Consider a classically configured airplane with the following parameters: weight W= 120 kN wing area S= 50 m² area of horizontal tail S₂ = 12 m² airplane lift curve slope CL = 0.08 / degree tail lift curve slope CLta 0.06/ degree horizontal tail volume V = 0.9 In two subsequent flight tests in air of density p= 0.55 kg/m³, the airplane is trimmed for straight, level and unaccelerated flight at different velocities. The following velocites V and associated tail incidences are recorded: Voo (m/s) it (degrees) Test 1 120 2.5 Test 2 220 2.0 Use this data to calculate the static margin SM. Enter your answer as a decimal number (NOT in %) in the text box and upload your workings together with those of Question 1 as described in the instructions above.

Consider a classically configured airplane with the following parameters: weight W= 120 kN wing area S= 50 m² area of horizontal tail S₂ = 12 m² airplane lift curve slope CL = 0.08 / degree tail lift curve slope CLta 0.06/ degree horizontal tail volume V = 0.9 In two subsequent flight tests in air of density p= 0.55 kg/m³, the airplane is trimmed for straight, level and unaccelerated flight at different velocities. The following velocites V and associated tail incidences are recorded: Voo (m/s) it (degrees) Test 1 120 2.5 Test 2 220 2.0 Use this data to calculate the static margin SM. Enter your answer as a decimal number (NOT in %) in the text box and upload your workings together with those of Question 1 as described in the instructions above.

Structural Analysis

6th Edition

ISBN:9781337630931

Author:KASSIMALI, Aslam.

Publisher:KASSIMALI, Aslam.

Chapter2: Loads On Structures

Section: Chapter Questions

Problem 1P

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Question

Consider a classically configured airplane with the following parameters:
weight W = 120 kN
!!
wing area S = 50 m2
area of horizontal tail S = 12 m2
airplane lift curve slope C1a = 0.08 / degree
tail lift curve slope CLa = 0.06 / degree
horizontal tail volume V = 0.9
In two subsequent flight tests in air of density p = 0.55 kg/m³, the airplane is trimmed for straight,
level and unaccelerated flight at different velocities. The following velocites v and associated tail
incidences i, are recorded:
Test 1
Test 2
Vx (m/s)
120
220
ų (degrees)
2.5
2.0
Use this data to calculate the static margin SM.
Enter your answer as a decimal number (NOT in %) in the text box and upload your workings
together with those of Question 1 as described in the instructions above.

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