1. Team 5 Aerodynamics QDR #1
Scott Bird
Mike Downes
Kelby Haase
Grant Hile
Cyrus Sigari
Sarah Umberger
Jen Watson
October 9, 2003
QDR

2. Preview Airfoil Sections and Geometry 3-view of aircraft
Aerodynamic mathematical model
October 9, 2003
QDR

3. Aerodynamic Known Values
Recruise =
At 1000 ft, Vcruise = 55 ft/s
Restall =
At Sea Level, Vstall = 30 ft/s
S = 28 ft2
b = 14 ft
c = 2 ft
October 9, 2003
QDR

4. Airfoil Sections Wing Horizontal tail Vertical tail S1223 Airfoil
High lift, Low Reynolds number
Used extensively in RC aircraft
Horizontal tail
NACA 0012
Symmetrical
5 degrees Sweep
To prevent tail stalling before wing
Taper Ratio = .803
Vertical tail
symmetrical
10 degrees Sweep
Tail sweep > 20 degrees not practical for slow flight
Taper Ratio = .73
October 9, 2003
QDR

5. Aircraft 3-view
October 9, 2003
QDR

6. Aerodynamic Mathematical Model
CL = * α
CLmax = 2.13
CD = * ( * α)2
Swet = 119 ft2
AR = 7
October 9, 2003
QDR

7. Questions?
Questions??
October 9, 2003
QDR

8. Aerodynamic Mathematical Model
CL= CLo + CLα * α
CLα = Clα / ( * Clα / (pi * AR * e))
CLo = -CLα * α when CL = 0
CD=CDo + k * CL * CL
CDo = f / S
f was interpolated using Figure 5.39 (Raymer)
k = 1 / (pi * AR * e)
e = 2 / (2 – AR + √ (4 + AR^2 * cosΛLE))
e = .877
Swet = Σ Swet_surfaces
October 9, 2003
QDR

9. Airfoil Section
October 9, 2003
QDR

10. Airfoil Section Data CL
Alpha
October 9, 2003
QDR

11. Airfoil Section Data CD CD CL CL
October 9, 2003
QDR