Wind-Tunnel Investigation of Effects of Unsymmetrical Horizontal-Tail Arrangements on Power-on Static Longitudinal Stability of a Single-Engine Airplane Model

Abstract

Verbatim from NASA NTRS. Not paraphrased, not summarized.

A wind-tunnel investigation has been made to determine the effects of unsymmetrical horizontal-tail arrangements on the power-on static longitudinal stability of a single-engine single-rotation airplane model. Although the tests and analyses showed that extreme asymmetry in the horizontal tail indicated a reduction in power effects on longitudinal stability for single-engine single-rotation airplanes, the particular "practical" arrangement tested did not show marked improvement. Differences in average downwash between the normal tail arrangement and various other tail arrangements estimated from computed values of propeller-slipstream rotation agreed with values estimated from pitching-moment test data for the flaps-up condition (low thrust and torque) and disagreed for the flaps-down condition (high thrust and torque). This disagreement indicated the necessity for continued research to determine the characteristics of the slip-stream behind various propeller-fuselage-wing combinations. Out-of-trim lateral forces and moments of the unsymmetrical tail arrangements that were best from consideration of longitudinal stability were no greater than those of the normal tail arrangement.

Authors

• Purser, Paul E. National Advisory Committee for Aeronautics. Langley Aeronautical Lab.
• Spear, Margaret F. National Advisory Committee for Aeronautics. Langley Aeronautical Lab.

Keywords

• AIRFOILS - NACA 65(216-012(MOD ) - CHAR & MOMENTS LOW-DRAG
• AIRFOILS - NACA 65(216)-015 4(MOD ) - CHAR & MOMENTS LOW-DRAG
• AIRPLANES, SINGLE-ENGINE
• PROPELLER SLIPSTREAM - EFFECT ON STABILITY
• TAIL SURFACES, HORIZONTAL
• AIRFOIL - NACA 66(215)-216 - CHAR & MOMENTS LOW-DRAG
• LOADS - TAIL SURFACES
• DOWNWASH
• AIRPLANES - TRIM