LOADING...
Text Size
NASA Dryden Past Projects: F-16XL Ship #2 Supersonic Laminar Flow Control
August 14, 2009
 

F-16XL Ship #2 first flightF-16XL Ship #2 first flight. Project Summary

Two F-16XL aircraft were used by the Dryden Flight Research Center, Edwards, CA, in a NASA-wide program to improve laminar airflow on aircraft flying at sustained supersonic speeds. It was the first program to look at laminar flow on swept wings at speeds representative of those at which a high speed civil transport might fly.

The initial research phase of the program at Dryden was flown in a single-seat F-16XL-1. The aircraft at Dryden subsequently used for the supersonic laminar flow program was the two-seat F-16XL-2, identical to its sistership except for the cockpit configuration.

The two aircraft are the only F-16XL's built and were used by NASA because the unique delta wing design is representative of the type of wing that will probably be used on future supersonic cruise aircraft.

Project Background

A certain amount of air turbulence occurs on the surface of most aircraft wings, regardless of the shape and size of the wing. As air moves across an airfoil, it is changed by the frictional force between it and the airfoil's surface from a laminar (smooth) flow at the forward area to a more turbulent flow toward the trailing edge. The "perfect" wing would demonstrate laminar airflow across the entire surface of the wing, with no sign of turbulence. This turbulence affects flying performance by increasing aerodynamic drag and fuel consumption.

Much laminar flow research is carried out with two basic types of experimental devices – active and passive – that are attached to the research aircraft's wing. These devices are commonly called "gloves."

Active test sections contain tiny holes or slots through which most of the turbulent layer of air is siphoned off by an internal suction system built into the wing. This decreases drag and enhances aerodynamic lift by either eliminating the turbulent airflow or reducing its effect.

Passive experimental devices also attach to or become a part of the research aircraft's wing, but do not use a suction system to remove the turbulent air. Through careful contouring of the wing's surface, some laminar flow can be achieved naturally. Both types of laminar flow devices obtain data from sensors and other instrumentation built into or attached to the wing to measure airflow characteristics (especially the region of transition from laminar to turbulent flow) and pressure distribution.

Flight Research

The initial flight test phase of the Dryden Supersonic Laminar Flow Control project (SLFC) examined the performance of an active experimental wing section on the upper surface of the left wing of the single-seat F-16XL-1. The 1991-1992 tests showed that with active laminar flow control, the aircraft achieved laminar flow over a significant portion of the wing during supersonic flight, although it did not obtain laminar flow on the active glove at the design point of Mach 1.6 (1.6 times the speed of sound) at 44,000 ft. The experimental glove with active (perforated titanium) and passive sections was designed by Rockwell International's North American Aircraft Division, El Segundo, CA (now a division of Boeing).

Dryden then used the two-seat F-16XL-2 to conduct a more comprehensive research effort, consisting of two phases. The first phase used a passive glove on the right wing to obtain baseline configuration data that served in the design of the active glove, which was installed over a portion of the left wing. This effort was far more comprehensive than the initial flight phase, and explored regions of transition and the maximum extent of laminar flow obtained over a wider range of supersonic Mach numbers.

The glove covered about 75 percent of the upper wing surface and 60 percent of the wing's leading edge. It was designed by a NASA and contractor team which included the Langley Research Center, Dryden, Rockwell International, Boeing, and McDonnell Douglas. It featured a titanium suction panel and a foam-and-fiberglass passive fairing. The device was instrumented to measure laminar flow and other variables such as surface imperfections and the acoustic environment that may affect laminar flow at various flight conditions.

The metal surface of the experimental wing panel was perforated with about 10 million nearly microscopic laser-cut holes. Through the tiny holes, a suction system embedded in the wing drew off a very small portion of the boundary layer of air just above the wing's surface, thereby expanding the laminar flow across the wing. The flight engineer used a control panel located in the aft cockpit of the airplane to fine-tune the amount of airflow sucked through the holes. This procedure permitted investigation of the effect of suction volume on the area distribution of laminar flow. Researchers believe that laminar flow conditions can reduce aerodynamic drag (friction) and help reduce operating costs by reducing fuel consumption.

The project flew the F-16XL-2 45 times between Oct.13, 1995, and Nov. 26, 1996, obtaining significant amounts of valuable flight research data. NASA research pilot Dana Purifoy flew 38 of the missions, with NASA research pilot Mark Stucky flying the other 7. During the flights, there were few problems with the experimental suction hardware.

Project Management

The F-16XL flight project office was located at the NASA Dryden Flight Research Center, Edwards, CA. The NASA Langley Research Center, developed and coordinated F-16XL experiments. Project managers at Dryden were Marta Bohn-Meyer and Carol Reukauf.

Aircraft Specifications

  • The F-16XL aircraft were built by General Dynamics Corp., at Ft. Worth, TX, as prototypes for a derivative fighter evaluation program conducted by the U. S. Air Force between 1982 and 1985.
  • The aircraft were developed from basic F-16 airframes, with the most notable difference being the delta (cranked arrow) wing, which give the aircraft a greater range because of increased fuel capacity in the wing tanks and a larger load capability due to increased wing area.
  • Crew size: F-16XL-2, used in the second phase of the laminar flow project, has a two-seat cockpit.
  • F-16XL-1, used in the 1991-1992 tests, is a single-seat aircraft.
  • Size: Length, 54.2 ft (16.52 m); wingspan, 34.3 ft (10.45 m); height at vertical tail, 17.7 ft (5.39 m).
  • Max. weight: 48,000 lb (17,915.60 kg)
  • Engines: The two-seat aircraft at NASA Dryden has a General Electric F110-GE-129 engine (with afterburner) rated at 29,000 lb thrust. The single-seat F-16XL is powered by a Pratt and Whitney 100-PW-100 engine (with afterburner), rated at 23,830 lb thrust.
  • Controls: Both aircraft featured an analog fly-by-wire electronic flight control system during the laminar flow research. The single-seat aircraft now has a digital flight control system.
  • Wing construction: The delta (cranked arrow) wings on both aircraft are manufactured of advanced graphite composites to provide strength for high wing loads during flight.
  • Design load: Baseline F-16XL: 9 "Gs". Modified F-16XL: 3 "Gs") Maximum Speed: F-16XL-2, Mach 2 (approx. 1,400 mph) (2,253 k/hr); F-16XL-1, Mach 1.8 (approx. 1,260 mph)
  • Range: Over 2,500 nautical miles (4,630 k), without in-flight refueling, and unlimited with in-flight refueling.

Fact Sheet         Photos

Image Token: 
[image-47]
Image Token: 
[image-62]
Image Token: 
[image-73]
Page Last Updated: February 9th, 2014
Page Editor: Yvonne Gibbs