The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane as determined by tests of a model in the NACA free-flight tunnel

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086 0 ⊔ ‡aY 3.N 21/5:11/L-55
099 ⊔ ⊔ ‡aNACA L-55
100 1 ⊔ ‡aCampbell, John P.
245 1 4 ‡aThe effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane as determined by tests of a model in the NACA free-flight tunnel / ‡cby John P. Campbell and John W. Paulson.
246 1 3 ‡aNACA wartime reports
260 ⊔ ⊔ ‡aLangley Field, VA : ‡bLangley Memorial Aeronautical Laboratory, ‡c1944.
300 ⊔ ⊔ ‡a12, [7] p. : ‡bill. ; ‡c28 cm.
500 ⊔ ⊔ ‡a"NACA WARTIME REPORTS are reprints of papers originally issued to provide rapid distribution of advance research results to an authorized group requiring them for the war effort. They were previously held under a security status but are now unclassified. Some of these reports were not technically edited. All have been reproduced without change in order to expedite general distribution." ‡5FU
500 ⊔ ⊔ ‡a"Report date June 1944." ‡5FU
500 ⊔ ⊔ ‡a"Originally issued June 1944 as Advance Restricted Report L4F02." ‡5FU
500 ⊔ ⊔ ‡a"Report no. L-55." ‡5FU
504 ⊔ ⊔ ‡aIncludes bibliographic references (p. 10).
520 ⊔ ⊔ ‡aSummary: The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. A range of static margins from 2 to 16 percent of the mean aerodynamic chord was covered in the tests. For each test condition the model was flown and the longitudinal steadiness characteristics were noted. It was found in the investigation that longitudinal steadiness was affected to a much greater extent by changes in static margin than by changes in rotational damping. The best longitudinal steadiness was noted at large values of static margin. For all values of rotational damping, the steadiness of the model decreased as the static margin was reduced. The model was especially unsteady at low values of static margin (0.03 or less). Reduction in rotational damping had little effect on longitudinal steadiness, except that with low values of static margin (0.03 or less) the longitudinal divergences were sometimes more violent with the tailless (low rotational damping) condition.
530 ⊔ ⊔ ‡aAlso available in electronic format. ‡5FU
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 0 ‡aAerodynamics ‡xResearch.
650 ⊔ 0 ‡aStability of airplanes, Longitudinal.
650 ⊔ 0 ‡aDamping (Mechanics)
700 1 ⊔ ‡aPaulson, John W.
710 1 ⊔ ‡aUnited States. ‡bNational Advisory Committee for Aeronautics.
710 2 ⊔ ‡aLangley Aeronautical Laboratory.
830 ⊔ 0 ‡aNACA collection.
CID ⊔ ⊔ ‡a012183005
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DAT 1 ⊔ ‡a20171120114410.0 ‡b2017-11-20T19:57:19Z
DAT 2 ⊔ ‡a2014-05-22T20:00:04Z
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