Investigation of Pressure Distributions Over Planar, Twisted, and Cambered Wings in a Hypersonic Shock Tunnel

Item

Title
Investigation of Pressure Distributions Over Planar, Twisted, and Cambered Wings in a Hypersonic Shock Tunnel
Date
1962
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
ASD TDR 62-171
Creator
Scheuing, Richard A.
Leng, Jarvis
Corporate Author
Grumman Aircraft Engineering Corporation
Laboratory
Flight Control Laboratory
Extent
178
Identifier
AD0276896
Access Rights
ASTIA
Distribution Classification
1
Contract
AF 33(616)-6846
DoD Project
8219
DoD Task
821901
DTIC Record Exists
No
Distribution Change Authority Correspondence
CFSTI PER SEG LTR
Abstract
An experimental program was undertaken at nominal Mach numbers of 12 and 19 to measure the changes in the pressure distributions of two basic wing planforms due to distortions in their profile shape. The models included three rectangular planform wings with a flat profile, a circulararc cambered profile, and a profile with symmetrical linear twist, and three 70 degrees delta planform wings with a flat profile, a circulararc cambered profile, and a sine-wave cambered profile. Angle of attack was varied from 0 to 15 degrees. Data are presented in both tabular and graphical form. Appended is a description of the tunnel calibration procedures, and a description of the development of a Grummandesigned piezoelectric pressure transducer employed in obtaining the data.
The abstract for this report is either unavailable or has yet to be entered
Report Availability
Full text available
Date Issued
1962-05
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
ASDTDR62-171.pdf