4.(15 pts) For the airfoil shown in Fig. 4, determine the lift and drag coefficients using (a) linear theory and (b)...
The measured lift slope for a new airfoil is 0.0975 degree-1, with al=0 =-1.15º. Consider a finite wing using this airfoil, with AR of 10 and taper ratio of 0.6. Calculate the lift and induced drag coefficients for this wing at a geometric angle of attack of 9º. Also, find the span efficiency factor. Hint: See Eq. (5.70) and Fig. 5.20. Are the values of lift and induced drag coefficients reasonable? do a = (5.70) 1 + (ao/A AR)(1 +...
Question 3-Concept Questions (10 points) a) What is the reason for having surface dimples (roughness) on a golf ball? Explain in 2-3 sentences. b) Draw the variation of lift and drag coefficients for a subsonic airfoil (at high Re number) over a Mach number range of 0.1-1.1. Explain the reason for trends Specify the primary drag mechanism for the following shapes in airstream at different Mach c) numbers. a. Symmetrical airfoil at an angle of attack of 4 degrees at...
For an aircraft shown in Fig. 1, assume that the wing span is b- 60 ft and wing airfoil is NACA-4415, of which, the a.c. locates at 0.245c. Determin the lift coefficient slope C, of the wing. (Assume M = 0.35) . Determine the a.c. position of the wing Determine ???.c-B. Also, determine the a.c. position of the wing-body (FORWARD OF WING) CE CENTROID NOTE: Xi SHOULD ALWAYS 8 COUNTED POSITIVE
use a Reynolds number of 2.6x10^5 to find using
graphs
2. Consider an NACA 23015 airfoil (Fig 5.2a and 5.2b in text) with a chord of 0.64 m in an airstream 1000m above sea level conditions. The freestream velocity is 70 m/s. The lift per unit span is 1200 N/m. Calculate the angle of attack and the drag per unit span. (See example 4.1) CHAPTER S incompressible Flow over Finite Wings Section lift coefficient - Moment coefficient, -20 -32 -24...
Question 2.10 A two-dimensional wedge-shaped airfoil, with chord, c, consists of straight-line segments with wedge angles, θ¡et and θaf, at the leading and trailing edges, as defined in the figure and given in the table below. The airfoil operates at an angle of attack, α, and it is moving through air at a supersonic speed, M. The atmospheric temperature and pressure far upstream of the airfoil are T and p as specified in the table The various flow regions are...
A wind tunnel test conducted on an airfoil section yielded the following data between the lift coefficient (CL) and the angle of attack (?): 12 1.40 16 1.71 20 1.38 de CL 0.11 0.55 0.95 You are required to develop a suitable polynomial relationship between ? and CL and fit a curve to the data points by the least-squares method using (a) hand calculations and (b) Matlab programming Hint: A quadratic equation (parabola) y(x)-aa,x +a x' can be used in...
Question 4 [15 MARKS] Using virtual work theory, determine the rotation at point A due to the load shown in Figure 4. E = 30 x 103 kN/mm2 and I = 200 x 104 mm. 20 KN 10 kNm A B 4 m 2 m K
The lift and drag graphs of the model airplane weights.7 lbf are shown in Fig 6.1 and 62 below Figure 6.1 Lift vs angle of attack of thae jet fighter mode Figure 6.2 Dig v angle of attack of the jet fighter model 1.2 08 500 0400 06 04 02 100 024610 12 14 16 18 20 22 24 0 24610 12 14 16 18 20 22 24 a C) 20MPH Determine: Figure 63 LD i angle of attack of...
Problem #9: For the mechanism shown in shown, determine the rotational speed of link 4 and the linear velocity of point C using complex numbers method. roAz=3.0 cm: roB= 1 cm 4.5 cm ro2O4= 5.0 cm; rBC 02 150°; an 18 rad/s CW (constant) 6 A2 on 2 As on 4 Bo 2.0 cm m 777
Problem #9: For the mechanism shown in shown, determine the rotational speed of link 4 and the linear velocity of point C using complex...
7.5 Determine the DFS coefficients of the peri- odic sequences shown in Fig. P7.5. Kap(n) 31 3 5-4-3-2-1 101 23 456 (Note: DFT and DFS coefficients have same values. Use any one period to find the DFT/DFS)