A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios
A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios

Author: Richard T. Whitcomb

Publisher:

Published: 1960

Total Pages: 24

ISBN-13:

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Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.

Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles
Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles

Author: Eugene S. Love

Publisher:

Published: 1949

Total Pages: 104

ISBN-13:

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The results of tests of 11 triangular wings were conducted at Mach numbers 1.62, 1.92, and 2.40 to determine the effect of leading-edge shape and to compare actual test values with the nonviscous linear theory. The two series of wings had identical plan forms, a constant thickness ratio of 8 percent, a constant location of maximum-thickness point of 18 percent, and a range of apex half-angles from 10 to 45 degrees. The first series had an elliptical leading edge and the second series, a wedge leading edge. Measurements were made of lift, drag, pitching moment, and pressure distribution, the latter being confined to three wings at one Mach number.

Performance and Ranges of Application of Various Types of Aircraft-propulsion System
Performance and Ranges of Application of Various Types of Aircraft-propulsion System

Author:

Publisher:

Published: 1947

Total Pages: 536

ISBN-13:

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This group of papers on the comparison of the performance of six aircraft-propulsion systems was prepared by members of the NACA Flight Propulsion Research Laboratory staff under the direction of Mr. Benjamin Pinkel and was presented at the meeting of the Institute of Aeronautical Sciences on Aircraft Propulsion systems held in Cleveland, Ohio, on March 28, 1947.