Real-time wall interference correction system of the 12 ft pressure wind tunnel

Ulbrich, Norbert; Boone, Alan

doi:10.2514/6.1998-707

Cited by 23 publications

(10 citation statements)

References 4 publications

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“…TWICS and its predecessor, the Wall Interference Correction System (WICS), were developed at the NASA Ames Research Center by Ulbrich et al [22][23][24][25][26][27][28][29] as a modification and extension of the Hackett wall signature method. [30][31][32][33][34] TWICS is an enhanced version of WICS that handles ventilated boundary conditions, typically seen in transonic wind tunnels.…”

Section: Wall Correction Methods For Ntf and Ames 11-ft Wind Tunnelsmentioning

confidence: 99%

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Rivers

Hunter

Campbell

2012

30th AIAA Applied Aerodynamics Conference

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An experimental investigation of the NASA Common Research Model was conducted in the NASA Langley National Transonic Facility and NASA Ames 11-foot Transonic Wind Tunnel Facility for use in the Drag Prediction Workshop. As data from the experimental investigations was collected, a large difference in moment values was seen between the experiment and computational data from the 4 th Drag Prediction Workshop. This difference led to a computational assessment to investigate model support system interference effects on the Common Research Model. The results from this investigation showed that the addition of the support system to the computational cases did increase the pitching moment so that it more closely matched the experimental results, but there was still a large discrepancy in pitching moment. This large discrepancy led to an investigation into the shape of the as-built model, which in turn led to a change in the computational grids and re-running of all the previous support system cases. The results of these cases are the focus of this paper. Nomenclature b= wing span, in. c = wing mean aerodynamic chord, in. = CRM wing/body/tail=0° configuration WBT0ss = CRM wing/body/tail=0° with support system configuration WBT0ssa = CRM wing/body/tail=0° with support system and arc sector configuration x/c = longitudinal distance from wing leading edge nondimensionalized by local wing chord α = angle-of-attack, degrees δ = change in per unit area values η = fraction of wing semi-span φ = radial station, degrees Δ = change in total values

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Section: Wall Correction Methods For Ntf and Ames 11-ft Wind Tunnelsmentioning

confidence: 99%

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Rivers

Hunter

Campbell

2012

30th AIAA Applied Aerodynamics Conference

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show abstract

“…TWICS and its predecessor, the Wall Interference Correction System (WICS), were developed at the NASA Ames Research Center by Ulbrich et al [17][18][19][20][21][22][23][24] as a modification and extension of the Hackett wall signature method. [25][26][27][28][29] TWICS is an enhanced version of WICS that handles ventilated boundary conditions, typically seen in transonic wind tunnels.…”

Section: Wall Correction Methods For Ntf and Ames 11-ft Wind Tunnelsmentioning

confidence: 99%

Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited)

Rivers

Dittberner

Sverdrup³

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

117

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Experimental aerodynamic investigations of the NASA Common ResearchModel have been conducted in the NASA Langley National Transonic Facility and the NASA Ames 11-ft wind tunnel. Data have been obtained at chord Reynolds numbers of 5 million for five different configurations at both wind tunnels. Force and moment, surface pressure and surface flow visualization data were obtained in both facilities but only the force and moment data are presented herein. Nacelle/pylon, tail effects and tunnel to tunnel variations have been assessed. The data from both wind tunnels show that an addition of a nacelle/pylon gave an increase in drag, decrease in lift and a less nose down pitching moment around the design lift condition of 0.5 and that the tail effects also follow the expected trends. Also, all of the data shown fall within the 2-sigma limits for repeatability. The tunnel to tunnel differences are negligible for lift and pitching moment, while the drag shows a difference of less than ten counts for all of the configurations. These differences in drag may be due to the variation in the sting mounting systems at the two tunnels.

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“…TWICS and its predecessor, the Wall Interference Correction System (WICS), were developed at the NASA Ames Research Center by Ulbrich et al [20][21][22][23][24][25][26][27] as a modification and extension of the Hackett wall signature method. [28][29][30][31][32] TWICS is an enhanced version of WICS that handles ventilated boundary conditions, typically seen in transonic wind tunnels.…”

Section: Wall Correction Methods For Ntf and Ames 11-ft Wind Tunnelsmentioning

confidence: 99%

Support System Effects on the NASA Common Research Model

Rivers

Hunter

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Real-time wall interference correction system of the 12 ft pressure wind tunnel

Cited by 23 publications

References 4 publications

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Further Investigation of the Support System Effects and Wing Twist on the NASA Common Research Model

Experimental Investigations of the NASA Common Research Model in the NASA Langley National Transonic Facility and NASA Ames 11-Ft Transonic Wind Tunnel (Invited)

Support System Effects on the NASA Common Research Model

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