author: henry a cole

Determination of Longitudinal Stability and Control Characteristics from Free-flight Model Tests with Results at Transonic Speeds for Three Airplane Configurations

Determination of Longitudinal Stability and Control Characteristics from Free-flight Model Tests with Results at Transonic Speeds for Three Airplane Configurations
Clarence L. GillsDavid AdamsonG. Chester FurlongHarold MirelsHenry A. ColeI. Irving PinkelJ. Howard ChildsRobert M. ReynoldsRobert T. JonesUnited States. National Advisory Committee for AeronauticsEdmund G. RosenbergJames G. McHughJesse L. MitchellRobert I. SammondsThaine W. ReynoldsW. E. BondWilliam B. BoatrightCharles C. GravesJohn H. WalkerM. A. Kissel
Aeronautics
... Wake thickness , chords .8 6 + N .24 .16 6 - percent - thick circular - arc wing of present tests-- .08 NACA 0018 section ( subsonic data of ref . I ) o 6 - percent - thick circular - arc wing ( supersonic data of present tests ) Values of ...
Experimental and Predicted Longitudinal and Lateral-directional Response Characteristics of a Large Flexible 35̊ Swept-wing Airplane at an Altitude of 35,000 Feet

Experimental and Predicted Longitudinal and Lateral-directional Response Characteristics of a Large Flexible 35̊ Swept-wing Airplane at an Altitude of 35,000 Feet
Clarence A. SyvertsonDavis H. CrawfordEdmund E. CallaghanFranklin K. MooreHenry A. ColeJames J. DoneganJohn E. YeatsJohn M. EgglestonWilliam J. AlfordUnited States. National Advisory Committee for AeronauticsCarl R. HussDavid H. DennisDonald S. WoolstonFranklin W. DiederichGeorge W. BrooksSimon OstrachStuart C. BrownWillard D. ColesWilliam D. McCauleyEuclid C. HollemanJohn C. Houbolt
Aerodynamic load
... 2 J 0.5 -6 O ( d ) Triangular span loading . FIGURE 7. - Concluded . The function given by equation ( 54 ) is plotted ... a ( a2 + 63a3 ) ( " * " K。( x ) dx − 1,120a1 + 32,256a2— 663,552 ] ( 56 ) 10 10 1.0 -B- @ 1.0 5 25 125 0625. 14 ...
Tests of an Asymmetrical Baffle for Fuel-sloshing Suppression

Tests of an Asymmetrical Baffle for Fuel-sloshing Suppression
Henry A. ColeBruno J. Gambucci
Fluid mechanics
... equation was used for determining damping ratio . Values of W and w were determined from the minimum and maximum ... equation ( 1 ) for the damping ratio determined from equa- tion ( 2 ) . As may be seen the measured frequency response ...

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