Bodies of revolution with minimal drag coefficient and low heat transfer at high supersonic speeds

Grodzovskii, G. L.

doi:10.1007/bf01029537

Cited by 1 publication

(1 citation statement)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Nevertheless, the efficiency of the approximate laws for the profiling nose shapes has been confirmed by investigations using exact methods of calculation. In the case of power-law bodies (r = x m , where x is measured along the axis of symmetry from the leading point of the body and r is the distance to the axis) calculations using Euler's equations showed that the optimum value of the exponent m lies in the range 0.60 to 0.75 [6]. Newton's theory gives value m = 3/4 for thin noses.…”

Section: Nose Shapes Of Minimum Wave Dragmentioning

confidence: 99%

Direct Method of Aerodynamic Shape Optimization For Supersonic Aircraft Design

Takovitskii

2023

joast

View full text Add to dashboard Cite

The efficient direct optimization method for Supersonic Aircraft Design is presented. Aerodynamic drag and sonic boom signature parameters are used as the objective functions minimized under geometric and aerodynamic constraints. The method combines Newton based algorithm with Euler space-marching solver. The efficiency of the method is demonstrated on examples of two- and three-dimensional aerodynamic design. Nose shapes that ensure minimum wave drag for specified constraints on the overall size are defined. It is shown that the near-optimal axisymmetric noses have a flat forward face. The median surface of a complex plane form wing with minimal drag due to lift is constructed. The simplest shape deformation of the wing providing the main part of aerodynamic drag diminishing is established. To profile the aircraft wing and fuselage providing optimal sonic boom parameters approaches of theory for sonic boom propagation are included in the method. The initial shock intensity as the primary value of the pressure signature is minimized. The results obtained within the framework of the Eulers equations and simplified flow models are compared.

show abstract

Section: Nose Shapes Of Minimum Wave Dragmentioning

confidence: 99%

Direct Method of Aerodynamic Shape Optimization For Supersonic Aircraft Design

Takovitskii

2023

joast

View full text Add to dashboard Cite

show abstract

Bodies of revolution with minimal drag coefficient and low heat transfer at high supersonic speeds

Cited by 1 publication

References 10 publications

Direct Method of Aerodynamic Shape Optimization For Supersonic Aircraft Design

Direct Method of Aerodynamic Shape Optimization For Supersonic Aircraft Design

Contact Info

Product

Resources

About