Application of pressure sensitive paint for determining aerodynamic loads on a scale model of the F-16C

Sellers, Marvin E.

doi:10.2514/6.2000-2528

Cited by 33 publications

(8 citation statements)

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“…3,8 Figure 1 shows an example of a set of calibration curves for the paint PtTFPP in FIB, 9 which is produced by Innovative Scientific Solutions, Inc. and is the current industry standard for large-scale PSP testing in the U.S. Ideally, the temperature, T, in Eq.…”

Section: A Paint Responsementioning

confidence: 99%

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On-Line Processing of Pressure-Sensitive Paint Images

Ruyten

Sellers

2004

Journal of Aerospace Computing, Information, and Communication

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This paper documents a milestone that has been reached at the Arnold Engineering Development Center, namely to reduce data reduction times for both intensity-based and lifetime-based pressure-sensitive paint measurements from an eight-camera system sufficiently that one data point can be processed in full (in 5 to 10 s) while the next data point is being acquired. The paper describes the hardware, software, and data reduction strategies used, and it presents results for benchmark data from wind tunnel tests on scale models of an F-16C fighter jet and NASA's X-38 Crew Return Vehicle.

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Section: A Paint Responsementioning

confidence: 99%

“…[1][2][3][4][5][6][7] Most commonly, the luminescence from the painted test article is captured using digital cameras. Thus, PSP is essentially an image-based technique.…”

Section: Introductionmentioning

confidence: 99%

On-Line Processing of Pressure-Sensitive Paint Images

Ruyten

Sellers

2004

Journal of Aerospace Computing, Information, and Communication

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“…3a). 19 Both tests were performed in AEDC's 16-ft transonic wind tunnel, with eight charge-coupled device (CCD) cameras mounted as shown in Fig. 1.…”

Section: Application Examplesmentioning

confidence: 99%

More Photogrammetry for Wind-Tunnel Testing

Ruyten

2002

AIAA Journal

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964-971) has led to renewed interest in the use of photogrammetry for measuring the position, attitude, and deformation of a test article in a wind tunnel. The present research expands on this work with a more comprehensive mathematical model that can be used not only for determining the interior parameters of the cameras, but also the wind-off alignment of both the cameras and the test article relative to the wind tunnel. This calibration is achieved by combining data from multiple cameras and multiple model attitude settings in a single least-squares t, though (with eight cameras) as many as 94 t parameters can be involved. Similarly, data from multiple cameras are combined in a single sixparameter t to determine the position and attitude of the test article at wind-on conditions. Precision estimates of tted parameters are obtained through use of the covariance-matrix formalism and by bootstrapping. The model is demonstrated on data from two pressure-sensitive paint tests. An absolute accuracy of 0.01 deg for pitch measurements is demonstrated for this nonoptimized con guration. Suggestions for improvements are given for a dedicated optical model attitude measurement system.

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“…Excellent reviews on the subject may be seen in the articles by Crites (1) , Liu et al (2) , and Bell (3) et al Notable progress has been made, particularly on aspects of data processing of PSP images and resection based methodology is known to yield enhanced accuracy of PSP results (4) .While the PSP technique has been widely used on models in transonic wind tunnels (5)(6)(7)(8) , very few applications in supersonic flow are available in literature. Earlier work on the application of PSP on highly swept wings at supersonic speeds include those of McLachlan et al (9) and Shimbo et al (10) .…”

mentioning

confidence: 97%

“…While the PSP technique has been widely used on models in transonic wind tunnels (5)(6)(7)(8) , very few applications in supersonic flow are available in literature. Earlier work on the application of PSP on highly swept wings at supersonic speeds include those of McLachlan et al (9) and Shimbo et al (10) .…”

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confidence: 99%

Pressure sensitive paint measurements on a delta-wing in supersonic flow

2006

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Last decade has witnessed significant developments on the application of pressure sensitive paint technique to the measurement of surface pressure distributions on wind tunnel models. Excellent reviews on the subject may be seen in the articles by Crites (1) , Liu et al (2) , and Bell (3) et al. Notable progress has been made, particularly on aspects of data processing of PSP images and resection based methodology is known to yield enhanced accuracy of PSP results (4) .While the PSP technique has been widely used on models in transonic wind tunnels (5)(6)(7)(8) , very few applications in supersonic flow are available in literature. Earlier work on the application of PSP on highly swept wings at supersonic speeds include those of McLachlan et al (9) and Shimbo et al (10) . McLachlan et al conducted PSP tests on a high sweep oblique wing model at Mach numbers of 1·6, 1·8 and 2·0 at relatively low angles of attack (-4°to 2°). Their PSP results using an insitu calibration compared well with pressure tap data at two Mach numbers. Shimbo et al (10) applied PSP and TSP (Temperature Sensitive Paint) to a scaled supersonic experimental airplane model at Mach numbers of 1·4, 1·6, 1·8 and 2·0 at zero incidence. PSP was applied to one side of the wing and TSP to the other side. Detailed comparisons with pressure port data showed that PSP data, in general, had a shift of about 0·1 in C p towards a higher pressure direction at Mach 2·0. Application of PSP technique to different flow problems (11)(12)(13)(14) and an assessment of its accuracy has been a major focus in our laboratory. Recently the technique was successfully applied to a 3D shock-induced boundary-layer interaction at Mach 1·8 (12) . It may be noted that, in all the above investigations, image registration using algebraic transforms was adopted. ABSTRACTExperiments have been performed documenting the pressure field on the lee-side of a delta-wing at three incidence angles (5°, 10°, and 15°) and at Mach 1·8 using a PSP (Pressure Sensitive Paint) technique. The delta-wing model having a leading edge sweep of 60°w as instrumented with 31 spanwise pressure ports at 68% of mean chord location. The Optrod-B1 binary paint was utilised and the PSP images were processed employing a resection based methodology. The comparisons of PSP results with those measured employing pressure taps show good agreement at different incidence angles. NOMENCLATUREC p surface pressure coefficient (p-p ∞ )/q ∞ I luminescence intensity I o intensity at reference conditions I R normalised intensity ratio [I/I o ] red ÷ [I/I o ] blue (Fig. 4) L length of the model, 103mm M Freestream Mach number, 1·80 p surface pressure p ∞ freestream static pressure q ∞ freestream dynamic pressure X distance along the span, from the model centreline Y distance along the model length from the model apex a model incidence angle, deg.

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Application of pressure sensitive paint for determining aerodynamic loads on a scale model of the F-16C

Cited by 33 publications

References 1 publication

On-Line Processing of Pressure-Sensitive Paint Images

On-Line Processing of Pressure-Sensitive Paint Images

More Photogrammetry for Wind-Tunnel Testing

Pressure sensitive paint measurements on a delta-wing in supersonic flow

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