200
STRESS ANALYSIS
Distortions of strippea aeroplane wings under torsional loading, by D. Williama, London, H.M. Stat. off., 1932. 3 p. diagrs.
(A.R.C. R. & M. no. 1507)
Etudes experimentales sur la cooperation des longerons dans les
ailes en porte & faux, par 2. Łuczyński. Warszawa, Sprawozdani Instytut Badań technicznych lotnictwa, buletyn no. 8, 1932, no. 40, p. 83-129. diagrs., illus., tables.
Flexion et rosion des ailes cantilever, par Leon Kirste. Paris, Travaux du cercie d*etudes aeronautiąues de lfAero-club de iTance, 1932. 14 p. illus.
A iMethod for computing leading-edge loads, by Richard V. Rhode and Henry A. Pearson. Washington, U.S. Govt. print. off., 1932.
12 p. diagrs., illus., tables. (N.A.C.A. Report no. 413)
Stresses produced in aeroplane wings by gusts, by Hans Georg
JUssner. V/ashington, 1932. 38 p, diagrs., illus., tables.
(N.A.C.A. Technical memorandums no. 654) (From Z.F.M.,
Mlinchen und Berlin, Oct. 14-21, 1931)
Torsional rigidity in cantilever wings, by C. G. Brown. Aviation, engineering, New York, Dec. 1931, v. 5, no. 5, p. 11-14. diagrs.
Le Ali dei velivoli e le loro strutture, dl Carlo Minelli. LłAero-tecnica, Roma, Sep. 1931, v. 11, no. 9, p. 1091-1118. diagr. illus.
LfInteruction des longerons dans les ailes cantilever, par Edmond Abit, LfAeronautiąue, Paris, May 1931, no. 144, p. 172-76. diagrs.
Stress.es in wing structures, by S. Scott-Hall. London, H.M. Stat. off., 1931. 6 p. diagrs., illus. (A.R.C. R. & M.
no. 1309)
Torsion in box wings, by J.B. Wheatley. Washington, 1931. 44 p.
diagrs. (N.A.C.A. Technical notes no. 366;
Analysis of the wing and other indeterminate structures, by J. Fradiss and A. Thieblot. Aviation, New York, June 15,
July 20, Sep. 21, 1929, v. 26-27, p. 36-90, 195-202, 644-45. diagrs.
Belastning av flygplan, av B. Carlsson. Teknisk tidskrift,
Stockholm, July 15, 1929, v. 59, no. 28, p. 369-74. illus.
Cantilever wings. An investigation of torsional strength and
stiffness, by F. Duncanson. Flight, London, Mar., June 27, 1929, v. 21, no. 21, 26, p. 258a-258b; 522a-522c.