Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage: lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3 Page: 1 of 28
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NFIDENT IA ML55L295
- A _
RESULTS OF ROCKET MODEL TEST OF AN AIRPLANE CONFIGURATION
HAVING AN ARROW WING AND SLENDER FLAT-WEDED FUSELAGE
LIFT, DRAG, LONGITUDINAL STABILITY, LATERAL FORCE, AND
JET EFFECTS AT MACH NUMBERS BETWEEN 1.0 AND 2.3
By Robert F. Peck
L.By autI- --1
SCCL ASSIFIED DOCUMENT
This material contaIs irforiat!cn affecting the National Defense of the United States witn th meanir.g
of the ea cage laws, Tite 18, U.S.C., Sees. 793 and 79, the trar.sw ss aor revelatioaof which n any
manner to an unauthorized person is p-cih:ted by law.
NATIONAL ADVISORY COMMITTEE
i February 21, 1956
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Peck, Robert F. Results of rocket model test of an airplane configuration having an arrow wing and slender flat-sided fuselage: lift, drag, longitudinal stability, lateral force, and jet effects at Mach numbers between 1.0 and 2.3, report, February 21, 1956; (digital.library.unt.edu/ark:/67531/metadc62413/m1/1/: accessed June 23, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.