[airplane_geometry]wing_area = 163.

[airplane_geometry] <br>wing_area = 163.0 <br>wing_span = 33.0 <br>wing_root_chord = 8.3 <br>wing_dihedral = -1.0 <br>wing_incidence = 5.0 <br>wing_twist = 0 <br>oswald_efficiency_factor = 0.60 <br>wing_winglets_flag = 0 <br>wing_sweep = 30.0 <br>wing_pos_apex_lon = 4.0 <br>wing_pos_apex_vert = 3.0 <br>htail_area = 0 <br>htail_span = 0 <br>htail_pos_lon = 0 <br>htail_pos_vert = 0 <br>htail_incidence = 0 <br>htail_sweep = 0 <br>vtail_area = 6 <br>vtail_span = 2 <br>vtail_sweep = 0 <br>vtail_pos_lon = 3 <br>vtail_pos_vert = -1 <br>elevator_area = 0 <br>aileron_area = 0 <br>rudder_area = 0 <br>elevator_up_limit = 37.0<br>elevator_down_limit = 35.0 <br>aileron_up_limit = 20.0 <br>aileron_down_limit = 20.0 <br>rudder_limit = 0 <br>elevator_trim_limit = 20.0 <br>spoiler_limit = 0 <br>spoilerons_available = 0 <br>aileron_to_spoileron_gain = 0 <br>min_ailerons_for_spoilerons = 0 <br>min_flaps_for_spoilerons = 0 <br>auto_spoiler_available = 0 <br>spoiler_extension_time = 0 <br>positive_g_limit_flaps_up = 4.0 //设计克负荷耐受（正，襟翼收）<br>positive_g_limit_flaps_down = 4.0 //设计克负荷耐受（正，翼片向下）<br>negative_g_limit_flaps_up = -2.0 //设计克负荷耐受（负，襟翼收）<br>negative_g_limit_flaps_down = -2.0 //设计克负荷耐受（负的，翼片向下）<br>load_safety_factor = 1.5 //设计克负荷的安全系数

[飞机]几何学]<br>翼区 = 163.0<br>翼距 = 33.0<br>翼[根]弦 = 8.3<br>翼子板 = -1.0<br>翼发生率 = 5.0<br>翼转 = 0<br>奥斯瓦尔德[效率]因子= 0.60<br>翼子板_标志 = 0<br>翼扫 = 30.0<br>翼_pos_apex_lon = 4.0<br>翼pos_apex_顶点 = 3.0<br>htail_区域 = 0<br>htail_span = 0<br>htail_pos_lon = 0<br>htail_pos_vert = 0<br>htail_发生率 = 0<br>htail_扫描 = 0<br>vtail_区域 = 6<br>vtail_span = 2<br>vtail_扫描 = 0<br>vtail_pos_lon = 3<br>vtail_pos_vert = -1<br>电梯_区域 = 0<br>艾龙面积 = 0<br>舵= 区域 = 0<br>电梯_上升_限制 = 37.0<br>电梯_向下_限制 = 35.0<br>艾龙[上升]限制 = 20.0<br>艾龙=向下=极限= 20.0<br>舵= 极限 = 0<br>电梯_修剪_限制 = 20.0<br>扰流板 = 限值 = 0<br>扰流板_可用 = 0<br>艾勒龙_to_扰流龙_增益 = 0<br>min_ailerons_for_扰流龙] 0<br>最小_flaps_for_扰流子 = 0<br>自动_扰流板=可用 = 0<br>扰流板_扩展_时间 = 0<br>正_g_限位_flaps_up = 4.0 //设计 G 负载容差（正，活门向上）<br>正_g_限位_flaps_downs=4.0 //设计G负载公差（正，活门向下）<br>负_g_限位_flaps_up = -2.0 //设计 G 负载容差（负，活门向上）<br>负_g_限位_flaps_downs=-2.0 //设计G负载公差（负，活门向下）<br>负载_安全_系数 = 1.5 //设计 G 负载安全系数

[飞机几何]<br>机翼面积=163.0<br>翼展=33.0<br>翼根弦=8.3<br>翼二面体=-1.0<br>翼部发病率=5.0<br>机翼扭曲=0<br>奥斯瓦尔德效率系数=0.60<br>Wing_Winglets_标志=0<br>翼扫=30.0<br>翼尖=4.0<br>机翼顶点顶点=3.0<br>htail_面积=0<br>htail_跨度=0<br>htail_pos_lon=0<br>垂直高度=0<br>Htail_发生率=0<br>htail_扫描=0<br>垂直尾翼面积=6<br>垂直尾翼跨度=2<br>垂直尾翼扫掠=0<br>垂直尾翼位置=3<br>垂直尾翼位置=-1<br>电梯面积=0<br>副翼面积=0<br>舵面积=0<br>电梯上升限制=37.0<br>电梯向下极限=35.0<br>副翼上升极限=20.0<br>副翼向下极限=20.0<br>舵极限=0<br>升降舵配平极限=20.0<br>扰流器极限=0<br>扰流板可用=0<br>副翼至扰流板增益=0<br>扰流板的最小副翼=0<br>扰流板的最小襟翼=0<br>提供自动扰流板=0<br>扰流板延长时间=0<br>正G_极限G_襟翼向上=4.0/设计G载荷公差（正，襟翼向上）<br>正G_极限G_襟翼向下=4.0/设计G载荷公差（正，襟翼向下）<br>负G_极限G_襟翼向上=-2.0/设计G载荷公差（负，襟翼向上）<br>负G_极限G_襟翼向下=-2.0/设计G载荷公差（负，襟翼向下）<br>荷载安全系数=1.5//设计荷载安全系数<br>