Investigation at High Speeds of a Horizontal-Tail Model in the Langley 8-Foot High-Speed Tunnel
Abstract
Pressure-distribution measurements and elevator hinge-moment measurements were made to determine the aerodynamic characteristics of a horizontal-tail model having an NACA 65-108 airfoil section equipped with a 30-percent-chord sealed unbalanced elevator and a 10 percent-chord plain trim tab. The tests were made for various angles of attack and control-surface deflections at Mach numbers ranging from 0.40 to 0.90. Data are presented for tests made with the surfaces of the model smooth and also with the boundary-layer transition fixed at the 0.10-chord station by a row of carborundum grains on each surface. The results of the investigation indicated that for small elevator deflections and for Mach numbers up to 0.85 no adverse changes in the lift-curve slopes, control-surface effectiveness, and hinge-moment parameters occurred. At Mach numbers in the range from 0.85 to 0.90 the values of the lift-curve slopes showed an abrupt decrease, the elevator effectiveness decreased rapidly, and the negative value of rate of change of elevator hinge-moment coefficient with elevator deflection C sub h sub delta increased abruptly. The tab effectiveness, however, remained almost constant throughout the Mach number range. Fixing transition at the 10-percent-chord station on both surfaces reduced the values of the lift-curve slopes and the elevator effectiveness. The value of the hinge-moment parameter C sub h sub delta was also reduced throughout the Mach number range.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 31, 1947
- Accession Number
- ADA801167
Entities
People
- Ralph P. Bielat
Organizations
- Langley Research Center