![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2019\/05\/B1C_Model_UPWT_stitch.jpg\")
<\/p>\nNASA engineers at the Langley Research Center in Hampton, Virginia, recently completed one set of wind tunnel tests in a series on the aerodynamics of the newest Space Launch System (SLS) vehicle configuration. Data was collected during several hundred supersonic test runs in the Unitary Plan Wind Tunnel at Langley of a scale model of the Block 1 Cargo vehicle that is the currently mandated booster for the upcoming Europa Clipper mission.<\/p>\n
The first of six major testing campaigns began last year and are being conducted at NASA wind tunnels across the United States in support of the SLS Program\u2019s design analysis of the new configuration. The aerodynamic data is used to refine analysis and modeling of the vehicle\u2019s atmospheric trajectories, Guidance, Navigation, and Control (GNC), and structural loading.<\/p>\n
Testing is planned to cover the early phase of flight all the way out to Solid Rocket Booster (SRB) separation, going back to the liftoff period to measure the effect of ground winds on the rocket, and also before liftoff while sitting on the Mobile Launcher.<\/p>\n
Supersonic Mach range test campaign for new SLS vehicle config<\/p>\n
A 0.8-percent scale model of the SLS Block 1 Cargo configuration was set up in the Unitary Plan Wind Tunnel at Langley for this round of aerodynamics testing. \u201cWe did about seven hundred runs, that was covering the Mach range in different pitches and rolls,\u201d Courtney Winski, a research aerospace engineer at NASA Langley, said in an interview. \u201cWe just completed that test, that was Mach 1.5 to 4.5.\u201d<\/p>\n
During test runs, the wind tunnel was run at a set velocity and then data was taken as the model was moved through different orientations. \u201cWe are varying angle of attack and roll, so we\u2019re doing pitch and roll combinations or alpha-roll combinations along with Mach number combinations, doing the same sets of pitch and roll at different Mach numbers,\u201d Winski explained.<\/p>\n
\u201cWe did continuous runs and so we would set the model at a roll angle or at a pitch angle and then continuously take data while we either pitched at a set roll angle or rolled at a set pitch angle. And so we took about seven hundred of those runs over the Mach range. The entire testing took about a month, but that wasn\u2019t all run time, it was about three weeks of actual \u2018wind on\u2019 running in the Unitary.\u201d<\/p>\n
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Credit: NASA\/Gary Banziger.<\/p>\n
(Photo Caption: 0.8 percent scale model of an SLS Block 1 Cargo configuration in the Langley Unitary Plan Wind Tunnel (UPWT) for aerodynamics testing. This model is configured with the shorter, 14-meter Delta 4 payload fairing (PLF) that would encapsulate Europa Clipper. The \u201cJupiter Direct\u201d trajectory is performance-challenging for the Block 1 vehicle and the shorter fairing saves weight over the longer, 19-meter PLF.)<\/em><\/p>\n \u201cA single run where we would pitch about twenty-four degrees just to kind of completely cover every option would take a little over a minute, [where] it was sitting at a single Mach number,\u201d she noted. The same data set would be collected in another run at another Mach number until the whole range was covered.<\/p>\n \u201cThe way that we would qualify it as is that the flight is quasi static in terms of Mach number,\u201d Jeremy Pinier, NASA\u2019s SLS Aerodynamics Team Lead at Langley, said in the interview. \u201cFrom liftoff to booster separation, that\u2019s around two minutes, so it goes from Mach zero to Mach four and a half in two minutes but that\u2019s actually pretty long and so we consider the state of the flow as quasi static.\u201d<\/p>\n \u201cSo we can go in the wind tunnel and sit at a Mach number and take data, take all the data we need at that Mach number and then go to the next Mach number, take all the data we need there and then create those databases where the GNC guys will be able to take our database and slice through this database even though in the wind tunnel we were statically sitting at a Mach number.\u201d<\/p>\n \u201cThe main data that we\u2019re collecting was force and moment data on the model,\u201d Winski noted. \u201cOn this model we did not have pressure ports, but we did [have] the pressure sensitive paint (PSP).\u201d<\/p>\n The luminescent paint provides visual data of the distribution of pressure over the model during wind tunnel testing. \u201cThere are special lights on the tunnel,\u201d Winski noted. \u201cHow much it actually causes the model to luminesce, because it\u2019s reacting with how much oxygen is in the air, is related to the pressure that it is seeing, how much light is luminescing off of it.\u201d<\/p>\n \u201cWe would have to sit at a condition for like thirty seconds or so and they would take images with the model just sitting still with conditions not changing.\u201d<\/p>\n \u201cFor this test what we actually did is we ran the model without paint for all of the force and moment testing and then once we completed the force and moment testing the model was painted for PSP,\u201d she added. \u201cIf we were to retest this model later on for force and moment we would actually remove the PSP paint before testing.\u201d<\/p>\n Credit: NASA\/David C. Bowman.<\/p>\n (Photo Caption: NASA Langley aerospace engineer Courtney Winski prepares the 0.8-percent, short-fairing Block 1 Cargo model for UPWT test runs with pressure sensitive paint. The paint luminesces under special lighting to indicate the pressure distribution over the model. A set of test runs is performed both with and without the paint.)<\/em><\/p>\n \u201cThe paint is very sensitive, we can only use it for one test,\u201d Pinier said. \u201cIt\u2019s sensitive to light, it\u2019s sensitive to oils on your hands, so if you touch the model it can damage the paint. So we paint it once for each test and then we can remove it and paint it again.\u201d<\/p>\n \u201cWhat you saw in the picture with Courtney is the traditional pressure sensitive paint, steady pressure sensitive paint,\u201d he noted. \u201cIt\u2019s a pretty mature technology, it\u2019s used in many institutions, in many labs and wind tunnels.\u201d<\/p>\n A new, unsteady pressure sensitive paint (uPSP) is still in development but may be applied to future testing. \u201cWe\u2019ve already run a few exploratory tests using the unsteady pressure sensitive paint and it\u2019s shown very promising results,\u201d Pinier noted.<\/p>\n \u201cWe\u2019re thinking at some point we\u2019ll be able to characterize the buffet environment using the unsteady pressure sensitive paint. I say at some point because it needs validation, this technology needs to be validated first.\u201d<\/p>\n Pad rollout to Boost phase aerodynamics<\/p>\n Current testing is focused on the Block 1 Cargo configuration. \u201cWe\u2019re just focusing this one right now because we\u2019ve already done a lot of testing on all the other configurations,\u201d Pinier said. \u201cThis Block 1 Cargo configuration was completely new to us when it came out and we had to start a whole testing campaign for that one specifically.\u201d<\/p>\n Credit: NASA\/LaRC.<\/p>\n (Photo Caption: NASA engineers and contractors set up for a liftoff test of a Block 1B Crew vehicle and Mobile Launcher subscale model in Langley Research Center\u2019s 14-by-22-foot subsonic wind tunnel in 2013. The tests measure wind-induced forces on the vehicle, the umbilical tower\/launch platform, and the connected pair from rollout to the pad through liftoff. Langley is getting ready to repeat the same series of tests in this wind tunnel for the new Block 1 Cargo configuration.)<\/em><\/p>\n The testing is intended to create an aerodynamic database for the vehicle configuration, from rolling out to the launch pad through liftoff, through the Boost phase of flight that goes through SRB separation and beyond. \u201cAt liftoff you\u2019ve got the ground winds that are pushing on the vehicle and the tower and those two are connected,\u201d Pinier explained. \u201cWe\u2019re really interested in the ground wind loads on the tower and the vehicle, just static loads from winds from all directions, north, south, east, west.\u201d<\/p>\n \u201cThey\u2019re also interested in when they are rolling out the vehicle on the Mobile Launcher from the Vehicle Assembly Building to the launch pad there\u2019s also ground wind environments there.\u201d<\/p>\n \u201cAt T-0 (liftoff) you\u2019re really at ninety degrees angle of attack with the wind perpendicular to the vehicle,\u201d he added. \u201cAs the vehicle accelerates that angle of attack reduces very quickly down to single digits in degrees. And so during ascent, subsonic all the way to supersonic Mach numbers we test at low angles of attack, meaning below eight degrees angle of attack. And really the vehicle is going to fly below four degrees angle of attack.\u201d<\/p>\n \u201cAs you\u2019re accelerating you go through Mach 1, you know lots of things happen around Mach 1,\u201d he continued. \u201cThe fluid dynamics around Mach 1, speed of sound, are very non-linear. The unsteady pressure environment on the vehicle is the highest and that\u2019s what creates buffet. Basically you can think of it as the air kind of shaking the vehicle structure around Mach 1.\u201d<\/p>\n \u201cThe buffet is all of the low-frequency type of shaking of the vehicle that happens around transonic Mach numbers and the aeroacoustics is all of the higher-frequency shaking that happens in this airflow as it\u2019s going over the vehicle.\u201d<\/p>\n \u201cSo you go through Mach 1, you get past peak buffet loads and then you get to maximum dynamic pressure, which is when basically the force of the air on the vehicle, the static force is the highest,\u201d he continued. \u201cYou get max dynamic pressure between Mach 1 and 2. The loads guys are mostly interested in the static loads on the vehicle during that [phase] in flight.\u201d<\/p>\n Credit: NASA\/George Homich.<\/p>\n (Photo Caption: SRB separation aerodynamic testing of the Block 1 Crew configuration in UPWT in 2014. A similar test campaign will be performed on the Block 1 Cargo configuration later.)<\/em><\/p>\n \u201cAnd then you accelerate and everything [in] the environments start to tail off. Aeroacoustics is still present but it\u2019s also tailing off.\u201d<\/p>\n \u201cSome of the things we look at as we get to higher and higher altitudes and close to booster separation is something called plume induced flow separation,\u201d he added. \u201cThe plumes of the vehicle as you\u2019ve probably seen when the rocket launches and gets to high altitude become very underexpanded, meaning they become very large and they can induce local separation of the flow on the back of the vehicle so we try to look at that at the highest Mach numbers.\u201d<\/p>\n \u201cAnd then you get to booster separation around Mach 4, Mach 5, and that\u2019s where we have to characterize that environment to make sure that the boosters don\u2019t come back and contact the Core Stage.\u201d<\/p>\n Testing to build aero database for design analysis of new vehicle configuration<\/p>\n Testing all of those regions in the early phase of flight involves wind tunnels at NASA centers across the country. \u201cWe tested at the Marshall (Space Flight Center) fourteen-inch trisonic tunnel to get some data quickly,\u201d Pinier said.<\/p>\n \u201cWe can test quickly in that tunnel and get the data for initial design cycles; however, very quickly for this one we needed mature data so where we\u2019ve got [is] we\u2019re probably in the middle of a testing campaign that comprises six large wind tunnel tests. This picture that you saw was from the test at the Langley Unitary Wind Tunnel to cover the high supersonic Mach range.\u201d<\/p>\n \u201cWe have also run a wind tunnel test at the Ames (Research Center) Unitary Plan Wind Tunnel to cover the subsonic to about Mach 2.5 range for ascent, that was a 1.3 percent scale model,\u201d he added. \u201cWe are current getting set up to run a liftoff test at the Langley fourteen by twenty-two wind tunnel to cover the liftoff phase of flight and a 1.75 percent scale model along with a 1.75 percent scale Mobile Launcher. We\u2019re trying to characterize the liftoff environment with winds from all directions and basically the entire rollout to liftoff phase of flight.\u201d<\/p>\n Credit: NASA.<\/p>\n (Photo Caption: Artist rendering of the SLS Block 1 vehicle, customized to the Block 1 Cargo configuration with the short PLF.)<\/em><\/p>\n \u201cWe\u2019re going to have a wind tunnel test this summer at the Ames Unitary Plan Wind Tunnel to characterize the aeroacoustics environment \u2014 transonic and low supersonic aeroacoustic environments,\u201d he continued. \u201cSo we\u2019re going to have a transonic buffet environment test at the TDT or Transonic Dynamics Tunnel at Langley, that\u2019s going to occur next calendar year and that\u2019s to characterize the unsteady buffet environment as the vehicle goes through the transonic Mach numbers.\u201d<\/p>\n \u201cThe sixth one is going to be a booster separation wind tunnel test at the Langley Unitary Plan Wind Tunnel and that\u2019s going to be a static 0.9 percent scale model. Those tests are pretty standard, those are critical phases of flight where we need to get that data right and so we rely heavily on wind tunnels for those critical databases.\u201d<\/p>\n \u201cFor pretty much every configuration of the Space Launch System family we\u2019ve run those tests,\u201d Pinier added. \u201cWe\u2019re just doing it all over for this particular configuration.\u201d<\/p>\n Data feeds into two areas of design analysis work<\/p>\n The database being generated for this vehicle configuration from the wind tunnel testing is used by different design groups. \u201cThere\u2019s really two customers for us \u2014 for the aerodynamics team,\u201d Pinier explained. \u201cOne of them is the trajectory and guidance navigation and control teams. They are interested in databases to cover the entire Mach range.\u201d<\/p>\n \u201cWe take force and moment data for the entire Mach range and we put it in databases, give that to them,\u201d he added. \u201cThey design trajectories, they run Monte Carlo simulations\u2026in dispersed flight conditions throughout the entire Boost phase. So that\u2019s one of the customers \u2014 integrated forces and moments go to GN&C and trajectory.\u201d<\/p>\n \u201cThe second customer is the loads team,\u201d he continued. \u201cThey\u2019re interested in the aerodynamic loading on the vehicle and in this case they are really interested in the peak loading phases of flight.\u201d<\/p>\n Credit: NASA.<\/p>\n (Photo Caption: On the left, Computational Fluid Dynamics (CFD) modeling of the Block 1 Cargo vehicle in supersonic flight. On the right, a Schlieren image of a 0.8 percent scale model of the vehicle in Langley\u2019s supersonic wind tunnel at a supersonic Mach number. The force-moment and pressure data collected in the wind tunnel tests validates and is fed back into the analytical models.)<\/em><\/p>\n \u201cSo for example, buffet. We don\u2019t have to characterize buffet throughout the entire Boost phase because we know buffet peaks around Mach 1 so we focus on transonic conditions for buffet environment.\u201d<\/p>\n \u201cAeroacoustics, we know those go a little higher than that so we characterize aeroacoustic environments all the way up to Mach two and a half and the aeroacoustics environment is also an environment that goes to the loads team.\u201d<\/p>\n \u201cSo those are the two biggest products, the aeroacoustics and the buffet, [that] go to the loads team that are kind of critical,\u201d Pinier said. \u201cA third one would be just the static loading, the distribution of the loading during ascent.\u201d<\/p>\n \u201cIt\u2019s not a driver for design, but we produce that. That comes mostly out of CFD (computational fluid dynamics), basically the distribution of the pressures over the entire vehicle as it goes through the Boost phase, but now that we have pressure sensitive paint when we\u2019re doing force-moment measurements we try to do this pressure sensitive paint measurement in order to validate the CFD.\u201d<\/p>\n Block 1 Cargo is a new config under analysis<\/p>\n The Block 1 Cargo configuration was studied earlier in the program, but more detailed design analysis began last year when the SLS option of flying the Europa Clipper spacecraft was moved back to the Block 1 vehicle as a part of Fiscal Year 2018 appropriations. SLS is still the mandated launch vehicle for Europa Clipper, but also remains a source of disagreement between the Trump Administration and Congress.<\/p>\n Congress mostly recently retained the SLS mandate in the language in Fiscal Year 2019 appropriations passed in mid-February. Although the FY 2019 appropriations were signed by the President, the Administration remains opposed to using SLS for Europa; as in past years, their Fiscal Year 2020 Budget submission that followed in mid-March continues to advocate use of U.S. commercial launch services.<\/p>\n Two other launch options on heavy-lift commercial vehicles would perform one or more gravity assist flybys past Earth and\/or Venus; the spacecraft is designed to be compatible with any of these options.<\/p>\n Credit: NASA.<\/p>\n (Photo Caption: Overall Europa Clipper mission summary and launch options from a recent presentation made by Project Manager Barry Goldstein.)<\/em><\/p>\n Congress and the Administration did reach agreement on one mandate also written into law, regarding the launch date. Previously, Congress enacted a 2022 launch mandate and the Administration proposed launch in 2025; the FY 2019 appropriations were passed with a 2023 launch target and the Administration\u2019s FY 2020 budget request supports this.<\/p>\n While the \u201cJupiter Direct\u201d launch mandate remains in place, the SLS Program continues design work on the general configuration and the specific mission, referred to as Science Mission-1 (SM-1). \u201cThis cargo configuration as you probably know is for the Europa Clipper mission and there are two potential fairings, a short one and a long one and currently the primary one we\u2019re testing is the short one,\u201d Pinier said.<\/p>\n The Block 1 vehicles use a derivative of United Launch Alliance\u2019s Delta 4 Heavy upper stage and the Delta\u2019s payload fairing system (fairing and attach fitting) would also be used to encapsulate the spacecraft in the SLS launch option. The short fairing is approximately 14 meters long, the long fairing is approximately 19 meters long.<\/p>\n \u201cIt makes a lot of sense once you\u2019re in the wind tunnel to go ahead and test several configurations, so we have done some testing on the long configuration but currently the shorter one is the priority,\u201d Pinier added.<\/p>\n Lead image credit: NASA\/Gary Banziger.<\/p>\n","protected":false},"excerpt":{"rendered":" NASA engineers at the Langley Research Center in Hampton, Virginia, recently completed one set of wind tunnel tests in a series on the aerodynamics of the newest Space Launch System (SLS) vehicle configuration. Data was collected during several hundred supersonic test runs in the Unitary Plan Wind Tunnel at Langley of a scale model of […]<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"","ping_status":"","sticky":false,"template":"","format":"standard","meta":{"_acf_changed":false,"inline_featured_image":false,"footnotes":"","_links_to":"","_links_to_target":""},"categories":[2],"tags":[1659,624],"class_list":["post-38048","post","type-post","status-publish","format-standard","hentry","category-news","tag-europa","tag-sls"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/38048"}],"collection":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/users\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/comments?post=38048"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/38048\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=38048"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=38048"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=38048"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}See Also<\/h4>\n
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The analytical models can then factor in atmospheric conditions such as winds at altitude. \u201cThose are models that the loads team have and they apply and they add those models gusts and wind shear and they add those models on top of what we give them in terms of environments,\u201d Pinier said. \u201cThere\u2019s no way to measure that in a ground test environment.\u201d<\/p>\n![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2019\/05\/EC-Options.gif\")
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