PREDICTION OF LIFT AND MOMENT ON A SLENDER CYLINDER-SEGMENT WING-BODY COMBINATION

被引：0

作者：

CROWELL, KR ^{[1
]}

CROWE, CT ^{[1
]}

机构：

[1] WASHINGTON STATE UNIV,DEPT MECH ENGN,PULLMAN,WA 99163

来源：

AERONAUTICAL JOURNAL | 1973年 / 77卷 / 750期

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

引用

页码：295 / 298

页数：4

共 44 条

[1] LIFT AND ROLLING MOMENT ON A SLENDER WING-BODY COMBINATION WITH A DEFLECTED TIP CONTROL
CLARKE, JF
JOURNAL OF THE AERONAUTICAL SCIENCES, 1958, 25 (03): : 203 - 205
[2] LIFT OF WING-BODY COMBINATION
YANG, HT
AIAA JOURNAL, 1972, 10 (11) : 1535 - &
[3] LIFT ON WING-BODY COMBINATION - REPLY
YANG, HT
AIAA JOURNAL, 1973, 11 (06) : 896 - 896
[4] ON SLENDER WING-BODY THEORY
SPREITER, JR
JOURNAL OF THE AERONAUTICAL SCIENCES, 1952, 19 (08): : 571 - 572
[5] ON SLENDER WING-BODY THEORY
MILES, JW
JOURNAL OF THE AERONAUTICAL SCIENCES, 1952, 19 (02): : 140 - 140
[6] CONTRIBUTION TO NONLINEAR PROPULSION AND PITCHING MOMENT PROPERTIES OF SLENDER WING-BODY COMBINATIONS
OTTO, H
ZEITSCHRIFT FUR FLUGWISSENSCHAFTEN, 1974, 22 (06): : 187 - 200
[7] GAP EFFECT ON SLENDER WING-BODY INTERFERENCE
MIRELS, H
JOURNAL OF THE AERONAUTICAL SCIENCES, 1953, 20 (08): : 574 - 575
[8] GAP EFFECT ON SLENDER WING-BODY INTERFERENCE
DUGAN, DW
JOURNAL OF THE AERONAUTICAL SCIENCES, 1954, 21 (01): : 57 - 58
[9] A FINITE VORTEX METHOD FOR SLENDER WING-BODY COMBINATIONS
CAMPBELL, GS
JOURNAL OF THE AERONAUTICAL SCIENCES, 1958, 25 (01): : 60 - 62
[10] Pitching-moment change caused by high-lift devices on wing-body configurations
van Es, GWH
JOURNAL OF AIRCRAFT, 2003, 40 (02): : 391 - 393