Accession Number:

AD0445924

Title:

AERODYNAMIC INFLUENCE COEFFICIENTS FROM PISTON THEORY: ANALYTICAL DEVELOPMENT AND COMPUTATIONAL PROCEDURE

Descriptive Note:

Corporate Author:

AEROSPACE CORP EL SEGUNDO CA

Report Date:

1962-08-15

Pagination or Media Count:

99.0

Abstract:

A method is presented for calculating the aerodynamic influence coefficients AICs based on third-order piston theory with an optional correction to agree with Van Dykes quasi-steady second-order theory. The AICs are computed assuming the airfoil to have a rigid chord with or without a rigid chord control surface. The influence coefficients relate the surface deflections to the aerodynamic forces through. The piston theory is limited to high Mach number or high reduced frequency, but Van Dykes quasi-steady correction extends the validity to some lower supersonic Mach number at low reduced frequency. The Aerospace IBM 7090 Computer Program Number HM11 provides the AICs from this theory in both a printed and an optional punchedcard output format. The program capacity is 25 surface strips, 15 Mach numbers, and 20 reduced velocities for each Mach number.

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE