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25. Vertical tail airfoil 26. Overall Vertical Stabilizer Geometry 27. Overall Aircraft Static Direction Stability 28. Rudder (TBD in Control Surfaces Design)
1. l/Lf Ratio: 0.6 The table below shows statistical ratios between the distance between the wing aerodynamic center and the horizontal tail aerodynamic center ๐๐๐ with respect to the overall fuselage length (Lf).
2. Fuselage Length (Lf): 60.00 in Choosing this value is an iterative process to meet longitudinal and vertical static stability, internal storage, and center of gravity requirements, but preliminarily choose ๐๐ = 60.00 ๐๐
๐๐๐ = 36.00 ๐๐ 4. Horizontal Tail Volume Coefficient (VH): 1.0 The table below shows the horizontal and vertical tail coefficients for various types of aircraft.
๐๐ป =๐๐ก๐๐ก๐๐
๐๐ป = 1
5. Center of Gravity Location (xcg):๐.๐๐๐ Justification:
a) Choose center of gravity aft of aerodynamic center to aid (give more room) with placing components to meet specified center of gravity location.
b) If horizontal tail stabilizes aircraft pitching up, it generates a positive lift force, adding to the wing lift.
c) 0.30๐ is the aft most recommended limit for center of gravity placement. 6. Horizontal Tail Arm ๐๐ : 35.2537 in
a) It is recommended that the aspect ratio of the tail be such that the span is longer than the propeller diameter to ensure that a portion of the tail is out of the wake or downwash of the wing, increasing tail efficiency ๐ .
b) Horizontal tail aspect ratio should be lower than that of the wing to increase stall angle and allow for recovery if needed
c) It is recommended that:
๐ด๐ ๐ก =2
3๐ด๐ ๐ค
๐ด๐ ๐ก = 4
10. Horizontal Tail Taper Ratio ๐๐ : 0.7
a) For transport aircraft, the horizontal tail taper ratio is usually between 0.4 and 0.7 b) To ensure a higher stall angle than the wing through a lower Oswald efficiency factor and a lift
distribution that is less elliptical, choose ๐๐ก = 0.7
a) For the benefits of applying the any of the above parameters to the horizontal geometry, refer to the preliminary wing design parameter selection document
b) In the preliminary design phase, it is recommended to make these parameters have the same values as those of the wing.
18. Vertical tail volume coefficient ๐ฝ๐ : 0.06 The following table shows the vertical tail characteristics for various aircraft. Because our aircraft configuration and mission requirements are very similar to the C-130, many vertical tail parameters are chosen so that they match those of that aircraft.
๐๐ฃ =๐๐ฃ๐๐ฃ๐๐
๐๐ฃ = 0.06 19. Vertical tail arm ๐๐ : 36.1102 in During the preliminary design phase, the vertical tail arm is selected to be equal to the horizontal tail arm, then adjusted after further iterations if needed. ๐๐ฃ = 36.1102 ๐๐
20. Vertical tail planform area ๐บ๐ฝ : 1.1521 ๐๐ก2
๐๐ฃ =๐๐ฃ๐๐ฃ๐๐
= 0.08
๐๐ฃ = 1.1521 ๐๐ก2
21. Vertical tail aspect ratio ๐จ๐น๐ : 1.84 Choose vertical tail aspect ratio such that it matches that of the C-130 (Table 6.6). ๐จ๐น๐ = ๐.๐๐ 22. Vertical tail span ๐๐ : 17.4716 in
๐ด๐ ๐ฃ =๐๐ฃ
2
๐๐ฃ
๐๐ฃ = 17.4716 ๐๐ 23. Vertical tail sweep angle ๐ฒ๐ : 18.8 deg Choose vertical tail sweep angle such that it matches that of the C-130 (Table 6.6). ฮ๐ฃ = 18.8 ๐๐๐