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Page 1 of 4 February 22, 2010 SUBJECT: Mandatory Test Problem for Support Engineer Applicants Overview In addition to requiring critical thinking and...

Consider a CFD simulation of a nominal wing configuration having a span of 1 meter
and operating at an angle of attack of 5 degrees. Images depicting the resulting
pressure field on the wing as well as the surface mesh are shown in Illustration 1 and 2.
For design purposes, the client is interested in knowing what the integral loading on the
wing is at 10 discrete air stations along the span. To provide this data to the client, it is
necessary to integrate the forces on the wing over the 10 different regions of interest.
Each air station has a constant width of .1 m. The air stations are depicted graphically
in Illustration 3.
Page 1 of 4 February 22, 2010 SUBJECT: Mandatory Test Problem for Support Engineer Applicants Overview In addition to requiring critical thinking and problem solving skills, the position of Support Engineer requires employees to apply these skills to practical applications stemming from client requests, consulting projects, etc. In order to demonstrate these abilities to ACUSIM, we are requiring the solution of a representative test problem for all applicants. If the following test problem is not completed, we will not read your resume. Background A common request by users is for the development of custom post-processing techniques to better utilize the output of a CFD simulation within their established design process. It is often the role of the support staff to assist users with this task. Therefore, the test case will focus on solving a representative problem that falls within this category. Problem Description Consider a CFD simulation of a nominal wing configuration having a span of 1 meter and operating at an angle of attack of 5 degrees. Images depicting the resulting pressure field on the wing as well as the surface mesh are shown in Illustration 1 and 2. For design purposes, the client is interested in knowing what the integral loading on the wing is at 10 discrete air stations along the span. To provide this data to the client, it is necessary to integrate the forces on the wing over the 10 different regions of interest. Each air station has a constant width of .1 m. The air stations are depicted graphically in Illustration 3. ACUSIM Software, Inc. 2685 Marine Way, Suite 1421, Mountain View, CA 94043 Tel: (650) 988-9700 Fax: (650) 988-9770 [email protected] http://www.acusim.com
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Page 2 of 4 Illustration 4 shows the coordinate system and flow direction for the conditions of interest. Note that the wing is aligned with the global x,y,z coordinate system, while the direction of flow is rotated about the z-axis to produce the 5° angle of attack. Solution Requirements Interested applicants are required to submit a program that provides the integrated lift and drag forces at each air station along the span of the wing. The program may be written in C, Perl, Python, or shell scripting language. Any assumptions should be clearly stated in the form of comments within the program. The following input data files are provided: ACUSIM Software, Inc. 2685 Marine Way, Suite 1421, Mountain View, CA 94043 Tel: (650) 988-9700 Fax: (650) 988-9770 [email protected] http://www.acusim.com Illustration 1: Pressure distribution on nominal wing Illustration 3: Graphical depiction showing air stations of interest Illustration 2: Surface mesh on the wing model Illustration 4: Coordinate system and flow direction for wing simulation. y x Flow direction (5° angle of attack)
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This question was asked on Mar 25, 2010.

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