Problem 1: Analyze the canard-wing combination shown in Fig. 1. The canard and wing are made of the same airfoil section and have AR AR, S = 0.25, and = 0.45% 1. Develop an expression for the moment coefficient about the center of gravity in terms of the shown parameters (, and zg) and the three-dimensional aerodynamic characteristics of the used wing/canard (CL C and CM). 2. What is the range of the cg location for this configuration to be statically stable? You may simplify the problem by neglecting the upwash (downwash) effects between the lifting surfaces and the drag contribution to the moment. You may also assume small angle approximation. Figure 1: Canard-Wing Configuration.

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2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Y Fx = Yu 0 0.0952 0.0922 0.0588 0 (Pu dYu dx - Calculate the drag and lift force on the airfoil by numerically evaluating the integrals Fy (P₁-P₂)dx = √ ( P₁ - 1 Pi Y₁ 0 -0.0254 -0.0144 -0.0052 0 dv) Y = Yu (x) dx y = Ye (x) Pu 1.000 -1.640 -0.786 -0.212 0 x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.

The drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 + 0.0405 C₁². It has a weight of 18,681 N. The wing area is 14.41 m². Calculate the minimum power required in watts. (Round off answer with no decimal places, No units, No commas) Answer given: 1461792 A 5,000 lbs. aircraft has an excess power of 75 hp at sea level. If the service ceiling is 3,657.6 m, determine the time to climb from sea level to absolute ceiling in minutes. (Round off answer with no decimal places. No units, No commas) Answer given: 17

4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil Eg. (4,57) C 2.0 - 1.e 1.2 Lift coefficient 0.8 0.4 -0.4 Eg. (4,64) -0.1 Moment coefficient -0.8 -0.2 -1.2 -0.3 Re - 3.1 X 10 O Re- 8.9 x 10 -0.4 16 a, degrees de; = ? da

Ign, McGraw-Hill, this chapter) and by New York, 1999, for more information. EXAMPLE 6.18 Estimate the landing ground roll distance at sea level for the CJ-1. No thrust reversal = 0. The spoilers increase the zero-lift, used; however, spoilers are employed such that L drag coefficient by 10 percent. The fuel tanks are essentially empty, so neglect the wejehr of any fuel carried by the airplane. The maximum lift coefficient, with flaps fully em ployed at touchdown, is 2.5.

Thank you!!   An aircraft weighing 65.2 kN when empty has a wing plan form area A of 62.3 m^2 . It cruises at a velocity of 900 km/h and a 4.0 degree angle of attack and altitude of 8500m. Also, the wing characteristics of the airfoil are shown. (a) Determine the allowable weigh of the cargo (b) and if the wingspan s is 20m determine the induce drag coefficient C_Di.

Derive a general expression to find circulation and the lift force for NACA 27014

a)What is the impact of increasing Reynolds number on skin friction and pressure drags over an airfoil? What can be happened for separation in this case? b) What is an adverse pressure gradient and where does it occur on an airfoil (show that on a sketch)? c) Why lift-to-drag ratio is an important parameter for an aircraft?  d)How can changing in altitude affect the aircraft power required, PR? Show thatmathematically and graphically?

6. For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is (where CL is the lift coefficient) (b) TAR CL 2TAR (d) TAR2 (a) TAR 7. Laminar flow airfoil is used to reduce the (a) pressure drag (b) induced drag (c) skin friction drag (d) wave drag 8. Set the aerofoil your chosen angle of incidence is gives a good installed pressure distribution. (a) twelve degree (b) ten degree (c) eight degree 9. The critical Mach number for a thick airfoil will be (a) lesser than a thin airfoil. (b) greater than a thin airfoil. (c) equal to a thin airfoil. (d) cannot be related to thin airfoil 10. What is the dimension for Lift coefficient? (a) N/s (b) kg/N (c) Dimensionless