghorbanian

Volume 7, Issue 2 , Summer and Autumn 2010, , Pages 132-137

  Extensive wind tunnel tests are conducted to evaluate surface pressure distribution of a semi span swept wing. The wing section has a laminar flow airfoil similar to NACA 6-series airfoils. The investigations are conducted at various speeds and angles of attack. Surface pressure distribution over the ...  Read More


Kaveh Amiri; Mohammad Reza Dr. Soltani; H. Haghiri; Mahmood Mani

Volume 6, Issue 2 , Winter and Spring 2009, , Pages 63-70

  A trisonic wind tunnel has been modified to improve its flow quality when operating at transonic speeds through perforated walls and side suctions. The usefulness of such a perforated wall, already known, is reduction of the blockage effect as well as the shock elimination. Two types of perforated walls ...  Read More

4. Impact of Body on the Tail Surface Flowfield at High Incidences

A. Davari; M. Hadi Dulabi; Mohammad Reza Dr. Soltani; F. asakari

Volume 6, Issue 1 , Winter and Spring 2009, , Pages 25-35

  An experimental study was performed to investigate the effects of the body angle of attack on the tail surface pressure distribution for a half body-tail combination in subsonic flow. The results show, in small deflection angle regions, that the tail deflection has the same effect on the surface pressure ...  Read More

5. Experimental Study of Vortex Shapes behind a Wing Equipped with Different Winglets

Mehdi Nazarinia; Mohammad Reza Dr. Soltani; Kaveh Ghorbanian

Volume 3, Issue 1 , Winter and Spring 2006, , Pages 1-20

  An extensive experimental study is conducted to examine effects of different winglet-shapes and orientations on the vortex behind a wing, static surface pressure over the wing, and wing wake of a swept wing at various angles of attack. Four types of winglets, spiroid (forward and aft), blended, and winggrid ...  Read More

6. Effect of Amplitude and Mean Angle of Attack on the Unsteady Surface Pressure of a Pitching Airfoil

Mohammad Reza Dr. Soltani

Volume 2, Issue 4 , Summer and Autumn 2005, , Pages 9-26

  Details of pressure distributions, on a two dimensional airfoil oscillating in pitch through stall, in a 0.8 0.8 m low-speed wind tunnel are presented. Pitching occurred about the airfoils quarter-chord axis. Pitch rate, Reynolds number, and oscillation amplitudes were varied to determine the effects ...  Read More