Calculation of Lift and Pitching Moments Due to Angle of Attack and Steady Pitching Velocity at Supersonic Speeds for Thin Sweptback Tapered Wings With Streamwise Tips and Supersonic Leading and Training Edges
Abstract
On the basis of linearized supersonic flow theory the stability derivatives C sub m sub a and C sub m sub q (moment coefficients due to angle of attack and steady pitching velocity, respectively) and C sub L sub q (lift coefficient due to steady pitching velocity) were derived for a series of thin sweptback tapered wings with streamwise tips and supersonic leading and trailing edges. The results are valid for a range of Mach number for which the Mach lines from the leading edge of the center section cut the trailing.edges. An additional limitation is that the foremost Mach line from either tip may not intersect the remote half of the wing. The results of the analysis are presented as a series of design charts. Some illustrative variations of the derivatives and of the chordwise" center-of-pressure location with the various wing design parameters are also included. To facilitate the transformation of the calculated results to arbitrary moment-reference locations, the required data for C sub L sub a have been selected or computed from the charts and equations in NACA TN 2ll4 and are also presented in the form of design charts.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1952
- Accession Number
- ADA380612
Entities
People
- Isabella Jeffreys
- John C. Martin
- Kenneth Margolis
Organizations
- National Aeronautics and Space Administration