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Effects of Angle of Attack and Bluntness on Heating Rate Distribution of Blunt Models at Hypersonic Speeds

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Abstract

The effects of nose radius on stagnation and surface heat transfer rate along the surface are addressed in this research paper. Experiments are carried out in hypersonic shock tunnel, at hypersonic Mach number of 6.56 for 11.38° apex angle blunt cone with nose radius of 0.2R, base radius of R. Similarly, experiments are carried out at Mach 7.32 for 13.87° apex angle blunt cone models with nose radius of 0.18R′, base radius of R′. Test is performed at stagnation enthalpy of 1.4 and 2 MJ/kg with effective test time of 3.5 ms. Convective heat transfer measurements have been carried out on the test model at two different angles of attack, namely 0° and 5° with angle of rotation of 0°, 90°,180° with platinum thin film sensors. ANSYS-Fluent used to simulate the flow over the blunt models at different Mach numbers. The measured shock standoff distance from Schlieren visualization images compared with theory and computational fluid dynamic study for both configurations. The measured stagnation heating value is compared with theoretical value estimated using Fay-Riddell expression and numerical simulation. The measured heat transfer rate is higher for configuration 1 than configuration 2. The increases in heat transfer rate is due higher density ratio across the shock wave and the reduced shock layer thickness. The measured shock layer thickness is 2.06 mm for Mach 6.56 and 3.45 mm for Mach 7.32. The heat transfer rate is higher for Mach 6.56 as compared to Mach 7.32.

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Abbreviations

α:

angle of attack

D :

base diameter (mm)

s :

distance along the surface of model (mm)

θc :

semi cone angle

ϕ:

angle of rotation

R n :

nose radius

M:

Mach number

P :

pressure (bar)

ρ:

density (kg/m3)

T :

temperature (K)

h :

enthalpy (MJ/kg)

q(t):

local surface heat transfer rate

Q o :

heat transfer rate at nose (W/cm2)

CH :

Stanton number

0:

stagnation condition

inf:

free stream condition

1:

condition ahead of normal shock wave

2:

condition behind the normal shock wave

5:

condition behind the reflected shock wave

ANSYS:

analysis systems

DRDL:

defence research &development laboratory

TPS:

thermal protection system

CFD:

computational fluid dynamics

DAS:

data acquisition system

NI:

national instrument

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Authors and Affiliations

  1. Department of Aerospace Engineering, MLR Institute of Technology, Telangana, Hyderabad, India

    M. Saiprakash

  2. Department of Aerospace Engineering, MIT Campus, Anna University, Chennai, 600044, India

    C. Senthilkumar

  3. Directorate of Aerodynamics, Defence Research & Development Laboratory, Hyderabad, 500058, India

    G. Kadam sunil, Singh Prakash Rampratap, V. Shanmugam & G. Balu

Authors
  1. M. Saiprakash
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  2. C. Senthilkumar
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  3. G. Kadam sunil
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  4. Singh Prakash Rampratap
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  5. V. Shanmugam
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  6. G. Balu
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Corresponding authors

Correspondence to M. Saiprakash, C. Senthilkumar, G. Kadam sunil, Singh Prakash Rampratap, V. Shanmugam or G. Balu.

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Russian Text © The Author(s), 2019, published in Izvestiya RAN. Mekhanika Zhidkosti i Gaza, 2019, No. 6, pp. 114–127.

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Saiprakash, M., Senthilkumar, C., Kadam sunil, G. et al. Effects of Angle of Attack and Bluntness on Heating Rate Distribution of Blunt Models at Hypersonic Speeds. Fluid Dyn 54, 850–862 (2019). https://doi.org/10.1134/S0015462819060090

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  • DOI: https://doi.org/10.1134/S0015462819060090

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