книги / Потенциальная теория неустановившихся сверхзвуковых течений
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36. |
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stream . J . Aero. Sci. |
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37. |
C h a n g C. |
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(1948). The |
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monically |
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flow. N. A. C. A. Tech. Note, № 2467; see Math. Rev. |
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(1952). |
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•40. C h e n g |
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R em ark son n on -Ii |
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41. |
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(1955). Observations of the flow around a two-dimensional |
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C O I e |
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Acceleration |
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44. C o l l a r |
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on |
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a thin aero foil with hinged flap at supersonic speeds. Rep. |
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45. |
C O p S O n |
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(1950). |
Diffraction |
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277— 84. |
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46. |
C O U r a n |
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(1948). |
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Super |
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sonic |
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a n t |
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Methoden |
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48. C U n n i n g h a m |
H. |
J . |
(1955). |
Tolal |
lift and |
pitching mo |
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m ent on thin arrowhead wings oscillating in supersonic potential |
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flow. N. A. C. A. Tech. N ote, |
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49. |
D o r r |
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(1949). Les forces aerodynamiques zur une aile vidrant |
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harmoniquement dans un ecoulement supersonique. 0 . N. E. R. A. |
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Rap. |
№ 3 7 . |
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50. |
D r a k e |
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G. |
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(1956). |
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51. |
in a compressible |
free jet. J . |
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aerofoil |
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D r a k e |
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two-dimensional |
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between |
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226— 39. |
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52. |
D г i s c h I e r |
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A. |
(1956). |
Calculation |
and compilation |
of |
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the unsteady lift functions for a rigid wing subjected |
to sinusoi |
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dal gusts and to sinusoidal sinking oscillations. |
N. |
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Tech. |
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53.E i c h e l b r e n n e r Е . А. (1954). Thcorie des corps elanccs.
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55.E i S I C у J . G. (1955). The Flutter of Simply Supported Rec tangular Plates in a Supersonic Flow. Pasadena: Cal, Inst. Technol., Guggenheim Aero. Lab.
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57.E v v a r d J . C. (1948). A linearized solution for time-depen dent velocity potentials near three-dimensional wings at super sonic speeds. N. A. C. A. Tech. Note, № 1699.
58.E v v a r d J . C. (1949). Use of source distribution for evalu ating theoretical aerodynamics of thin finite wings at super
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sonic speeds. N. A. |
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59. |
F |
l a x |
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A. |
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(1959). |
Relations |
between |
the |
characteristics |
of |
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a wing and its reverse |
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in |
supersonic |
flow. |
J . |
Aero. |
Sci. |
16, |
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496— 504, |
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60. |
F |
I a X |
A. |
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(1952a). |
The |
reverse flow theorem |
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for |
nonstationary |
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flows. |
J . Aero. Sci. 19, |
352— 3. |
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61. |
F l a x |
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A. |
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(1952b). General reverse flow and variational theo- |
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remx |
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361— 74. |
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62. |
F |
I a |
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A, |
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(1953). Reverse flow and veriational theorems for |
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lifting |
surfaces in nonstationary compressible flow. |
J , |
Aero. |
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Sci. |
20, |
120— 6. |
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63. |
F o x |
E. |
N. |
(1948). The |
diffraction |
of |
sound |
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pulses by an |
infi |
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nitely |
long strip. Phil. Trans. A 241, |
71 — 103. |
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64. |
F |
r a e n к e I |
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L. |
E. |
(1953), |
On the |
operational form |
of |
the |
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linearized |
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equation |
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of |
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supersonic |
flow. |
J . |
Aero. |
Sci. |
20, |
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6 4 7 - 8 . |
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65. F r a e n k e l |
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L. |
E. |
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(1955). On the unsteady |
motion |
of |
a slen |
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der |
body |
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through |
a |
compressible |
fluid. |
Aeronaut. |
Q uart. 6, |
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5 9 - 8 0 . |
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66. |
Ф P a H K Л ь |
Ф. |
(1946). |
Влияние ускорения |
точных тел |
вра |
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щения |
на |
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их сопротивление в газе. ПММ 10, стр. |
521— 524. |
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67. |
F |
г о е 1 i C h |
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J . |
Е. |
(1951). Nonstationary |
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motion |
of |
purely |
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supersonic wings. J . |
Aero. Sci. 18, |
298— 310. |
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68. |
F u n |
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Y . |
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C. |
(1955a), |
An |
Introduction to |
the Theory of Aeroe- |
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lasticity. New |
York: John |
W iley and Sons, |
Inc. (Имеется |
рус |
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ский |
перевод: Ф ы н |
Я. |
Ц ., |
Введение |
в теорию |
аэроупру- |
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гостп, Фнзматгиз, Москва, 1959. — Прим, персе.) |
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69. |
F |
U п g |
Y . |
С. |
(1955Ь). |
The |
Flutter |
of |
а |
Buckled |
Plate |
in a |
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Supersonic |
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Flow. |
Pasadena: |
Cal. |
Inst. |
Techn., Guggenheim |
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Aero, |
Lab. |
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70. |
G a l i n |
L. |
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(1947). A wing rectangular in plan in a supersonic |
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flow. |
Akad. |
Nauk |
SSSR , Prikl, Math. Mech. 11, 4 65 — 74. |
71.G a r d n e r C. S. (1950a). Time-dependent linearized super sonic flow past planar wings. Comm. Pure Appl. Math, 3,
72. |
G а г d n е г |
С, |
S. |
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(1950Ь). А relation between time-dependent |
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and steady linearized supersonic flows past conical bodies. |
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Comm. |
Pure |
Appl. Math, |
3, |
39— 43. |
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73. |
G |
a r d n e r |
C. S. and |
L u d l o f f |
H. F, |
(1949). Lift and drag of |
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rectangular |
wings |
of |
finite |
aspect |
ratio |
in |
accelerated, tran |
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sonic |
flight, |
J , |
Aero. Sci, |
16, |
635— G. |
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F. |
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74. |
G |
a r d n e г |
C. |
S. |
and |
L u d l o f f |
И, |
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(1950). Influence |
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of |
acceleration |
on |
aerodynamic characteristics of thin airfoils |
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in |
supersonic |
and |
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transonic |
flight. J . Aero. Sci. |
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17, 47 — 59, |
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75. |
G a r г i C к |
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I. E. (1957). |
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Nonsteady |
wing |
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characteristics. |
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Aerodynamics |
of |
A ircraft |
Components |
at |
High |
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Speeds, Sect. |
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F , |
Princeton University Press. |
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76. |
G a r г i C к |
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I. |
E . |
and |
R u b i n |
о w |
S. |
I. |
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(1946). |
Flutter |
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and oscillating airforce calculations for an airfoil in two-dimen |
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sional supersonic flow. N. A. C. A. Rep. № 846. |
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77. |
G a r г i C к |
I. |
E . |
and |
R |
u b i n о w |
S. |
I. |
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(1947).•Theoreti |
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cal |
study |
of |
air |
forces on an |
oscillating |
or steady |
thin |
win |
in |
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a supersonic |
main |
stream . N. A. C. A. Rep. № 872. |
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78. |
G e r m a i n |
P. |
(1949). La |
theorie |
dcs |
mouvements homogenes |
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et son application au calcul de certaines ailes delta en regime |
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supersonique. |
Rech. |
Aero. |
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3 — 16. |
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79. |
G e r m a i n |
P . |
and |
B a d e r |
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R. |
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(1949). Quclques remarques |
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sur Ies mouvements vibratoires d’une aile en |
regime supersoni |
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que. |
Rech. |
Aero. |
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11, 3— 13. |
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80. |
G O I d s t e i n |
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S. |
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and |
W |
a rd |
G. |
N. |
(1950). |
The linearized |
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theory |
of |
conical |
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fields in supersonic flow, with applications |
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to |
plane aerofoils. |
Aeronaut. Quart. 2, |
39 —84. |
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81. |
G O O d m a n |
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T. |
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R. |
(1951). |
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Aerodynamics |
of |
a supersonic |
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rectangular wing |
stri |
ing a sharp-edged |
gust. J . |
Aero. Sci. |
18, |
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519— 26. |
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82. |
G O O d m a n |
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T. |
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R. |
(1952). The |
quarter-infinite |
wing oscilla |
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ting at |
supersonic |
speeds. Q uart. |
Appl. Math. |
10, 189— 92. |
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•83. |
G u n n |
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J . |
C. |
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(1947). |
Linearized |
supersonic |
aerofoil |
theory. |
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Parts |
I |
and |
II. Phil. Trans, A, 240, |
327— 73. |
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84. |
H a d a m a r d |
J . |
(1923). Lectures on Cauchy’s Problem i |
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Linear |
Partial |
Differential |
Equations. |
New |
Haven: Yale |
U ni |
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versity |
Press |
(также |
New |
York: Dover Publications, 1952). |
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85. |
H a r m O n |
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S. |
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M. |
(1949). Theoretical relations between the |
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stab ility |
derivatives |
of |
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a |
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wing |
in |
direct |
and |
reverse |
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flow. N. A. C. A. Tech. Note, № 1943. |
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86. |
X |
a c K и H Д |
M. |
Д . |
и |
Ф a л ь к о п и ч С. |
В. |
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(1947). Коле |
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бания крыла конечного размаха в сверхзвуковом потоке. |
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ПММ |
11, |
стр. |
371— 376. |
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87. |
H |
а S S I g |
J . |
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(1954). Aerodynamic flutter coefficients for an |
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airfoil |
with |
leading-and trailing-edge flaps in two-dimensional |
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supersonic flow. J . Aero. |
Sci. |
21, |
131— 2, |
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88. |
H a у e s |
W . |
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D. |
(1947a), |
Linearized Supersonic Flow. Ph. D. |
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Thesis, |
California |
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Inst, of Technology, Pasadena; также Rep. |
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N. Amer. Aviation |
In c,, |
№ AL -222. |
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89. |
H |
a у e S |
W . |
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D. . (1947b). |
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On |
hypersonic sim ilitude. |
Quart. |
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Appl. |
Math. |
5, |
1 0 5 - 6 . |
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90. |
H a y e s W. D. |
(1948). Reversed flow |
theorems in supersonic |
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aerodynamics. Proc. V lIlh |
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Rep. N. Amer. Aviation |
Inc. № A L-755. |
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H a y e s |
W. |
D ., |
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о b e r |
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and H a a s e r N. (1952). |
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Generalized linearized conical flow. N. A. C. A. Tech. |
Note, |
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No 2667. |
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92. |
H e a s l e t |
M. |
A. |
and |
L о m a x H. |
(1949). Two-dimensional |
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unsteady lift problems in supersonic flight. |
N. A. C. A. Rep. |
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No 945. |
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93. |
H e a s I e t |
M. |
|
A. |
and |
L o m a x |
H. |
(1954a). |
Supersonic |
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and transonic small perturbation theory; see Sears (1954), Div. |
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D. стр. |
275— 314. |
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94. |
H e a s I c t |
M. |
A. |
and |
L о m a x H. |
(1954b). Further remarks |
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concerning integral transforms of the |
wave |
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Aero. |
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142. |
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95. |
H e a s I e t |
M. |
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and |
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R. (1953). |
Recip |
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|
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96. |
H e d g e P e t h J . M ., B u d i a n s k y |
B. |
and L e o n a r d |
R .W . |
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|
(1954). |
Analysis |
of flutter |
in compressible |
flow of |
a panel on |
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many supports. J . |
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97. |
von |
H e l m h o l t z |
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die physikalische |
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tung des Princips dcs Kleinsten Wirkung. Crelle (J. reine angew. |
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M ath.) |
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1 3 7 - 6 6 , |
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98.H i p s c h И. M. (1951). Harmonic Oscillations of a Narrow Delta Wing in Supersonic Flow. Ph. D. Thesis, Pasadena: C ali fornia Inst, of Technology.
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at supersonic |
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K. |
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TN , № |
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100.H O n I H. (1949). Two-dimensional wing theory in the super sonic range. Transl. in N. A. C. A. Tech. Memo. Ns 1238.
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Прим, перев.)
102. |
H u c k e l |
V. |
(1956). |
Tabulation |
of |
the |
functions which |
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|
occur in the aerodynamic theory of oscillating wings in super |
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|
sonic flow. N. A. C. A ., |
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103. |
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and D u r l i n g |
B . |
J . |
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104. |
H u n n |
B. |
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(1955). |
On the |
determ ination of the flutter |
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forces on wings with supersonic leading edges. Q uart. J . Mech. 8 , |
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293— 309; |
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также Math. Rev. |
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105.J o n e s R. T. (1946). Properties of low aspect ratio pointed wings at speeds below and above the speed of sound. N. A. C. A. Rep. № 835.
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107.J o n e s W . P. (1947). The influence of thichncss-cliord ratio on supersonic derivatives for oscillating aerofoils. Aero. Res. Coun., Lond. Rep. № 10, 871.
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Rep. |
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109. J o n e s |
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W . |
(1950). Aerodynamic |
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forces on biconvex |
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and calculation of forces for aerofoil with flap. Aero. Res. Coun., |
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Lond. |
Rep. № 13, 162 and 14, 217; Rep. Memor. Aero. Res. |
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Coun., |
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HO. von |
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K a r P |
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N .. S h U |
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W e i I |
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and |
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M. A. |
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(1947) |
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Aerodynamics |
of the oscillating airfoil in compressible |
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flow. |
U. |
S. Army Air |
Force |
Air |
Materiel |
Command Rep. |
№F -T R -1 167-ND.
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K a r p |
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N. . S h u |
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and B i o t |
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(1948) |
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of graphical and numerical data. U. S. Army Air Force Air |
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113. K o n d o |
Jiro (1954). The transient |
potential of an unsteady |
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supersonic |
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Proc. |
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Mcch, |
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283 — 7. |
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114. |
K P a C и Л ь Щ и K 0 D a |
E. |
A. |
(1947). |
Возмущенное движе |
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ние воздуха |
при |
вибрациях |
крыла, |
движущегося |
со |
сверх |
|||||||||||
|
звуковой |
скоростью. ПММ, П , стр. 147— 164, см. также ДАН |
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СССР 56, |
стр. 571-^574. |
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.115, К P а C и л ь щ H к о в а |
Е . |
|
А. |
(1950). К теории |
нестацио |
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нарного движения сжимаемой жидкости. ДАН |
СССР |
72, |
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стр. |
23 — 26. |
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116. |
К P а C и л ь щ и к о в а |
Е. |
А. |
(1954а). |
Неустановившееся |
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|
движение крыла бесконечного размаха. ДАН 94, |
стр. |
397, |
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|
см. также |
Изв. АН |
СССР, O TH , вып. 2, |
1954, стр. |
25— 41. |
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117. |
К р а с н л ь щ и к о в а |
Е. А. (19546). Неустановившееся |
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|
движение |
крыла |
бесконечного |
удлинения. |
Ученые записки |
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|
М ГУ |
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172, |
Мех. |
5. |
стр. |
6 1 - 7 8 . |
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118. |
K i i s s n e r |
Н. |
G. |
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(1940). |
AlIgem eineTragflachentheorie, |
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Luftfahrtforsch, |
17, |
3 7 0 - 8 . |
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119. |
L а g е г S t г о m |
Р. |
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А. |
(1947). Low aspect ratio rectangular |
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wings |
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in |
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Rep, |
Douglas |
A ircraft |
Co. № |
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L a m b |
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and |
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125. L а п C |
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128. |
L a n d a h l |
M. |
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ratio wings at |
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129.L a n d a h l M. (1956). Forces and Moments on O scillating Slender W ing-Body Combinations at Sonic Speed, M. I. T. Fluid
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Dynamics |
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130. |
L a n d a h l |
M. |
(1957). Unsteady flow |
around |
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131. |
L a n d a h I |
M ., |
A s h l e y |
H. |
and M o l l |
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S e n |
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(1955). On approxim ate solutions for |
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135. |
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and S c h w i n g e r |
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|
theory of diffraction by an aperture in an infinite plane screen. |
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Phys. Rev. 74, |
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1423— 32. |
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137. |
L i T . |
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a rectangular |
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138. |
L i |
T. |
(1956). Aerodynamic |
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23, |
613 — 22. |
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139. |
L i g h t h i l l |
M. |
J . |
(1945). |
Supersonic flow |
past |
bodies |
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|
of |
revolution. |
Rep. |
Memor. Aero. Res. Coun., Lond. № 2003. |
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140. |
L i g h t h i l l |
M. |
J . |
(1949). A |
technique for rendering |
appro |
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|
xim ate |
solutions to |
physical |
problems |
Uniformly |
valid. |
Phil. |
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|
Mag. |
(7), |
40, |
1179— 1201. |
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141. |
L i g h t h i l l |
M. |
J . (1951). A new approach to thin airfoil |
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theory. |
Aeronaut. |
Quart. 3, |
193— 210. |
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142.L i g h t h i l l M. J . (1953). Oscillating airfoils at high Mach number. J . Aero. Sci. 20, 402— 6.
143. |
L i n |
C. |
C ., |
R e i s s n e r |
E. |
and |
T s i e n |
H. S. |
(1948). |
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|
On two-dimensional non-steady |
motion |
of a |
slender |
body in |
||||||
|
a compressible fluid. J . Math. Phys. 27, |
220— 31. |
|
||||||||
144. |
L o m a x |
H. (1954). |
Lift |
developed |
on unrestrained |
rectan |
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|
gular |
wings |
entering |
gusts |
at subsonic |
and supersonic |
speeds. |
||||
|
N. A. |
C. A. |
Rep. № 1162. |
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145.* L o m a x |
|
H. , |
F u l l e r |
F. |
В. and |
S I u d e г |
L. |
(1955). |
||||||||
|
Generalized |
|
indicial forces |
on |
deforming |
rectangular |
wings |
|||||||||
|
in supersonic flight. N. A. C. A. Rep. № 1230. |
|
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||||||||||||
146. |
L o m a x |
|
H. , |
H e a s l e t |
M. , |
F u l l e r |
F. |
and |
S l u |
|||||||
|
d e r |
L. |
(1952). Twoand three-dimensional |
unsteady lift prob |
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|
lems in high-speed flight. N. A. C. A. Rep. № 1077. |
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|
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147. |
L o n g h o r n |
A. L. (1952). |
The |
unsteady, |
subsonic motion |
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|
of a sphere |
in |
a compressible |
inviscid |
fluid. |
Q uart. J . |
Mech. |
|||||||||
|
Appl. |
M ath. |
5 , |
64 — 81. |
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|
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148. |
L u k e |
Y . |
|
L . |
(1956). |
On |
the evaluation |
of generalized aero |
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|
dynam ic |
forces |
for |
triangular |
wings |
with |
supersonic leading |
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|
edges. |
W right Air |
Development Center R ep ., |
№ 56-525. |
|
|||||||||||
149. |
L U к e |
Y . |
L ., |
C o o m b s |
G. |
V. |
and W |
a g n e r |
F. |
(1957). |
||||||
|
Solution |
of |
the potential |
equation |
for |
the unsteady |
flow |
about |
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|
a triangular wing, |
etc. W rig h tA ir |
Development Centre |
R ep., |
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|
№ 57-258 |
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150. |
M a g n u s |
|
W. |
and O b e r h e t t i n g e r |
F . (1949). Form u |
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|
las Theorems for the Special Functions of |
M athem atical |
Phy |
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sics. |
New |
York; Chelsea |
Publ. |
Co. |
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151.M a n g i e r K. W. (1951a). Improper integrals in aerodyna mics. R. A. E. Rep. Aero, № 2424.
152.M a n g i e r K. W. (1951b). Calculation of the pressure dis
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№ 2439; Rep. Memor. Aero. Coun., Lond., № 2888.
153.M a n g i e r K. W. (1952). A method of calculating the shortperiod longitudinal stability derivatives of a wing in linearized unsteady compressible flow. Rep. Memor. Aero. Res. Coun., Lond., № 2924.
154.M a r t i n J . C. and G e r b e r N. (1954). The effect of thick ness on pitching airfoils at supersonic speeds. J . Math. Phys. 33, 46 — 56.
155. |
M a r t i n |
J. |
C. |
and G e r b e r N. |
(1955). |
The effect of |
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|
thickness on airfoils with constant vertical acceleration at super |
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|
sonic speeds. J . |
Aero. Sci. |
22, 179— 88. |
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156. |
M a z e l s k y |
B . |
(1956). |
Theoretical properties |
of vanishing |
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|
aspect ratio |
harm onically oscillating rigid |
airfoils |
in a compres |
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|
sible medium. J . |
Aero. Sci. 23, 639—52. |
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157.M c L a c h l a n N. (1951). Theory and Application of Mathieu Functions. Oxford: Clarendon Press.
158.M e i x n e r J . "W. (1949). Die Kantenbedingung in der Theorie der Beugung electromagnetischer Wellen an volkommen
Ieitenden |
ebenen Schirmen. Ann. |
Ph ys., |
Lpz. (6) |
6 , 2 — 9. |
|||
159. M e r b t |
H. |
and |
L a n d a h l |
M. |
(1953). |
Aerodynamic |
|
forces on oscillating low aspect |
ratio |
wings in |
compressible |
||||
flow. K . Tekn. Hogsk. H andl., Stockholm , Aero, |
TN , № 30 . |
||||||
160. M e r b t |
H. |
and |
L a n d a h l |
M. |
(1954). The oscillating |
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wing of low aspect ratio-results and tables of auxiliary func |
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tions. |
K. |
Tekn. |
Hogsk. H andl., |
Stockholm , Aero. T N , №3 1 . |
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M i g O f s |
к у |
E . |
(1955). Some |
considerations on two-dimen |
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sional thin airfoils deforming in |
supersonic flow. |
N. A. C. A. |
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Tech |
N ote, № 3386. |
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M i I e s |
J . |
W. |
(1947). The aerodynamic forces on |
an |
oscilla |
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ting airfoil |
at |
supersonic speeds. J . Aero. Sci. |
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351—8. |
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163. |
M i l e s |
J . |
W. |
(1948a). |
Acoustical methods |
in |
supersonic |
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aerodynamics. J . |
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164. |
M i l e s |
J . |
W. |
(1948b). Harmonic and transient |
motion of |
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a swept |
wing |
in |
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15, |
343— 7. |
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165. |
M i l e s |
J . |
M. |
(1948c). The aerodynamic forces on an oscillating |
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flap at |
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J . Aero. Sci. |
15, 565 —8; |
16, 442; |
17. 124.
166.M i l e s J . M. (1948d). Transient loading of airfoils at super sonic speeds. J . Aero. Sci. 15, 592— 8.
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J . |
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in supersonic |
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168. |
M i l e s |
J . |
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M i l e s |
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at supersonic |
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M i l e s |
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