2013 Test Results -> Updates Coming @Oshkosh2016!

A Columbia 300, N190LC, was tested to establish baseline performance in cruise and climb. This basic performance evaluation also included a measurement of stall speed with a swivel head pilot static boom.

The Lam Aero System permitted a new wing for the same N190LC Columbia that was tested in an analogous fashion after modification. Each test point was repeated using the same methods and instruments as was done on the stock aircraft.

Cruise Speed Comparison at Equivalent Power Settings

Fuel Flow Comparison

A very interesting alternative to focusing on a cruise speed increase is to compare fuel flows at equal speeds for various altitudes:

  • At 7000 FT, a comparison shows fuel flow savings of 3.9 gallons per hour at 170 KTAS (26.7% savings).
  • At 12,000 FT, a similar comparison is a savings of 4.3 gallons per hour at 180 KTAS for the Lam modification compared to 178 KTAS for the stock aircraft (27.2% savings).
  • At 17,000 FT, another comparison is a savings of 2.6 gallons per hour at 168 KTAS for the Lam modification compared to 166 KTAS for the stock aircraft (21.8% savings).

Cruise Performance Comparison Equivalent Power Settings

KIAS corrected for position error (~ minus 2 knots) for KCAS used for calculating KTAS

The tabulated data above shows that the cruise speed has increased by as much as 16 KTAS for the given altitude, MAP, RPM, and GPH points.

Climb Performance Comparison


The above figure gives a graphical representation of the rate of climb increase demonstrated by the Lam wing as compared to the stock wing. In addition to this, the aircraft feels much more solid and climbs much better at high altitudes. The stock aircraft is quite good at reaching 17,000 FT, but the modified aircraft is much better in all ways at this altitude.

Flight Characteristics


The Lam Aero System fitted to this aircraft has improved lateral control power in the landing configuration. The ailerons are lighter at high speeds as compared to the stock aircraft. The feel of the lateral control system is quite “conventional.”

The aircraft is much more longitudinally stable. The Columbia 300 could benefit from a more aft CG range or a reduction in horizontal stabilizer size. A smaller horizontal stabilizer would allow for a further weight and drag reduction and resulting performance increase.

One area that has not been investigated is spinning behavior. It is believed that simultaneous deployment of the Lam flaps and ailerons will destroy the wing’s autorotation in a spin. This ability points towards a possible auto spin recovery feature.