NDLI: Wind tunnel force and pressure tests

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Wind tunnel force and pressure tests

Content Provider	NASA Technical Reports Server (NTRS)
Author	Wentz Jr., W. H.
Copyright Year	1981
Description	Force and surface pressure distributions were measured for a 13% medium speed (NASA MS(1)-0313) airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted in the Walter Beech Memorial Wind Tunnel at a Reynolds number of 2.2 million and a Mach number of 0.13. Results include lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions. The basic airfoil exhibits low speed characteristics similar to the GA(W)-2 airfoil. Incremental aileron and spoiler performance are quite comparable to that obtained on the GA(W)-2 airfoil. Slotted flap performance on this section is reduced compared to the GA(W)-2, resulting in a highest c sub l max of 3.00 compared to 3.35 for the GA(W)-2.
File Size	5887539
Page Count	120
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19830008016
Archival Resource Key	ark:/13960/t6sz1454f
Language	English
Publisher Date	1981-06-01
Access Restriction	Open
Subject Keyword	Aerodynamics Slots Pitching Moments Flaps Control Surfaces Wind Tunnel Tests Pressure Distribution Ailerons Airfoils Angle of Attack Aerodynamic Forces Spoilers Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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