Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds Page: 4 of 115
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NACA TN 3421
A series of design charts presented herein permits rapid estimations
of the aerodynamic derivatives to be made for a given Mach number and a
given angle of attack.
The results for the wing of infinite aspect ratio are used to make
estimates of a number of the aerodynamic derivatives for rectangular wings
at finite angles of attack.
A aspect ratio
1,127(7 - 1)
Bo = ~o l - 1
B1l M2 - 1
B2 = /M2 - 1
b wing span
c1 velocity of sound behind shock
C2 velocity of sound in flow over upper surface of airfoil
cv specific heat at constant volume
G(x,y,z) = 0 equation of perturbed shock surface
g acceleration due to gravity
arbitrary functions of (x - Bjz) and (x + Bjz), respectively
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Martin, John C. & Malvestuto, Frank S., Jr. Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds, report, July 1955; (digital.library.unt.edu/ark:/67531/metadc57675/m1/4/: accessed October 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.