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Sādhanā

, 43:63 | Cite as

Aerodynamic characteristics of an ogive-nose spinning projectile

  • J LIJIN
  • T J S JOTHI
Article

Abstract

This work experimentally investigates the Robins–Magnus effect on a 5-caliber spinning projectile at a low subsonic Mach number of 0.1 corresponding to a Reynolds number of 3.2 × 105 based on the model length. The model configuration tested was a cylinder with spherically blunt tangent ogive nose portion. The normal, axial and side force coefficients were obtained for various angles of attack (α) ranging from 0° to 34° with non-dimensional spin rates (Ω) of 0–0.05. Results indicate that the side force coefficient increases with α up to a value of around 28° and decreases thereafter. Interestingly, in the range of spin rates considered in the present study, normal and axial force coefficients are not affected due to spin. However, the side force coefficients are seen to increase with spin rates at higher α. Flow visualization studies are demonstrated to explain the underlying mechanism behind the variation of these aerodynamic coefficients.

Keywords

Spinning projectile spinning missile Robins–Magnus force aerodynamic coefficients 

List of symbols

lB

projectile length, m

d

projectile diameter, m

lN

projectile nose length, m

A

projectile cross-sectional area, m2

FL

lift, N

FD

drag, N

FN

normal force, N

FA

axial force, N

FY

Robins–Magnus/side force, N

V

free-stream velocity, m/s

ρ

density, kg/m3

q

dynamic pressure \( \frac{{\rho V_{\infty }^{2} }}{2} \), Pa

\( Re_{l} \)

Reynolds number based on projectile length

α

angle of attack, deg

p

spin rate, rad/s

Ω

non-dimensional spin rate, \( {\raise0.7ex\hbox{${pd}$} \!\mathord{\left/ {\vphantom {{pd} {2V_{\infty } }}}\right.\kern-0pt} \!\lower0.7ex\hbox{${2V_{\infty } }$}} \)

CN

normal force coefficient, \( {\raise0.7ex\hbox{${F_{N} }$} \!\mathord{\left/ {\vphantom {{F_{N} } {q_{\infty } A}}}\right.\kern-0pt} \!\lower0.7ex\hbox{${q_{\infty } A}$}} \)

CA

axial force coefficient, \( {\raise0.7ex\hbox{${F_{A} }$} \!\mathord{\left/ {\vphantom {{F_{A} } {q_{\infty } A}}}\right.\kern-0pt} \!\lower0.7ex\hbox{${q_{\infty } A}$}} \)

CY

side force coefficient, \( {\raise0.7ex\hbox{${F_{Y} }$} \!\mathord{\left/ {\vphantom {{F_{Y} } {q_{\infty } A}}}\right.\kern-0pt} \!\lower0.7ex\hbox{${q_{\infty } A}$}} \)

CL

lift force coefficient, \( {\raise0.7ex\hbox{${F_{L} }$} \!\mathord{\left/ {\vphantom {{F_{L} } {q_{\infty } A}}}\right.\kern-0pt} \!\lower0.7ex\hbox{${q_{\infty } A}$}} \)

CD

drag force coefficient, \( {\raise0.7ex\hbox{${F_{D} }$} \!\mathord{\left/ {\vphantom {{F_{D} } {q_{\infty } A}}}\right.\kern-0pt} \!\lower0.7ex\hbox{${q_{\infty } A}$}} \)

Notes

Acknowledgement

The authors would like to thank the anonymous reviewers for their valuable comments and suggestions for improving the manuscript.

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Copyright information

© Indian Academy of Sciences 2018

Authors and Affiliations

  1. 1.Department of Mechanical EngineeringNational Institute of Technology CalicutKozhikodeIndia

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