A flight test engineer wants obtain aerodynamic data an aircraft at an ambient pressure of
Using Standard Atmosphere table given in Appendix A. determine at what altitude should
the aircraft be flown? What type of altitude this?
b. fthe temperature probe the aircraft measures ambient air temperature 28°C at the
flying altitude and assuming the ambient pressure is as desired what is the density altitude
2. (30 pts.)
rectangular wing with m span has NACA 2412 airfoil The wing being
tested in av tunnel at standard : level condition with wind speed angle
of attack of degrees. Assume that two-dimensional airflow can be achieved the wind
a. Calculate the Reynolds the flow (use mean acrodynamic chord the reference
length). Then determine from the NACA 2412 airfoil data given in
b. How much lift, drag. and pitching moment about its aerodynamic center the wing
Whatis angle of attack of the wing generate the lift 7000 N?
To what angle attack zero lift?
Express the lift coefficient angle attack equation in the form c-m-a+n.
their values for the NACA 2412 airfoil
Consider flying wing 206 10. span efficiency
factor and a NACA airfoil. The weight the flying wing 7.5x10 N. If the
aircraft altitude km speed ol 100 m/s. determine
a. the angle of for
c. the drag the aircraft experiences during the flight (use the highest Re the 4412 airfoil
data Appendix and assume CD,min drag polar).
d. the lift- to-drag ratio for the flight.
The Fairchild Republic A- 10 with the following characteristics in steady- level flight
Write the drag polar equation for the A-10 at this condition
Find the stall sealevel.
flying at 150m/s sealevel, what are the lift and drag experienced during
Assuming that all the lift necessary for the A-10 flight produced by the wing. and the
airfoil thin with zero-lift angle and span efficiency factor of 0.9.
determine the angle attack to achieve the flight condition given
Characteristics the International Standard Atmosphere, SI Units
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