Title

Shock-Tube Measurements of Step-Blast Loads on a NASA 64A010 Airfoil

Description

Measurements of the transient loads on a two-dimensional airfoil set at various fixed angles of attack and subjected to a step-blast wave in the MIT-ASD shock tube are reported. The free-stream Mach number range employed was 0.4 to 1.0 and the angles of attack ranged from 15 to 60 degrees. Measurements were made using both an interferometer and pressure transducers flush-mounted in the airfoil. During the diffraction period, good agreement was obtained with linearized theory, even up to an angle of attack of 60 degrees. In the post-diffraction period the departures from linearized theory became very large after the leading-edge vortex approached the trailing edge. The transient stalling behavior is examined in detail.

Date

1962

Index Abstract

Contrails and DTIC

Photo Quality

Incomplete

Report Number

ASD TR 61-219

Creator

Ruetenik, J. Ray

Herrmann, Walter

Corporate Author

Massachusetts Institute of Technology

Laboratory

Flight Dynamics Laboratory

Extent

51

Identifier

AD0275496

AD0275496

Access Rights

OTS

Distribution Classification

1

Contract

AF 33(616)-6195

DoD Project

1350

DoD Task

14045

DTIC Record Exists

Yes

Distribution Change Authority Correspondence

None

Report Availability

Full text available by request

Date Issued

1962-02

Abstract

Measurements of the transient loads on a two-dimensional airfoil set at various fixed angles of attack and subjected to a step-blast wave in the MIT-ASD shock tube are reported. The free-stream Mach number range employed was 0.4 to 1.0 and the angles of attack ranged from 15 to 60 degrees. Measurements were made using both an interferometer and pressure transducers flush-mounted in the airfoil. During the diffraction period, good agreement was obtained with linearized theory, even up to an angle of attack of 60 degrees. In the post-diffraction period the departures from linearized theory became very large after the leading-edge vortex approached the trailing edge. The transient stalling behavior is examined in detail.

Provenance

AFRL/VACA

Type

report

Format

vii, 51 pages : ill. ; 28 cm.

Subject

Airfoils

Shock Waves

Aerodynamic Configurations

Blast

Boundary Layer

Compressible Flow

Load Distribution

Measurement

Model Tests

Pressure

Shock Tubes

Subsonic Flow

Transonic Characteristics

Vortices

Publisher

Wright-Patterson Air Force Base, OH : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command,

Distribution Conflict

No