The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $71,000 - Saturday the 1st of December 2012
  National Aeronautics And Space Administration
  ARMSTRONG FLIGHT RESEARCH CENTER
  IGF::OT::IGF OTHER FUNCTIONS: THE DESIGN AND MANUFACTURE OF AN ULTRA-HIGH EFFICIENCY PROPELLER FOR AN ELECTRIC AIRCRAFT TEST BED THE SCOPE OF THE STTR PHASE III WORK IS TO FURTHER INVESTIGATE THE WORK PERFORMED ON THE ABOVE STTR BY EXPLORING ALTERNATIVE PROPELLER DESIGNS AIMED AT INCREASING EFFICIENCY AND REDUCING THE NOISE OF THE PROPELLER AS A RESULT OF TIP VORTEX SHEDDING. THE CONTRACTOR WILL DESIGN AND MANUFACTURE A HIGH EFFICIENCY PROPELLER TO IMPROVE THE PERFORMANCE OF ELECTRIC PROPULSION.

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• $31,060 - Wednesday the 2nd of May 2012
  Department Of Navy
  NAVSUP FLT LOG CTR NORFOLK
  UNIVERSITY DESKTOP WATER TUNNEL

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• $165,000 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  LANGLEY RESEARCH CENTER
  IGF::OT::IGF "OTHER FUNCTIONS" THE CONTRACTOR SHALL CONSTRUCT A WATER-TUNNEL MODEL OF THE NASA HYBRID-WING BODY CONFIGURATION BASED ON GEOMETRY INFORMATION PROVIDED BY NASA LARC. THE MODEL SHALL BE SUITABLE FOR STATIC AND DYNAMIC TESTING WITH FORCE AND MOMENT MEASUREMENTS AND FOR FLOW VISUALIZATION EXPERIMENTS. THE CONTRACTOR SHALL CONDUCT A SERIES OF STATIC AND DYNAMIC WATER TUNNEL EXPERIMENTS TO INVESTIGATE STABILITY CHARACTERISTICS OF THIS VEHICLE. IN PARTICULAR, DAMPING CHARACTERISTICS AND UNSTEADY AERODYNAMIC BEHAVIORS OF THE NASA HYBRID-WING BODY MODEL SHALL BE INVESTIGATED. STATIC AND DYNAMIC MEASUREMENTS SHALL BE RECORDED COVERING A LARGE ENVELOPE OF ANGLE OF ATTACK AND SIDESLIP. FOR THE STATIC SERIES OF EXPERIMENTS, THE TEST GRID SHALL USE ONE-DEGREE INCREMENTS IN BOTH ANGLE OF ATTACK AND SIDESLIP. THE MAXIMUM RANGE OF THESE TWO VARIABLES WILL BE DETERMINED BY THE NASA LARC CONTRACTING OFFICER S TECHNICAL REPRESENTATIVE (COTR) AND PHYSICAL LIMITATIONS PRESENTED BY THE MODEL AND WATER TUNNEL COMBINATION. HOWEVER, THE MAXIMUM RANGES DURING ALL EXPERIMENTS SHALL COVER THE LINEAR CONDITIONS BEFORE STALL AND NONLINEAR CONDITIONS DURING AND AFTER STALL. FOR DYNAMIC TESTS, A LIMITED NUMBER OF SCREENING TESTS WILL BE USED BY THE NASA LARC COTR TO IDENTIFY LOCATIONS FOR NONLINEAR OR UNSTEADY BEHAVIORS OVER THE SAME ENVELOPE COVERED IN STATIC TESTING (WITHIN PHYSICAL LIMITATIONS OF THE FACILITY). ONCE IDENTIFIED, THESE REGIONS SHALL BE INVESTIGATED USING ONE DEGREE INCREMENTS IN ANGLE OF ATTACK AND THREE SIDESLIP VALUES INCLUDING ZERO. FORCE AND MOMENT TIME HISTORIES SHALL BE RECORDED DURING SMALL AND LARGE AMPLITUDE FORCED OSCILLATIONS. A MINIMUM OF THREE AMPLITUDES WILL BE SPECIFIED BY THE NASA LARC COTR BASED ON DYNAMIC SCREENING EXPERIMENTS. ONLY ONE OF THE THREE AMPLITUDES SHALL BE SUFFICIENTLY SMALL TO ENSURE LINEAR AERODYNAMIC RESPONSES BUT STILL PRESENT SUFFICIENTLY HIGH SIGNAL-TO-NOISE RATIO FOR SYSTEM IDENTIFICATION OF THE MATHEMATICAL MODELS. FORCED OSCILLATIONS SHALL BE GENERATED PRIMARILY BY SINGLE SINE WAVES AND BROADBAND INPUTS. BROADBAND INPUTS WILL BE DEFINED BY THE NASA LARC COTR. TESTS USING RAMPS AND CONING SHALL BE PERFORMED FOR MODEL VALIDATION. EXPERIMENTAL INPUTS WILL BE DESIGNED AND APPROVED BY THE NASA LARC COTR.

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