Free-flight base pressure and heating measurements on sharp and blunt cones in a shock tunnel.

Lockman, W. K.

doi:10.2514/3.4328

Cited by 17 publications

(4 citation statements)

References 6 publications

(2 reference statements)

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“…Additional flight data are available from Cassanto [7] on 10°cones with blunting ratios up to 0.6. The data of Lockman (1967) using wiresupported models in a wind tunnel exhibited a systematic variation of nose blunting. Pick (1972) fired free flight sharp cones in a wind tunnel over a range of Mach number, Reynolds number, and angle of attack.…”

Section: Experimental Flow Conditions and Geometriesmentioning

confidence: 95%

“…Shown in Fig. 21 is Bulmer's laminar flight data for 9°cones with Lockman's (1967) measurements on 15°cones with blunting from zero to 40%. Lockman's data fall below the correlation line for Bulmer's data just as did the corresponding pressure measurements (Fig.…”

Section: Laminar Flowmentioning

confidence: 99%

“…31. This geometry and flow condition are from°o ne of Lockman's (1967) experiments. The figure shows profiles computed by an Euler code (SANDIAC) and a Parabolized Navier-Stokes code (SPRINT).…”

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confidence: 99%

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A review and development of correlations for base pressure and base heating in supersonic flow

Lamb

Oberkampf

1993

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A comprehensive review of experimental base pressure and base heating data related to supersonic and hypersonic flight vehicles has been completed. Particular attention was paid to free-flight data as well as wind tunnel data for models without rear sting support. Using theoretically based correlation parameters, a series of internally consistent, empirical prediction equations has been developed for planar and axisymmetric geometries (wedges cones, and cylinders). These equations encompass the speed range from low supersonic to hypersonic flow and laminar and turbulent forebody boundary layers. A wide°r ange of cone and wedge angles and cone bluntness ratios was included in the data base used to develop the correlations. The present investigation also included preliminary studies of the effect of angle of attack and specific-heat ' ratio of the gas. 3 OlSTRIBUTION OF TH!_"DOCUMENTl,SUNLIMITED Acknowledgment The authors thank Mary McWherter Walker of the Computational Fluid Dynamics Department at Sandia National Laboratories for computing the inviscid and parabolized Navier-Stokes solutions used in this study. The authors also thank David Kuntz and Vincent Amatucci of the Thermophysics Department at Sandia for reviewing this report and making a number of valuable suggestions.

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Section: Experimental Flow Conditions and Geometriesmentioning

confidence: 95%

Section: Laminar Flowmentioning

confidence: 99%

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A review and development of correlations for base pressure and base heating in supersonic flow

Lamb

Oberkampf

1993

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“…1 -5 -8 This paper is concerned with the further development of telemetry for the afterbody heat-transfer measurements presented in Ref. 9. In particular, increased system sensitivity and shielding techniques were developed where heating rates were low and where the measurement is likely to be obscured by noise produced by a hot plasma in the bow shock layer and wake of the model.…”

Section: Heat-transfer Telemetry For Models Using Thermocouple Sensorsmentioning

confidence: 99%

Heat-transfer telemetry for models using thermocouple sensors.

Harrison

Lockman

1969

Journal of Spacecraft and Rockets

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satisfactorily during entry. The panel was initially 3.2 cm thick. We estimate that the heating rate did not exceed 120 kw/m 2 , and the total heat load was about 8000 kjoules/m 2 . Postflight inspection indicated that at least 1.3 cm of undegraded foam remained, and the backface temperature did not exceed 370°K. ConclusionsThe low-density 5-1 foam is an excellent heat-shield material for protection at low heating rates. Despite the large removal rates in air at 170 kw/m 2 , the backface temperature increase was small except when the material was completely removed. The large surface-removal rates are apparently caused by oxidation. Resistance to oxidative removal may be improved by the addition of other materials to the foam system. Compositions of 5-1 with various filler additives will be evaluated in the future. The strength of the 5-1 foam or future composite foams can be enhanced with honeycomb while acceptable insulative capability is maintained. Nomenclature c = specific heat of sensor disk material, joules/kg °C E = output voltage of telemeter receiver, v q = heat-transfer rate, w/cm 2 Rb = base radius of cones, cm R n = nose radius of cones, cm t = time, sec a. = sensitivity of telemeter receiver discriminator, mv/kHz | 8 = sensitivity of thermocouple, MV/°C 7 = sensitivity of telemeter voltage-controlled oscillator, kHz/Vv p = density of sensor disk material, kg/cm 3 T = thickness of sensor disk, cm R ECENT developments in the application of telemetry to tunnel testing have clearly indicated that the model support system used in conventional testing can significantly alter the aerodynamic parameters from the free-flight conditions. 1 * 2 Such results have encouraged the development of telemetry for free-flight measurements of aerodynamic stability parameters, 3 -4 afterbody pressures, 1 > 2 -5~7 and afterbody heating rates. 1 -5 -8 This paper is concerned with the further development of telemetry for the afterbody heat-transfer measurements presented in Ref. 9. In particular, increased system sensitivity and shielding techniques were developed where heating rates were low and where the measurement is likely to be obscured by noise produced by a hot plasma in the bow shock layer and wake of the model. The approach used here is similar to that of Ref. 1, but the technique has been considerably improved and now provides a greatly increased signal-to-noise ratio under tunnel test conditions. The present method employs a calorimeter using a relatively insensitive thermocouple sensor with an amplifier to provide usable signal voltages for telemetering. At the expense of the additional amplifier circuitry, this approach avoids most of the major problems encountered with the use of resistive sensors. 1 -5 ' 10 ' 11 Basically, the telemeter system consists of a thermocouple sensor and a differential amplifier which controls the frequency of an rf oscillator. The rf energy is radiated directly from the oscillator tuned circuit inductance. The receiving system consists of a loop antenna, a vhf preamplifier, and an...

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Gorshkov¹,

Lunev²

2002

Fluid Dynamics

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Free-flight base pressure and heating measurements on sharp and blunt cones in a shock tunnel.

Cited by 17 publications

References 6 publications

A review and development of correlations for base pressure and base heating in supersonic flow

A review and development of correlations for base pressure and base heating in supersonic flow

Heat-transfer telemetry for models using thermocouple sensors.

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