BEGIN:VCALENDAR

VERSION:2.0

PRODID:-//wp-events-plugin.com//7.2.3.1//EN

TZID:Asia/Jerusalem

X-WR-TIMEZONE:Asia/Jerusalem
BEGIN:VEVENT

UID:0-1560@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20260525T133000

DTEND;TZID=Asia/Jerusalem:20260525T143000

DTSTAMP:20260524T091906Z

URL:https://aerospace.technion.ac.il/events/seminar-suryapratap-shinde-25m
 ay2026/

SUMMARY:Impact of Aerodynamic Modeling on Aeroelastic Simulations of Straig
 ht and Swept wings
DESCRIPTION:Lecturer:Suryapratap Shinde\n Faculty:The Stephen B. Klein Facu
 lty of Aerospace Engineering\n Institute:Technion – Israel Institute of 
 Technology\n Location:Classroom 240\, 1st floor\, Aerospace Eng. building\
 n Zoom: https://technion.zoom.us/j/98372598857\n Abstract: Highly flexible
  wings exhibit strong aeroelastic coupling\, and the accuracy of static lo
 ad and deformation predictions depends critically on the fidelity of the a
 erodynamic model. Previous studies on the Pazy wing benchmark have focused
  mainly on structural modelling while relying on low-order aerodynamic app
 roaches. These studies showed that straight-wing response can be predicted
  reasonably well with simplified aerodynamics\, whereas swept-wing cases e
 xhibit larger discrepancies when the deformed three-dimensional geometry i
 s not properly resolved. This suggests that the importance of aerodynamic 
 fidelity depends strongly on wing planform and deformation characteristics
 .\nThis research investigates the static aeroelastic behaviour of the Pazy
  wing using three aerodynamic models of increasing fidelity\, all coupled 
 to the same linear elastic modal structural framework. The models consider
 ed are a reduced-order strip-theory\, a potential-flow panel method implem
 ented in FEMAP–Nastran\, and the EZair Euler CFD solver. Straight\, 10
 ◦ swept\, and 20◦ swept wing configurations are analysed over a range 
 of freestream velocities and angles of attack within a deformation regime 
 where the structural response remains predominantly linear. The comparison
  is based on key aerodynamic and structural response parameters\, includin
 g spanwise aerodynamic load distribution\, sectional lift variation\, wing
  twist\, twisting moment\, and tip deflection\, in order to isolate the in
 fluence of aerodynamic fidelity on the predicted static aeroelastic respon
 se.\nThe results show that\, for the straight wing\, all three approaches 
 give broadly consistent predictions\, indicating that low-order aerodynami
 c models are adequate for preliminary analysis in the linear deformation r
 egime. For swept wings\, however\, bending–torsion coupling induces nose
 -down twist and inboard load shift\, leading to increasingly noticeable di
 fferences between the low- and high-fidelity aerodynamic models. The large
 st discrepancies occur for the 20◦ swept configuration. These findings d
 emonstrate that accurate static aeroelastic prediction of flexible swept w
 ings requires aerodynamic models capable of resolving the actual deformed 
 three-dimensional wing geometry.\nThis work is towards an M.Sc. degree und
 er the supervision of Prof. Daniella Raveh\, The Stephen B. Klein Faculty 
 of Aerospace Engineering\, Technion\n Details: \n 
CATEGORIES:Seminars
LOCATION:Classroom 240\, 1st floor\, Aerospace Eng. building

END:VEVENT

BEGIN:VTIMEZONE

TZID:Asia/Jerusalem

X-LIC-LOCATION:Asia/Jerusalem

BEGIN:DAYLIGHT

DTSTART:20260327T030000

TZOFFSETFROM:+0200

TZOFFSETTO:+0300

TZNAME:IDT

END:DAYLIGHT

END:VTIMEZONE
END:VCALENDAR