Aerodynamic force measurements over missile configurations in IISc shock tunnel at M∞ =3.85 and 9.15

Raju, Channa; Reddy, N. M.

doi:10.1007/bf00215027

Cited by 14 publications

(6 citation statements)

References 1 publication

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“…A schematic diagram of the balance system is shown in figure 3a and a photograph of the balance system along with a typical missile model is shown in figure 3b. The detaits of this balance system along with the basic theory have been reported earlier (Reddy 1983, Joshi & Reddy 1986: Channa Raju & Reddy 1990).…”

Section: Measurement Of Aerodynamic Forces Over Missile Shaped Bodiessupporting

confidence: 54%

“…This balance system has been successfully used to measure the aerodynamic force coefficients like the lift, drag and moment over different aerodynamic bodies of interest flying at Mach numbers 3.85, 5.5 and 9.15 (Shah 1983: Joshi 1985Joshi & Reddy 1985, 1986Channa Raju 1989;Channa Raju & Reddy 1990). Model configurations chosen for the investigations are the typical nose cone-cylinder configurations used for missiles and re-entry vehicles.…”

Section: Measurement Of Aerodynamic Forces Over Missile Shaped Bodiesmentioning

confidence: 99%

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Review of hypersonic research investigations in IISc shock tunnel (HST1)

Reddy

Nagashetty

Jagadeesh

et al. 1996

Sadhana

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Real gas effects dominate the hypersonic flow fields encountered by modem day hypersonic space vehicles. Measurement of aerodynamic data for the design applications of such aerospace vehicles calls for special kinds of wind tunnels capable of faithfully simulating real gas effects. A shock tunnel is an established facility commonly used along with special instrumentation for acquiring the data for this purpose within a short time period. The hypersonic shock tunnel (HST1), established at the Indian Institute of Science (IISc) in the early 1970s, has been extensively used to measure the aerodynamic data of various bodies of interest at hypersonic Mach numbers in the range 4 to 13. Details of some important measurements made during the period 1975-1995 along with the performance capabilities of the HST 1 are presented in this review. In view of the re-emergence of interest in hypersonics across the globe in recent times, the present review highlights the suitability of the hypersonic shock tunnel at the IISc for future space application studies in India.

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Section: Measurement Of Aerodynamic Forces Over Missile Shaped Bodiessupporting

confidence: 54%

Section: Measurement Of Aerodynamic Forces Over Missile Shaped Bodiesmentioning

confidence: 99%

Review of hypersonic research investigations in IISc shock tunnel (HST1)

Reddy

Nagashetty

Jagadeesh

et al. 1996

Sadhana

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“…But the complete measurement system is cumbersome and moreover it is difficult to maintain the necessary level of accuracy during measurement. The other type of support system is by mounting the model with flexible rubber bushes [7,9] such that the rubber bushes have negligible effect during the free flight duration of $1 ms. However the analysis is limited to simple slender configurations such as cones and cylinders.…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

et al. 2007

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“…[10][11] Extending this facility to shock tunnels, researchers conducted force measurement successfully on a missile shaped configuration at supersonic and hypersonic Mach numbers. [12][13] The surface heating measurements on blunt bodies for variety of interdisciplinary space science applications have also been exhaustively carried out. [14][15][16] With the above viewpoint, the authors report about installation of a particular shock tube facility as one of the case study.…”

Section: Introductionmentioning

confidence: 99%

Fabrication and Installation of Moderate Size Shock Tube Facility – A Case Study

Agarwal¹,

Sahoo²

2017

AAOAJ

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A moderate size shock tube of 7m long with inner diameter of 55mm and thickness of 20mm has been is designed in-house and installed successfully in the Mechanical Engineering Department at Indian Institute of Technology Guwahati (IITG). The shock wave is generatedby rupturing metallic diaphragms instantly with appropriate pressure ratios across the driver (2m) and driven (5m) section of the shock tube. The pressure rise across the across primary and reflected shock is measured by high frequency pressure transducers located towards end of driven section. All necessary shock tube parameters are calculated through one-dimensional shock tube relations and are validated with experimental data.

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Aerodynamic force measurements over missile configurations in IISc shock tunnel at M∞ =3.85 and 9.15

Cited by 14 publications

References 1 publication

Review of hypersonic research investigations in IISc shock tunnel (HST1)

Review of hypersonic research investigations in IISc shock tunnel (HST1)

Design and analysis of a flat accelerometer-based force balance system for shock tunnel testing

Fabrication and Installation of Moderate Size Shock Tube Facility – A Case Study

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