Accession Number:

AD0274576

Title:

STATIC AERODYNAMIC CHARACTERISTICS OF A TWO-STAGE AND A THREE-STAGE ROCKET VEHICLE AT MACH NUMBERS FROM 1.47 TO 4.63

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Report Date:

1962-04-01

Pagination or Media Count:

1.0

Abstract:

An investigation was conducted in the Langley Unitary Plan wind tunnel to determine the effects of fin cant and size on the static aerodynamic characteristics of a 0.081-scale model of a three-stage and a two-stage Trailblazer II configuration. Tests were performed at Mach numbers from 1.47 to 4.63 and at a Reynolds number per foot of 3.0 x 10 to the 6th power. he angleof-attack range varied from approximately -5 to 5 degrees and angle of sideslip varied from approximately -4 to 4 degrees. All first-stage fins tested gave adequate static stability when the center-of-gravity travel of the flight model was taken into account. The presence of the auxiliary rocket motors in the lateral plane decreased the effectiveness of the fins in the pitch plane at the lower Mach number and increased the fin effectiveness at the higher Mach numbers. Removal of the auxiliary rocket motors from the first stage of the two-stage configuration reduced the axial force about 25 at the low Mach numbers and about 15 at the high Mach numbers. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE