Test Results

Supero Test Results

There have been many tests and trials over the more than 30-years of development of the Internal Wing Aircraft (IWA) technology. Here we will do as we did with our patents governing the technology: show you the results of the earliest and the latest tests. Plus a little more.

First wind-tunnel and aeronautical lab testing: 1980

Place: University of Oklahoma, Norman, Oklahoma.

Testing supervisor: Dr. Edward F. Blick, Professor of Aerospace, Mechanical and Nuclear Engineering.

Assisting: Terry F. Reddout, Aeronautical Engineer, Lear Jet Corporation, Tuscon, Arizona.

Here is Dr. Blick’s letter of May 8, 1980, giving an overview of test results:

Letter, Dr. Edward Blick

Letter, Dr. Edward Blick

And here is the report itself, dated June 2, 1980, starting with a quote of the entire Summary paragraph:


The IWA wing was found to produce 20.7 lbf [pound-force] of lift during a test on May 7, 1980. The horsepower in the air was found to be equal to 0.7 hp. The lift/horsepower ratio was computed to be 29.6 lbf/hp. This static lift/horsepower ratio puts the IWA wing in the same class as helicopter static lift/horsepower ratios.“

Click to download a PDF of the complete report:

Engineering Report on the Theory and Test of the Static Lift of the IWA Wing


Testing and academic research: 2008

Place: University of Oklahoma, Norman, Oklahoma

Testing supervisor: Brian Zabovnik, Ph.D. candidate, aeronautics.

And the amazing (to some) or simply corroborative (to others) results…

Computational Fluid Dynamics (CFD) Results (.xls file)

Optimization of the Internal Wing Aircraft (PDF)

Final Presentation, IWA (PDF)



X Wing

X-Wing Internal Wing Aircraft (IWA)

Some graphics gathered from various wind-tunnel and CFD tests over the years…

First, some pressure gradients:

IWA wing pressures

IWA wing pressure gradients

Note the very high pressures under the leading wing – lift – and the low pressure above: more lift.

Next, some flow-related pressures:

IWA Coanda Vortex

IWA Coanda Vortex

Note particularly the airflow coming from above – lift – and the dense air going out the back of the IWA wings – velocity (from F=(ma)). Buoyancy + acceleration.

And finally, for the moment, some CFD of IWA TD1 aircraft.

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