The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft, TED No. NACA DE332 Page: 7 of 20
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CONFIDENTIAL
NACA RM SL5OC16a
*o 3. A corresponding change in nose shape for the winged models
decreased the drag coefficient by about 0.05 in the Mach number range
* from 1.1 to 1.4. At Mach numbers greater than 1.6, no measurable
e.o reduction in drag coefficient was obtained.
4. The present fuselage has less drag than a parabolic fuselage
which could contain the same equipment.Langley Aeronautical Laboratory
National Advisory Committee for Aeronautics
Langley Air Force Base, Va.James R. Hall
Aeronautical Research Scientist
Carl A. Sandahl
Aeronautical Aerodynamics ScientistApproved:
Robert R. Gilruth
Chief of Pilotless Aircraft Research DivisionDLMcC
REFERENCE
1. Laitone, E. V.: The Linearized Subsonic and Supersonic Flow about
Inclined Slender Bodies of Revolution. Jour. Aero. Sci., vol. 14,
no. 11, Nov. 1947, pp. 631-642.CONFIDENTIAL
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Hall, James R. & Sandahl, Carl A. The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft, TED No. NACA DE332, report, March 16, 1950; (https://digital.library.unt.edu/ark:/67531/metadc65533/m1/7/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.