"" title: design, analysis, and fabrication of conventional and krueger slat models -model#1: main element airfoil#1 with conventional slat. The first main-element with slat model shall follow the…

This federal contract award, valued at $173,950.00, was issued by the National Aeronautics and Space Administration (NASA) Langley Research Center to Advanced Technologies, Inc., a small business aerospace engineering company based in Newport News, Virginia. The contract is for the design, analysis, and fabrication of two wind tunnel models - a main element airfoil with a conventional slat, and a main element airfoil with a Krueger slat. The models will be used to support NASA's aeronautics research and are part of the Reliance Consolidated Models IV (RECOM IV) multiple-award indefinite-delivery/indefinite-quantity (IDIQ) contract. Advanced Technologies has also been awarded a separate blanket purchase agreement (BPA) for general and precision machining/fabrication services with NASA Langley Research Center.

"" title: design, analysis, and fabrication of conventional and krueger slat models -model#1: main element airfoil#1 with conventional slat. The first main-element with slat model shall follow the provided profile geometry of the 30P30N configuration. The equivalent stowed chord of model#1 shall be 16.751 . The main element (2-dimensional) shall have a span of 36 . The main element shall be secured to the quiet flow facility test section side walls using an existing brace and adaptor device (see drawing # 1079347 1-e-1 and # 1079357 1-d-1). This brace and adaptor device is also used to set the main element angle of attack. The conventional slat model (2-dimensional) shall have a 36 span. The position of the conventional slat with respect to the main element airfoil shall be adjustable. If cost efficient the position of the slat may be set with an existing pair of slat brackets (see drawing# 1075230). A characteristic slat design (not the correct OML, but overall correct size) that was previously used with the latter slat brackets is shown in drawing# 1075229. The final OML of the desired conventional slat is to be determined, but will be similar to the provided geometry; thus modifications are being considered which will thicken and smooth the inner cove region of the slat compared to that provided. At a minimum the thin edges of the provided geometry will be thickened to ensure structural integrity. The slat design shall be evaluated for structural integrity and instrumentation installation. As necessary, the slat OML shall be thickened on the cove portion of the slat to accommodate the installation of pressure taps and unsteady surface pressure sensors, as well as achieve reasonable thickness for machining purposes. The slat shall be instrumented with 5 unsteady surface pressure sensors distributed in the mid-span region of the slat and 20 pressure taps distributed in a chordwise row near the slat mid-span. The main element of airfoil#1 shall be instrumented with 5 unsteady surface pressure sensors distributed in the mid-span/ leading edge region of the airfoil. The main element of airfoil #1 shall have 40 pressure taps distributed in a chordwise row near the airfoil mid-span, and eight additional pressure taps located at -span and -span on the suction and pressure sides of the main element. The main element of airfoil #1 shall have a total of 48 steady pressure taps. The unsteady surface pressure sensors shall be kulite sensors that will be government furnished. The main element model and slat model shall include a mounting scheme for simplified slat brackets at the model center span, connecting the main element and slat. The bracket(s) shall be non-structural, included as noise generation mechanisms. The bracket designs are not complete. The brackets are part of the statement of work, although do not require holding to the delivery date of the rest of the model hardware. The mounting scheme shall allow for a flush surface finish when no bracket is used. The surface finish for the new hardware shall be at least 32 -inches and have a surface contour tolerance of 0.003. The trailing edges of the slat and main element model shall have a thickness of 20 thousandths of an inch with a tolerance of 0.003. Model#2: main element airfoil#2 with krueger slat the second main element with slat model shall follow a profile geometry to be determined, with a krueger slat instead of a conventional slat. Overall dimensions match those of model#1, although the details of the slat geometry and leading portion of the main element shall differ. This means the equivalent stowed chord of model#2 shall also be 16.751 . The main element (2-dimensional) shall have a span of 36 . IT shall have a krueger cavity machined out of the main element. The main element shall be secured to the quiet flow facility test section side walls using an existing brace and adaptor device (see DR