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1. Layout design requirements:

   1. Roll control requirements, critical flight phase for roll control, research standards i.e. time required for aircraft to roll from initial bank angle to a specific angle

   2. Select inboard and outboard positions of the aileron. Determine b_ai/b, b_ao/b, and C_a/C.

   3. Determine aileron effectiveness parameter tau_a.

   4. Determine I_xx (moment of inertia about the roll axis, estimate since not everything is finalized)

2. Performing calculations:

   1. Calculate aileron rolling moment coefficient derivative (C_l-delta-A). Use the following equation:

      

      1. C_r = root chord. yo = outboard distance from fuselage, yi = inboard distance from fuselage, S = wing planform area, b = wing span

      2. C_L_alpha_w = wing sectional lift curve slope - assumed to be in the constant region, therefore, the aileron sectional lift curve slope is also the same…

      3. Calculate tau using the graph above. Tau(Ca/C)

   2. Select maximum aileron deflection (delta_Amax). Typ +/- 25 degrees.

   3. Calculate rolling moment coefficient (C_l) when aileron is deflected with max. deflection using

      

   4. Calculate aircraft rolling moment (L_A) for maximum aileron deflection using

      

   5. Determine steady-state roll rate (P_ss) using

      

   6. Calculate the bank angle at which aircraft achieves steady state roll rate.

      

   7. Calculate the rate of change of roll rate (before steady state is reached)

      

   8. If phi_1 > phi_req (aka the total desired bank angle) determine time to reach phi_req using the formula

      

      1. If phi_1 < phi_req, use the eqns below to solve t2

         

   9. Compare t_2 with t_req. Minimum difference must not exceed 10%. If this isn’t the case, choose different aileron params and repeat the calculations.

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Workflow diagram

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