Simplified procedures for estimating flap-control loads at supersonic speeds Page: 3 of 15
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2 FIFT NACA RM L55E12
P -P
P pressure coefficient,
Q dynamic pressure
M free-stream Mach number
y spanwise distance
a angle of attack, deg
8 control deflection, deg
Ado, increment in section normal force on control
ACnw increment in section normal force on wing plus control
ACdm increment in section pitching moment due to load on control
Acmw increment in section pitching moment due to load on wing
plus control
K constant
Subscripts
I local
1 ahead of control hinge line
2 behind control hinge line
av average
cr critical
TRAILING-EIGE CONTROLS
Basic Flow Types
In figures 1 and 2 are depicted two basic types of flow over a
flap-type control. Figure 1 shows a flow that adheres closely to the
airfoil surface. This type of flow occurs only at relatively low angleslrc-~ .113 __rc
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Czarnecki, K. R. & Lord, Douglas R. Simplified procedures for estimating flap-control loads at supersonic speeds, report, May 27, 1955; (https://digital.library.unt.edu/ark:/67531/metadc61520/m1/3/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.