Approximate Aerodynamic Influence Coefficients for Wings of Arbitrary Plan Form in Subsonic Flow
Abstract
Aerodynamic influence coefficients for symmetrically loaded wings of arbitrary plan form in subsonic flow are derived from a simple empirical method of estimating spanwise lift distributions. The application of the coefficients to an aeroelastic analysis is discussed. In the aeroelastic analysis of reference I the spanwise lift distribution was assumed to be given by strip theory with over-all reduction and rounding at the tip to take aerodynamic induction approximately into account. The spanwise lift distribution may be incorporated into the aeroelastic analysis more accurately by using suitable aero-dynamic influence coefficients. In this paper a method is presented for determining approximate aerodynamic influence coefficients for symmetric loadings from the method of estimating lift distributions presented in reference 2. An approximate means of taking the effect of the fuselage into account is also presented in the present paper; it is based on the assumption that the fuselage carries an amount of lift which depends solely on the angle of attack of the wing at its root.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1950
- Accession Number
- ADA380465
Entities
People
- Franklin W. Diederich
Organizations
- National Aeronautics and Space Administration