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Summary
Summary
Use a low speed wind tunnel to measure the pressures at various points along a wing at various different velocities and angles of attack. Use this data to determine a pressure distribution at the different velocities and angles of attack. Use this pressure distribution to calculate the lift and pressure drag for the various test cases.
Disclaimer:
This project was rushed at the end and some of the code had unresolved errors. This can be seen in some of the coefficients of pressure being more than 1 as well as in the coefficients of lift and drag being much larger than 1. The group was aware of these errors, but was unable to fix them before the labs due date.
Quad Chart
Quad Chart
Quad Chart Group 16 Draft.pptxReport Summary
Report Summary
ASEN_2002__Aero_Lab_2.pdfPage updated
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