Normal-force-curve and pitching-moment-curve slopes of forebody-cylinder combinations at zero angle of attack for Mach numbers up to 5.
Abstract:ESDU 89008 uses data drawn from the literature to produce semi-empirical correlations for the aerodynamic characteristics of cone and ogive forebodies, either sharp or with varying degrees of spherical blunting, on cylindrical afterbodies. The correlations provide the two slopes as the sum of three contributions: the inviscid loading distribution at angle of attack, the changes caused by the boundary layer displacement thickness, and the skin friction contribution. A fully turbulent boundary layer is assumed and the correlations are expected to apply to all axisymmetric forebody shapes whether or not there is a smooth-surface transition from the forebody to the cylinder. The correlations are presented graphically and the ranges of geometries and flow conditions studied are tabulated. Two worked examples illustrate their application in practice. The calculation, procedure is programmed in ESDUpac A9034, see ESDU 90034.
- Cone Cylinders
- Ellipsoidal-Nosed Cylinders
- Normal-Force-Curve Slope
- Ogive Cylinders
- Pitching-Moment-Curve Slope (MW or Cmα)
|Data Item ESDU 89008|
The graphs listed below are available only to subscribers.
|Figure 1||CNαl as a function of M ∞ and lf/D|
|Figure 3||Displacement thickness at body base for fully turbulent boundary layers|
|Figure 4||Mean skin friction coefficient for fully turbulent boundary layers|
|Figure 6||G for bodies with discontinuity at forebody-cylinder junction|
|Figure 7||Δ[(Cm)0α/CNα]i for secant-ogive forebodies|
|Figure 8a||Δ[(Cm)0α/CNα]i for blunted tangent-ogive and cone forebodies|
|Figure 8b||Δ[(Cm)0α/CNα]i for blunted tangent-ogive and cone forebodies|