High-Reynolds Number Circulation Control Testing in the National Transonic Facility (invited)

Transonic Drag Reduction Through Trailing-Edge Blowing on the FAST-MAC Circulation Control Model

“…The Fundamental Aerodynamics Subsonic/Transonic-Modular Active Control (FAST-MAC) model was again used to test circulation control concepts at realistic flight Reynolds numbers at transonic cruise conditions, building upon the successes and lessons learned of the first two test entries (NTF Tests 195 and 213). 16 The FAST-MAC model has a super-critical wing and represents an advanced configuration that is characteristic of modern aircraft. The geometry and results of the high Reynolds number tests in the NTF can be openly distributed to the research community to aid in CFD validation.…”

High-Reynolds Number Active Blowing Semi-Span Force Measurement System Development

“…This model was used to characterize a circulation control blowing concept that focused on a high-speed jet that blows over the flap region of the wing. The performance results of the FAST-MAC model are described 14 , and the highlighted issues with the blowing characteristics are shown in Figure 12. The cruise performance that is highlighted in the pressure profile data shown in Figure 13 indicates an improvement in drag characteristics for different blowing levels by reattaching the boundary layer and moving the shock aft on the wing.…”

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

“…Whereas it is possible for changes in plenum temperature to create run-torun slot height differences, they are unexpected as Milholen noted [12]. Thermal effects in the slot flow were not observed during calibration.…”

“…Collins [10] and Lin [11] completed a 3-D test of a full-span, hybrid wing STOL model with blown flaps. Most recently, Milholen [12] documents the testing of a semi-span model with trailing edge blowing; the model is intended to test circulation control concepts at realistic flight Reynolds numbers for both low speed and transonic cruise conditions.…”

“…Recall the discussion related to Figure 3.4 for the lift curve at these conditions. The region at low C µ where the increase in C L with each increment of blowing is the highest is referred to as the separation control region [12].…”