Bump Elliott, Marlene Dietrich, Bob Chappuis; Bruce Hilkene, UM Football

[Taken on studio tour prior to 1948 Rose Bowl game.]

Bump Elliott, UM Football, vs USC in 1948 Rose Bowl

[Elliott received jump-pass from Chappuis for a first down]

Four UM Football coaches: Bump Elliott, Bo Schembechler, Gary Moeller, Lloyd Carr, 1994, at 125th Year Football Reunion

[jpeg file from Athletic Dept. Photo taken at 125th All-Time football Reunion]

Bump Elliott, UM Football, named new head coach, 1958

[attached wire service caption dated Nov. 14, 1958]

UM Football, 1971 Seniors recruited by Bump Elliott, at Rose Bowl

Top Row: Tom Darden, Jim Brandstatter, Fred Grambau, Mike Oldham, Mike Taylor, Tom Beckman, Paul Seymour, Scott Hulke, Reggie McKenzie, Glenn Doughty, Butch Carpenter

Middle Row: Bruce Elliott, Dave Zucareli, Fritz Seyferth, Guy Murdock,

Front Row: Billy Taylor, Dana Coin, Bump Elliott, Mike Keller, Frank Gusich.

Pete Elliott with 12-letter winner blanket

[left Bump Elliott, right Pete Elliott]

Active flow control bump design using hybrid Nash-game coupled to evolutionary algorithms

In this paper, the optimal design of an active flow control device; Shock Control Bump (SCB) on suction and pressure sides of transonic aerofoil to reduce transonic total drag is investigated. Two optimisation test cases are conducted using different advanced Evolutionary Algorithms (EAs); the first optimiser is the Hierarchical Asynchronous Parallel Evolutionary Algorithm (HAPMOEA) based on canonical Evolutionary Strategies (ES). The second optimiser is the HAPMOEA is hybridised with one of well-known Game Strategies; Nash-Game. Numerical results show that SCB significantly reduces the drag by 30% when compared to the baseline design. In addition, the use of a Nash-Game strategy as a pre-conditioner of global control saves computational cost up to 90% when compared to the first optimiser HAPMOEA.

Shock control bump design optimization on Natural Laminar Aerofoil

The chapter investigates Shock Control Bumps (SCB) on a Natural Laminar Flow (NLF) aerofoil; RAE 5243 for Active Flow Control (AFC). A SCB approach is used to decelerate supersonic flow on the suction/pressure sides of transonic aerofoil that leads delaying shock occurrence or weakening of shock strength. Such an AFC technique reduces significantly the total drag at transonic speeds. This chapter considers the SCB shape design optimisation at two boundary layer transition positions (0 and 45%) using an Euler software coupled with viscous boundary layer effects and robust Evolutionary Algorithms (EAs). The optimisation method is based on a canonical Evolution Strategy (ES) algorithm and incorporates the concepts of hierarchical topology and parallel asynchronous evaluation of candidate solution. Two test cases are considered with numerical experiments; the first test deals with a transition point occurring at the leading edge and the transition point is fixed at 45% of wing chord in the second test. Numerical results are presented and it is demonstrated that an optimal SCB design can be found to significantly reduce transonic wave drag and improves lift on drag (L/D) value when compared to the baseline aerofoil design.