| 70 |
 The mean skin friction coefficient for a rough flat plate with a turbulent two-dimensional boundary layer in compressible adiabatic flow, with application to wedges, cylinders and cones. |
73016 |
| 70 |
The compressible two-dimensional turbulent boundary layer, both with and without heat transfer, on a smooth flat plate, with application to wedges, cylinders, and cones. |
68020 |
| 70 |
The compressible two-dimensional laminar boundary layer, both with and without heat transfer, on a smooth flat plate, with application to wedges, cylinders, and cones. |
68019 |
| 70 |
Critical Mach number for high speed aerofoil sections.
|
Aero W.00.03.01 |
| 70 |
Critical pressure coefficient and component of local Mach number normal to the surface isobar for a swept wing.
|
75027 |
| 70 |
Estimation of critical Mach number for an aerofoil from its low-speed pressure distribution. |
74008 |
| 70 |
Pressure distribution on blunt noses of two-dimensional sections at zero incidence in supersonic flow. |
Aero W.S.05.03.01 |
| 70 |
Profile drag coefficients for two-dimensional biconvex aerofoil with zero heat transfer at supersonic speeds. |
Aero W.S.02.04.13 |
| 70 |
Skin friction drag coefficients for a flat plate in two-dimensional flow with zero heat transfer. |
Aero W.S.02.04.12 |
| 70 |
Wave drag of flat plates with blunt noses at zero incidence. |
Aero W.S.02.03.10 |
