Liftoff and Transition Aerodynamics of the Ares I Launch Vehicle

Capone, F. J.; Paulson, John W.; Erickson, Gary E.

doi:10.2514/1.58973

Cited by 2 publications

(5 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The thickness of the boundary layer in the test section near the location of the SLS model is about 5 inches. Previous LOT experiments performed by Capone et al 2 and Pinier et al 3 did not use the boundary layer removal system because the wind tunnel model was always above this height from the floor and they concluded that the floor boundary layer effects were minimal and could be ignored. Similarly, the system was not used for SLS LOT Test 633.…”

Section: Wind Tunnel Descriptionmentioning

confidence: 99%

“…This is not easy for a slender launch vehicle that is pitched and rolled to large angles during testing. Capone et al 2 led a study of the most effective boundary layer tripping strategy for this type of vehicle and found that a uniform sprinkling of #80-grit (approximately 0.008 inch size) on the entire body was the most consistent and predictable way to trip the boundary layer. The previous SLS LOT test used this strategy, therefore, the same strategy was used for Test 633.…”

Section: B Boundary Layer Transitionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic Characterization and Improved Testing Methods for the Space Launch System Liftoff and Transition Environment

Chan

Paulson

Shea

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

View full text Add to dashboard Cite

Low-speed wind tunnel testing for the liftoff and transition environment of the Space Launch System (SLS) was recently completed in the NASA Langley Research Center 14by 22-Foot Subsonic Tunnel using 1.75%-scale models of three SLS vehicle configurations. During the liftoff testing, the primary objective was to evaluate the aerodynamic forces and moments on the SLS launch vehicles, as the vehicle, launch tower, and mobile launch platform were subjected to ground winds from all directions at varying heights for the vehicle off the launch pad. Additionally, aerodynamic forces and moments were acquired for all three SLS vehicles during the transition phase from liftoff to ascent that covered a wide range of angles of attack and angles of sideslip. Details of the experimental setup including improved testing methods and a stiffer sting-balance system based on lessons learned from previous test entries are presented. Also, a new force measurement technique was applied during the test where two subminiature six-component load cells were installed in each Solid Rocket Booster (SRB) to acquire forces and moments for each SRB separately from the full vehicle forces and moments measured by the main strain gauge balance. Finally, sample results from the experiment are presented including improved overall data coverage, evaluation of the new SRB data, and smoke flow visualization photos.

show abstract

Section: Wind Tunnel Descriptionmentioning

confidence: 99%

Section: B Boundary Layer Transitionmentioning

confidence: 99%

Aerodynamic Characterization and Improved Testing Methods for the Space Launch System Liftoff and Transition Environment

Chan

Paulson

Shea

et al. 2019

AIAA Scitech 2019 Forum

Self Cite

View full text Add to dashboard Cite

show abstract

“…Because the wind tunnel model was always above this distance from the floor, it was decided not to remove the test section boundary layer. Capone et al 4 also recently showed during a very similar test conducted with the Ares I launch vehicle that the floor boundary layer effects were minimal and could be ignored. Because of the scale of the model, the Reynolds number of the flow on the vehicle is lower than in full scale flight.…”

Section: Introductionmentioning

confidence: 95%

“…This test builds on knowledge and experience gained during testing of the liftoff aerodynamics of the Ares I launch vehicle in the same wind tunnel during the Constellation program. Capone et al 4 describe this test in detail. Many valuable lessons were learned during the Ares I test, which enabled a successful and efficient SLS test.…”

Section: Introductionmentioning

confidence: 99%

“…It is therefore important to devise a strategy to trip the boundary layer to make it turbulent, like on the flight vehicle. Capone et al 4 led a study of the most effective boundary layer tripping strategy on a slender launch vehicle that is pitched and rolled during testing. They found that a uniform sprinkling of #80-grit on the entire body was the most consistent and predictable way to trip the boundary layer.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Space Launch System Liftoff and Transition Aerodynamic Characterization in the NASA Langley 14x22' Subsonic Wind Tunnel

Pinier

Erickson

Paulson

et al. 2015

53rd AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

Notice to the Reader The Space Launch System, including its predicted performance and certain other features and characteristics, has been defined by the U.S. Government to be Sensitive But Unclassified (SBU). Information deemed to be SBU requires special protection and may not be disclosed to an international audience, such as the audience that might be present at the 2015 AIAA SciTech Conference. To comply with SBU restrictions, details such as absolute values have been removed from some plots and figures in this paper. It is the opinion of the authors that despite these alterations, there is no loss of meaningful technical content. Analytical methodologies and experimental capabilities are discussed; significant technical results are presented; and meaningful conclusions and lessons learned are provided.

show abstract

Liftoff and Transition Aerodynamics of the Ares I Launch Vehicle

Cited by 2 publications

References 0 publications

Aerodynamic Characterization and Improved Testing Methods for the Space Launch System Liftoff and Transition Environment

Aerodynamic Characterization and Improved Testing Methods for the Space Launch System Liftoff and Transition Environment

Space Launch System Liftoff and Transition Aerodynamic Characterization in the NASA Langley 14x22' Subsonic Wind Tunnel

Contact Info

Product

Resources

About