J003 - Annex B - Objectives Traceability Matrix (OTM) for SOO Goals_10APR24_V2.xlsx
XLSX spreadsheet 27 KB Posted
- Attached to
- USMA Wind Tunnel Federal contract opportunity
- Solicitation number
- W91RUS24R0025
About this file
This document is a Statement of Objectives (SOO) for a wind tunnel design and procurement contract at the United States Military Academy (USMA) in New York. The key objectives include providing a detailed design report with specifications and operational limits, ensuring compatibility with the existing building infrastructure, including a subsonic test section with model positioning and load measurement capabilities, and procuring and installing the wind tunnel system to meet the specified design requirements. The SOO outlines 18 specific requirements and 6 design attributes that the contractor must address, such as maximizing the subsonic test section dimensions and Reynolds number, incorporating safety features, and providing data acquisition and reduction software. The related federal contract opportunity is Solicitation W91RUS24R0025 issued by the Department of the Army Materiel Command Army Contracting Command Aberdeen Proving Ground.
View the file
Other files for this federal contract opportunity
Show all 16
On GovTribe
Work with this file on GovTribe
- Download the original file
- Contacts named in this file
- Similar government files
- Ask GovTribe AI about this file
Text version
Requirements
Requirement Information
| SOO OBJECTIVES FOR WIND TUNNEL DESIGN CONTRACT USMA, NY | ||||
| ID | Requirement | Location or Room Type | Capability Category | Requirement Type (Functional, Operational, Interface, Design, or Performance) |
| R1 | Provide a design report detailing the wind tunnel system design solution including design embodiment, specifications, and operational limits. | Design | ||
| R2 | The design report must include detailed dimensional drawings of all components and their interface with the existing infrastructure. | Design | ||
| R3 | The design report must include performance specifications that map to each of the contract requirements and each design attribute listed in Appendix A. These design specifications should include a target/estimated value and a minimum/maximum acceptable value. | Design | ||
| R4 | All utilities, connections, interface, mounting, or infrastructure not present or planned in the existing building infrastructure must be part of the system design including cost, permits/approval, installation, and testing. This includes an electrical transformer to connect to the electrical grid for any power requirements exceeding the CEAC building supply. | Design | ||
| R5 | Design must be compatible with the space available, building infrastructure, and meet building code requirements for the equipment location or have any modifications to infrastructure coordinated and approved through the appropriate building authority. | Interface | ||
| R6 | Designs must include safety features to relieve pressure in case of overpressurization on all presurized ducting or closed-circuit wind tunnels. | Design | ||
| R7 | Provide data reduction software capable of calculating aerodynamic coefficients (lift, drag, side force, pitch, roll, yaw), test section flow parameters (dynamic pressure, temperature, static pressure, flow velocity), pressure port data, and display results graphically. The software must be able to save data to a computer database and plot aerodynamic coefficients and pressure in near real-time during tunnel operation. | Design | ||
| R8 | Designs must have tunnel control station(s) capable of controling and monitoring all wind tunnel equipment and tunnel operation, viewing test section data and performing data reduction. | Design | ||
| R9 | Designs with a fan downstream of the test section must include a protective device to prevent debris from impacting fan in case of test model structural failure. | Design | ||
| R10 | Designs must include laser safety devices including laser safe blackout curtains and laser safety/alert signage for any rooms designed to have lasers in operation. | Design | ||
| R11 | Designs must include a subsonic test section with a minimum minor axis of 2 feet. | Design | ||
| R12 | Designs for the subsonic test section must include a model positioning system and load measurement capability. Minimum threshold is 2-axis motion and 3 component load measurement (normal, axial, pitching moment). | Design | ||
| R13 | Wind tunnel systems must have a data acquisition system capable of receiving, signal conditioning, synchronizing by time, and saving all test section measurement data (electrical signal and pressure) at a rate no less than 200hz. | Design | ||
| R14 | Procure and install wind tunnel system in accordance with accepted/approved design report. | CEAC Room EC-246 | Procurement | |
| R15 | Conduct operational checks on all system components after installation. | CEAC Room EC-246 | Procurement | |
| R16 | Demonstrate all design specifications listed in the design report are within acceptable limits. | CEAC Room EC-246 | Procurement | |
| R17 | Provide a training plan and conduct training in accordance with training plan for USMA personnel on the operation, maintenance, safety procedures for the wind tunnel system | Procurement | ||
| R18 | Provide documentation for wind tunnel equipment including operator's manuals, maintenance manuals with recommended mainteance schedules, emergency procedures for tunnel operation, and data reduction software user manuals. | Procurement |
Design Attributes
| SOO DESIGN TRADE-OFFS FOR WIND TUNNEL CONTRACT USMA, NY | |||||
| ID | Condition | SOO Objectives/Use cases | Location or Room Type | Capability Category | 1 = Highest Importance, 10 = Lowest Importance |
| A1 | Maximize subsonic test section chord Reynolds Number at Mach < 0.4 for airfoils. Goal is to achieve values of at least 250,000, minimum threshold is 125,000. | 1a, 1f, 1g, 1h, 1i, 2a, 2d, 3a, 3b, 3c, 3d, 3f, 3g, 3j, 4g, 4l | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A2 | Maximize chord Reynolds Numbers on aircraft/wing-body models spanning no more than 80% of test section width with wing aspect ratios of no less than 7.5. Goal is values of at least 150,000, minimum threshold is 75,000. | 1b, 1h, 1j, 2b, 2c, 2e, 2h, 2i, 2j, 2l, 3b, 4a, 4c, 4d, 4e, 4l, 4m, 4n | CEAC Room EC-246 | Subsonic Test Section | 2 |
| A3 | Maximize the subsonic test section dimensions, with a minimum minor axis of no less than 2 feet. Goal is a test section minor axis of 3 feet or larger. | 1a, 1b, 1f, 1g, 1h, 1i, 1j,2a, 2b, 2c, 2d, 2e, 2h, 2i, 2j, 2l, 3a, 3b,3c, 3d, 3f, 3g, 3j, 4a, 4c, 4d, 4e, 4g, 4l, 4m, 4n | CEAC Room EC-246 | Subsonic Test Section | 2 |
| A4 | Subsonic test section should be rectangular, filleted rectangular, or octagonal and allow for mounting of test articles or mounting points on test section walls. | 1f, 3d, 3f, 3g, 3h, 3i, 3j, 4g, 4h, 4i, 4j, 4k | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A5 | Continuously variable tunnel speed for subsonic test section up to operational limits. | 1a, 1f, 1g, 1h, 1i, 2a, 2d, 3a, 3b, 3c, 3d, 3f, 3g, 3j, 4g, 4l | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A6 | Include an internal strain-gauge balance with load limits appropriate for low-speed test section size and ability to mount the internal balance to the model positioning system. The internal balance shall include a calibration report and calibration matrix. Desired is a 6-component balance with accuracy <0.2% full-scale, threshold is a 3 component balance with accuracy <0.5% full-scale. | same as req 16 & 17 | CEAC Room EC-246 | Subsonic DAQ | 2 |
| A7 | Maximize range of Model Positioning System (MPS) motion up to +30/-15 deg pitch, +/- 180 deg roll, +/- 20 deg yaw while maintaining model balance moment center location. | same as req 16 & 17 | CEAC Room EC-246 | Subsonic DAQ | 3 |
| A8 | Maximize automation of tunnel speed, MPS positioning, and data acquisition system data recording so that that one-factor-at-a-time (OFAT) test runs may be programmed and executed without manual selection of each set condition. | same as req 16 & 17 | CEAC Room EC-246 | Subsonic DAQ | 3 |
| A9 | Include traversing mechanism (TM) on the downstream end of the test section capable of holding a probe and traversing a maximum amount of the test section width and height. | 1g, 1l, 1p, 3a, 4i | CEAC Room EC-246 | Subsonic Test Section | 2 |
| A10 | External balance capable of measuring forces and moments in the wind reference frame. Load limits must be appropriate to test section size. External balance should include struts and fairings for model mounting, and allow for model attitude adjustments in pitch and yaw. Data Aquisition software should be capable of conducting a Tare & Interference test. Desired accuracy is <0.2%, minimum threshold for load accuracy is <0.5%. | 1n, 3c, 3f, 4g, 4n | CEAC Room EC-246 | Subsonic Test Section | 5 |
| A11 | Include a model NACA 2412 airfoil or finite wing and capability to measure lift, drag, and pitching moment. | 1a, 1f, 1g, 1h, 1i, 1q, 2a, 2d, 3a | CEAC Room EC-246 | Subsonic Test Models | 1 |
| A12 | Include a model Cessna 206 capable of being mounted to the MPS/Internal Balance and spanning no more than 80% of the test section width. Desired construction should allow for a drag build-down separate removal of landing gear, empennage, struts, and wing during test. | 1b, 1h, 1j, 2b | CEAC Room EC-246 | Subsonic Test Models | 4 |
| A13 | Include test models of the following aerodynamic shapes, capable of being mounted to the MPS/Internal Balance: Circular flat plate, sphere, forward facing semi-spherical cup, backward facing semi-spherical cup, teardrop. | 1g, 3b | CEAC Room EC-246 | Subsonic Test Models | 2 |
| A14 | Include subsonic wing-body check model, demonstrate drag polar accuracy within 5% of another wind tunnel at maximum Reynold's Number and across a lift coefficient range from -0.1 through 0.6, demonstrate repeatability within 1% for a minimum of 5 separate runs. | Same as req 26 | CEAC Room EC-246 | Subsonic Test Models | 10 |
| A15 | Include pressure reading capability in DAQ system, including scani-valve or multiple pressure port measurements for reading 20 or more pressure ports. Include ability to view pressure data in a format similar to a manometer bank. | 1c, 1d, 1f, 1p, 2d, 3b, | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A16 | Include a pitot-static tube capable of being mounted to the Traversing Mechanism and/or the MPS. | 1c, 1l, 1p | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A17 | Include a multi-hole pitot-static probe capable of being mounted to the Traversing Mechanism and/or the MPS and measuring flow angularity | 1c | CEAC Room EC-246 | Subsonic Test Section | 3 |
| A18 | Include a wake-rake with >= 7 pressure probes capable of being mounted to the Traversing Mechanism. | 1g, 1p, 3a, | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A19 | Include a flat plate and pressure rake capable of measuring boundary layers profiles | 1k, 3d | CEAC Room EC-246 | Subsonic Test Section | 2 |
| A20 | Include hotwire anemometer system for use in subsonic test section and ability to calculate flow velocity in the data acquisition system from hotwire measurements. | same as req 34 | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A21 | Include a smoke wand for flow visualization with capability of moving the wand ahead of a model during wind tunnel operation. | 1h, 1j, 1o, 1q, 2f, 3d, 3h, 4i | CEAC Room EC-246 | Subsonic Test Section | 2 |
| A22 | Minimize test section flow turbulence intensity and maximize flow uniformity. Desired performance is flow turbulence intensity <=0.5% measured at test section entrance, spatial flow variation is <=5%, and flow angularity is <=0.5deg at all test section locations. | Supports all uses | CEAC Room EC-246 | Subsonic Test Section | 1 |
| A23 | Minimize noise level while subsonic wind tunnel is in operation. Desire is to be less than 70 dB or able to operate the tunnel at the lower range of test section speeds while talking and teaching in the room. | Supports all uses | CEAC Room EC-246 | Subsonic Test Section | 4 |
| A24 | Include air supply system including compressor, air storage, conditioning equipment (air drying/heating), and ducting to start and operate supersonic test sections. Air supply must provide 60 minutes of continuous conditioned dry air at >= 1kg/s mass flow rate and >= 125psi. | 1r, 1s, 4o | Compressor Pad | Supersonic Test Section | 7 |
| A25 | Design the ability to connect Stanford Mach 2 test section to air supply system and diffuser, start, and operate continuously at >=Mach 2 without water vapor condensation or air liquification. | 1r, 1s, 4o | CEAC Room EC-246 | Supersonic Test Section | 7 |
| A26 | Design additional high pressure supply line air connections with flow control valves, regulators, and connection flanges to allow for future installation of additional supersonic test sections. | 1r, 1s, 4o | CEAC Room EC-246 | Supersonic Test Section | 10 |
| A27 | Provide a variable Mach number transonic/supersonic nozzle, test section, and diffuser that maximizes the Mach number range and test section operation time. Desired operation time is greater than 30 seconds across a Mach number range of 1.5-3. | 1r, 1s, 4o | CEAC Room EC-246 | Supersonic Test Section | 9 |
| A28 | Include a supersonic test section model positioning system and ability to measure 3-component aerodynamic loads. | 1r, 1s, 4o | CEAC Room EC-246 | Supersonic Test Section | 9 |
| A29 | Include Schlieren imaging system and Faucault tester capable of recording images and video. | 1r | CEAC Room EC-246 | Supersonic Test Section | 7 |
| A30 | Include PIV seeding capability supersonic tunnels to include appropriate disposal of seed on the exhaust end. Seeding capability includes appropriate pressure source to ensure seed may be injected at all potential operating conditions and at a Stokes Number <= 0.1 | 1o, 2f, 3d | CEAC Room EC-246 | Supersonic Test Section | 10 |
| A31 | Include a complete Particle Image Velocimetry (PIV) system. Desired system includes (1) double-pulsed Nd:YAG laser, 532 nm wavelength, 200 mJ/pulse, 15 Hz repetition rate (2) hi resolution camera of at least 24 megapixel resolution, 12 bit pixel depth, greater than 15 frames per second, and with computer interface card (framegrabber), (3) synchronizer with at least 250 picosecond resolution, (4) PIV software for two-dimensional, two-component velocity measurements, (5) hi-performance PC for data processing and storage, (6) laser sheet forming optics for sheet thicknesses from 0.5 mm to 2 mm at focal lengths of 300 mm to 2 m, and widths of up to 30 cm, (7) camera optics including 100 mm camera lens and 532 nm band pass filter for imaging under ambient light conditions, (8) installation, training, and set-up by a manufacturer representative | 1o, 2f, 3d | CEAC Room EC-246 | Supersonic Test Section | 10 |
| A32 | Include hotwire anemometer system capable of use in supersonic test section | 1k | CEAC Room EC-246 | Supersonic Test Section | 9 |
| A33 | Minimize noise level while supersonic wind tunnel system is in operation. Desire is to have noise levels in adjacent rooms outside the EC-236 soundproofing enclosure less than 60 dB while in operation. | 1k | CEAC Room EC-246 | Supersonic Test Section | 9 |
File details come from the government source that posted it. Updated .