CL0 Lift coefficient at zero 零攻角升力系数
angle of attack (AOA) 攻角
CLa Lift coefficient due to AOA 一定攻角下的升力系数
CD0 Zero-lift drag coefficient 零升力阻尼系数
CDL Drag coefficient due to lift 一定升力下的阻力系数
(induced drag effect)衰减阻尼效应
Cmq Pitching moment due to pitch rate 一定俯仰速率下的俯仰力矩
(pitch damping)（纵摇阻尼）
Cmad Pitching moment due to AOA rate 一定攻角速率下的俯仰力矩
(aero interaction between wings and horiz tail)（主翼和尾翼的区域配合）
Cyb Side force due to sideslip 侧滑决定的侧力
Cyp Side force due to roll rate 滚转速率决定的侧力
Cyr Side force due to yaw rate 偏航速率决定的侧力
Clb Roll moment due to sideslip 侧滑导致的滚转力矩
Clp Roll moment due to roll rate 滚转速率导致滚转力矩
(roll damping)（滚转阻尼）
Clr Roll moment due to yaw rate 偏航率导致的滚转力矩
Cnb Yaw moment due to sideslip 侧滑导致的偏航力矩
Cnp Yaw moment due to roll rate 滚转速率导致的偏航力矩
Cnr Yaw moment due to yaw rate 偏航速率导致的偏航力矩
(yaw damping)（偏航阻尼）
CLiftdc Lift due to control surface deflection 操纵面转向（偏斜）导致的升力
CDdc Drag due to control surface deflection 操纵面转向（偏斜）导致的阻尼
Cydc Side force due to control surface deflection 操纵面转向（偏斜）导致的侧力
Cldc Roll moment due to control surface deflection 操纵面转向（偏斜）导致的滚转力矩
Cmdc Pitch moment due to control surface deflection 操纵面转向（偏斜）导致的俯仰力矩
Cndc Yaw moment due to control surface deflection 操纵面转向（偏斜）导致的偏航力矩
DeltaStallAlpha Increase in max angle-of-attack before stall 失速前最大攻角增加值
Xac X-location of aerodynamic center 空气动力学中心的X位置
Ymac=Mean Area Chord at "Y" axis Y轴上的平均翼弦
Cla = Lift coefficient as a function of AOA 升力系数为系数的攻角函数
CD0 = Zero-lift drag coefficient 零升力阻尼系数
CDL = Total drag coefficient 总阻尼系数
Cmq = Pitch moment coefficient per radian 每弧度力矩系数
Cmad = Pitch moment coefficient per radian AOA ? 每弧度攻角力矩系数
Cyb = Side force coefficent per degree of sideslip 每度侧滑侧力系数
Clb = Roll moment coefficient per degree of sideslip 每度侧滑滚转力矩系数
Clp = Roll moment coefficient per roll rate (radians) 每弧度滚转滚转力矩系数
Clr = Roll moment coefficient per yaw rate (radians) 每弧度俯仰系数滚转力矩系数
Cnb = Yaw moment coefficeint per degee of sideslip 每度侧滑俯仰力矩系数
Cnp = Yaw moment coefficient per roll rate (radians) 每弧度偏航率俯仰力矩系数
Cnr = Yaw moment coefficient per yaw rate (radians) 每弧度俯仰率俯仰力矩系数
CLaMachTable = Lift coefficient factor (of Cla) vs Mach number 每马赫数对应的升力系数因子
CD0MachTable = Zero-lift drag coefficient factor (of CD0) vs Mach number 每马赫数对应的零升力阻力因子
CDLAlphaTable = Total drag coefficient vs AOA 攻角对应的总阻尼系数
CmqMachTable = Pitch moment coefficient vs Mach number 每马赫数对应的俯仰力矩因子
ClbAlphaTable = Clb as a function of AOA 侧滑导致的滚转为系数的攻角函数
ClpAlphaTable = Clp as a function of AOA 每弧度滚转滚转力矩系数为系数的攻角函数
ClrAlphaTable = Clr as a function of AOA 每弧度俯仰系数滚转力矩系数为系数的攻角函数
CnpAlphaTable = Cnp as a function of AOA 滚转速率导致的偏航力矩为系数的攻角函数
CnrAlphaTable = Cnr as a function of AOA 偏航速率导致的偏航力矩为系数的攻角函数
XacMachTable = Center-of-pressure distance from wing's neutral point (?) (AOA independent) vs AOA
攻角对应的 机翼中和点到压力中心的距离
CLmax = Maximum lift coefficient 最大升力系数
AlphaStall = Angle-of-attack where stall begins 失速开始时的攻角
AlphaMax = Maximum angle-of-attack while retaining full control? 在机体全面可控下的最大攻角
AlphaDepart = Angle-of-attack where wing departs 机翼分离的最大攻角
Ymac = Lift moment arm about aircraft's longitudinal axis 升力力矩对航空器的纵轴的力臂
发表于 2011-8-30 14:06:37
发表于 2011-9-3 15:34:41
