Accession Number:

AD0619157

Title:

WIND TUNNEL TESTS OF A FULL-SCALE ROTOR AT HIGH SPEEDS

Descriptive Note:

Final rept.

Corporate Author:

BELL HELICOPTER TEXTRON INC FORT WORTH TX

Personal Author(s):

Report Date:

1965-07-01

Pagination or Media Count:

73.0

Abstract:

This report summarizes the results of a wind tunnel program conducted to define the effects of compressibility and advance ratio on the performance of a 46-foot diameter, three-bladed rotor. Measured rotor profile power increase with lift coefficient and advance ratio were greater than predicted. Airfoil characteristics were synthesized that improve correlation of Mach number and lift effects on profile power. Preliminary radial flow considerations are presented and discussed. Additional analytical and experimental work is recommended to investigate in more detail the effects of advance ratio on profile power.

Subject Categories:

  • Helicopters

Distribution Statement:

APPROVED FOR PUBLIC RELEASE