ESTIMATION OF SIDEFORCE AND YAWING MOMENT DERIVATIVES DUE TO SIDESLIP FOR COMPLETE AIRCRAFT AT SUBSONIC SPEEDS.

被引：0

作者：

Anon

机构：

来源：

Engineering Sciences Data Unit, Data Items | 1982年

关键词：

AIRCRAFT; -; Stability;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

ESDU 82011 illustrates the estimation of the sideforce and yawing moment derivatives due to sideslip for complete aircraft at subsonic speeds. It shows how to combine the ESDU methods for predicting the contribution of the separate parts of the aircraft. It covers cruise, landing and take-off configurations and is applicable where there is a linear variation of lift coefficient with angle of attack and of sideforce and yawing moment coefficient with angle of sideslip.

引用

共 13 条

[1] ESTIMATION OF SIDEFORCE, YAWING MOMENT AND ROLLING MOMENT DERIVATIVES DUE TO RATE OF ROLL FOR COMPLETE AIRCRAFT AT SUBSONIC SPEEDS.
Anon
Engineering Sciences Data Unit, Data Items, 1985,
[2] ESTIMATION OF ROLLING MOMENT DERIVATIVE DUE TO SIDESLIP FOR COMPLETE AIRCRAFT AT SUBSONIC SPEEDS.
Anon
Engineering Sciences Data Unit, Data Items, 1982,
[3] WING-BODY YAWING MOMENT AND SIDEFORCE DERIVATIVES DUE TO SIDESLIP: Nv AND Yv.
Anon
Engineering Sciences Data Unit, Data Items, 1981,
[4] CONTRIBUTION OF WING PLANFORM TO DERIVATIVES OF YAWING MOMENT AND SIDEFORCE DUE TO ROLL RATE AT SUBSONIC SPEEDS (Np)w AND (Yp)w.
Anon
Engineering Sciences Data Unit, Data Items, 1981,
[5] CONTRIBUTION OF BODY TO YAWING MOMENT AND SIDEFORCE DERIVATIVES DUE TO RATE OF YAW, (Nr)B AND (Yr)B.
Anon
Engineering Sciences Data Unit, Data Items, 1983,
[6] CONTRIBUTION OF FIN TO SIDEFORCE, YAWING MOMENT AND ROLLING MOMENT DERIVATIVES DUE TO RATE OF YAW, (Yr)F, (Nr)F, (Lr)F.
Anon
Engineering Sciences Data Unit, Data Items, 1982,
[7] ESTIMATION OF ATTAINABLE LEADING-EDGE THRUST FOR WINGS AT SUBSONIC AND SUPERSONIC SPEEDS.
Carlson, Harry W.
Mack, Robert J.
Barger, Raymond L.
NASA Technical Paper, 1979, (1500):
[8] ALLEVIATION OF THE SIDE FORCE AND THE YAWING MOMENT ACTING ON A SLENDER CONE-CYLINDER BODY AT HIGH ANGLES OF ATTACK, USING SMALL JET INJECTION AT SUBSONIC AND TRANSONIC SPEEDS.
Almosnino, D.
Rom, J.
TAE Report (Technion Israel Institute of Technology, Department of Aeronautical Engineering), 1979, (380):
[9] AERO-NORMALISED STABILITY DERIVATIVES: EFFECT OF WING ON YAWING MOMENT DUE TO YAWING.
Anon
Engineering Sciences Data Unit, Data Items, 1971,
[10] A novel technique to neutralize the Yawing moment due to asymmetric thrust in a hybrid buoyant aircraft
Haque, Anwar U.
Asrar, Waqer
Omar, Ashraf A.
Sulaeman, Erwin
Ali, Mohamed J. S.
EFM15 - EXPERIMENTAL FLUID MECHANICS 2015, 2016, 114

← 1 2 →