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┃ ┃ .1 ┃ ┃ ┃ ┃ I ┃
┃ ┣━━━━━━━━━━━━━┫ ┃ ┃ ┃ ┃
┃ ┃ ┃ ┃ ┃ Yo ┃ ┃
┣━━━━━╋━━━━┳━━━━━━━━╋━━━━━━━━┳━━━┫ ┃ ┃ ┃
┃ l ┃)- f : ┃ l ┃ ----. -- ┃I N ┃ ┃ ┃ ┃
┃ ┃ ┃h1=2-25m ┃ h2:1 5m' ┃ ┃ ┃TYi ┃ ┃
┃h:2- srh ┃-- ┃ J ┃\ ┃ ┃ ┃ ┃ ┃
┣━━━━━╋━━━━╋━━━━━━━━┻━━━━━━━━╋━┳━┻━━╋━━┻━━┫
┃ ┃ ┃ :-- :. --- 1zw =0-65m ┃P ┃---_/ ┃ ┃
┣━━━━━╋━━━━┻━━━━━━━━━━━━━━━━━╋━╋━━━━┫ ┃
┃ ┃- lt/l J ┃ ┃ ┃ ┃
┃ ┃ 'I ┃ ┃ ┃ ┃
┃ ┣━━━━━━━━━━━━━━━━━━━━━━┫ ┃ ┃ ┃
┃ ┃ 3Lt/4 ┃ ┃- 2 5m ┃ ┃
┗━━━━━┻━━━━━━━━━━━━━━━━━━━━━━┻━┻━━━━┻━━━━━┛
Fig.P3.20 Sketchofturplane.
317
-Om
5-Om
3.21 Using stnip theory, determine the yawing moment developed by a flying
wing having a rectangular planform and moving at a forward speed'of 75 m/s and
a sideslip of 5 m/s at sea level. The wing loading is 2000 N/m2, aspect ratio is 8,
taper ratio is 0.7, sectional lift-curve slope is O.lO/deg, sectional drag coefficient
CD.L = 0.015 + 0.0008a deg, dihedralis 5 deg, and wing span is 16 m. [Answer:
-1289 Nm.]
3.22 Plot the variation of (Cnp)A.W with angle of attack using the strip theory for
a swept-back wing with the following data: ALE = 30deg, aspect ratio- 8.0,
span-Y16.0 m, taper ratio-l.0, sectional drag coefficient CDO.L - 0.013 +
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL2(93)
