SIMPLIFIED TREATMENT OF THE TURBULENT BOUNDARY LAYER ALONG A CYLINDER IN COMPRESSIBLE FLOW

被引：16

作者：

ECKERT, HU

机构：

来源：

JOURNAL OF THE AERONAUTICAL SCIENCES | 1952年 / 19卷 / 01期

关键词：

D O I：

10.2514/8.2144

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

引用

页码：23 / &

共 14 条

[1] CHAPMAN DR, 1950, NACA TN2137
[2] CHARACTERISTICS OF THE TURBULENT BOUNDARY LAYER ON A FLAT PLATE IN COMPRESSIBLE FLOW FROM MEASUREMENTS OF FRICTION IN PIPES
ECKERT, HU
[J]. JOURNAL OF THE AERONAUTICAL SCIENCES, 1950, 17 (09): : 573 - 584
[3] Jakob M., 1946, T ASME, V68, P123
[4] KURZWEG H, 1949, S EXPT COMPRESSIBLE, P103
[5] INTERRELATIONSHIP BETWEEN BOUNDARY LAYER AND BASE PRESSURE
KURZWEG, HH
[J]. JOURNAL OF THE AERONAUTICAL SCIENCES, 1951, 18 (11): : 743 - 748
[6] RUBESIN MW, 1951, NACA TN2305
[7] Schultz-Grunow F., 1940, LUFTFAHRTFORSCHUNG, V17, P239
[8] SKIN-FRICTION AND HEAT-TRANSFER CHARACTERISTICS OF A LAMINAR BOUNDARY LAYER ON A CYLINDER IN AXIAL INCOMPRESSIBLE FLOW
SEBAN, RA
BOND, R
[J]. JOURNAL OF THE AERONAUTICAL SCIENCES, 1951, 18 (10): : 671 - 675
[9] SEBAN RA, 1949, SKIN FRICTION HEAT T
[10] SPIVACK HM, 1950, CM615 N AM AV REP