Zobrazeno 1 - 10
of 32
pro vyhledávání: '"Iraj M. Kalkhoran"'
Publikováno v:
AIAA Journal. 56:3071-3085
A computational model is developed using a delayed detached-eddy simulation to examine the various aspects of shock-wave/vortex interactions, in which the specific case of naturally formed bow shoc...
Autor:
Iraj M. Kalkhoran, Pankaj Rajput
Publikováno v:
Journal of Propulsion and Power. 33:213-226
The aim of this investigation was to perform a parametric computational study of the blockerless engine thrust reverser system concept. Early experimental investigations had revealed that injection flow rates of the order of 3% of the fan flow were n
Publikováno v:
23rd AIAA/CEAS Aeroacoustics Conference.
Autor:
Iraj M. Kalkhoran, Ryan B. Caeti
Publikováno v:
AIAA Journal. 52:26-32
In this study, a method for reducing the jet noise of a high-speed jet is presented. An array of microjets was immersed within the centerline of an underexpanded Mach 1.6 jet in an effort to reduce the overall sound pressure level and alter its spect
Autor:
Valerio Magri, Iraj M. Kalkhoran
Publikováno v:
Computers & Fluids. 86:343-356
The purpose of the present study was to investigate the interaction between stream-wise vortices with oblique shock fronts of various intensities. A three-dimensional, Navier–Stokes solution of the problem with an orthogonal grid incorporating a RA
Autor:
Hamideh Pourhashem, Iraj M. Kalkhoran
Publikováno v:
8th AIAA Flow Control Conference.
Autor:
Iraj M. Kalkhoran, Pankaj Rajput
Publikováno v:
54th AIAA Aerospace Sciences Meeting.
The aim of this investigation was to perform a parametric computational study of the Blockerless Engine Thrust Reverser System (BETR) concept. Early experimental investigations had revealed that injection flow rates of the order of 3% of the fan flow
Autor:
Iraj M. Kalkhoran, Pankaj Rajput
Publikováno v:
33rd AIAA Applied Aerodynamics Conference.
Autor:
Iraj M. Kalkhoran, C Paek
Publikováno v:
AIAA Journal. 42:1264-1268
Autor:
Ivana Milanovic, Iraj M. Kalkhoran
Publikováno v:
The Aeronautical Journal. 106:39-49
An experimental study of the supersonic vortices from a 75° swept-back delta wing has been carried out in a Mach 2.49 stream. Five-hole conical probe surveys were conducted at the trailing edge of the planform for 7° and 12° angles-of-attack. The