Wave drag coefficient for axisymmetric forecowls at zero incidence (M∞ ≤ 1.5).
Abstract:ESDU 94014 presents charts for 20 cowls of the coefficient computed from finite difference solutions to the Euler equations for inviscid compressible flow. Computed shock waves are smeared over a few mesh cells which should give correct shock pressure jumps and wave drag. Data are presented for ranges of values of mass flow ratio and freestream Mach number. Sixteen cowls have NACA 1-series external profile, with differing combinations of diameter ratio and fineness ratio. The remaining four have fixed diameter ratio and fineness ratio but external profiles that differ systematically from the NACA 1-series profile. Charts of computed forecowl pressure force coefficient and pre-entry force coefficient are also given for each cowl for conditions at which a non-zero wave drag is calculated. See ESDU 94013 for details of the NACA 1-series profile and ESDU 94015 for pressure distribution data for the same profiles as treated here.
|Data Item ESDU 94014|
- Aircraft Noise
- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
- Physical Data, Chemical Engineering
- Stress and Strength
- Transonic Aerodynamics
- Vibration and Acoustic Fatigue
- Wind Engineering
Aerospace Materials Data
Additional Engineering References