Space launch vehicle aerodynamics - Comparison of engineering and CFD predictions with wind tunnel data

Shivananda, T.; McKeel, S. A.; Salita, Mark; Zabrensky, E.

doi:10.2514/6.2001-258

Cited by 3 publications

(1 citation statement)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…DATCOM has been widely used in projects for aerodynamic force and moment predictions of most air vehicle configurations [9][10][11][12]. The reference length and reference area values correspond to the mean chord of the tail wing and its plane area, respectively.…”

Section: Methodsmentioning

confidence: 99%

Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

2009

View full text Add to dashboard Cite

This paper presents an aerodynamic study for a target unmanned air vehicle with controlled canard, at cruise Mach number between 0.7 and 0.85, using a solid rocket motor as power. The results of semi-empirical method (DATCOM), computational fluid dynamics (CFD) were compared with wind tunnel tests to evaluate perdition accuracy. Here DATCOM shows big discrepancy in pitching-moment coefficient; the CFD estimation of static aerodynamic force and moment agree well with wind tunnel data. An analysis was focused on the longitudinal data for complicated controlled canard-elements interactions and canard vortex behavior. The canard vortex interaction with tail wing of initial configuration concept with a thick canard (NACA0012) and the final improved configuration with a thin canard (NACA0007) were reviewed. It is proved that the stability and control characteristics of whole TUAV are sensitive to the thickness of canard in transonic peed regime because of different canard vortex intensity and effect generated.

show abstract

Section: Methodsmentioning

confidence: 99%

Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

2009

View full text Add to dashboard Cite

show abstract

Aerodynamic study of theater ballistic missile target

Zhang

Wang

Liu

2013

Aerospace Science and Technology

View full text Add to dashboard Cite

Test Section Design for Measuring the Drag Coefficient of a Suborbital Rocket Model at Ma 2.45

Wasilczuk,

Kurowski,

Flaszyński

2024

Transactions on Aerospace Research

View full text Add to dashboard Cite

This study investigates the drag coefficient of three models of suborbital rockets with different nosecones. A test section allowing for force measurement of a 1:50 scale rocket model was designed with the aid of numerical simulations. The velocity obtained in the wind tunnel corresponds with a Mach number of 2.45. RANS simulations were used in verifying operating parameters, as well as testing the support configurations for connecting the model with the bottom wall of the tunnel section. Pressure distribution measurements on the top and bottom walls of the wind tunnel matched simulation results well. The shock structure in the test section was visualized using the schlieren technique, revealing that the measured angle of the main shock generated at the tip of the rocket matched the simulation data. Finally, the measured forces were compared with simulations for one of the nosecone configurations. Despite very good agreement for pressure distribution on the wind tunnel walls and shock structure, a significant mismatch in the forces measured was nevertheless observed: the simulated CD (0.57) being four times larger than that obtained in measurements (0.138). Further analysis of the test section is required to pinpoint the source of discrepancies and redesign the force measurement system to achieve improved force results.

show abstract

Space launch vehicle aerodynamics - Comparison of engineering and CFD predictions with wind tunnel data

Cited by 3 publications

References 1 publication

Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

Controlled canard configuration study for a solid rocket motor based unmanned air vehicle

Aerodynamic study of theater ballistic missile target

Test Section Design for Measuring the Drag Coefficient of a Suborbital Rocket Model at Ma 2.45

Contact Info

Product

Resources

About