Date: Tue, 19 Mar 2024 05:38:21 -0500 (CDT) Message-ID: <89001754.19338.1710844701728@cornell1-cos-conf1.managed.contegix.com> Subject: Exported From Confluence MIME-Version: 1.0 Content-Type: multipart/related; boundary="----=_Part_19337_1162269441.1710844701728" ------=_Part_19337_1162269441.1710844701728 Content-Type: text/html; charset=UTF-8 Content-Transfer-Encoding: quoted-printable Content-Location: file:///C:/exported.html
Author(s): Sebastian Vecchi, ANSYS Inc.
Problem Specification
1. Start-Up
2. Geometry=
3. Mesh
4. Physics Setup
5. Results
6. =
Verification & Validation
Created using ANSYS 18.1
A wing with a NACA 0012 airfoil sectio= n has a chord of 1 meter, a span of 1 meter, and a thickness of 0.01 meter.= The wing is made of Aluminum 6061-T6. If air moves at 987.84 km/hour aroun= d the airfoil, find the velocity vectors of compressible flow over the airf= oil.