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Sinha Deturbulator Progress Reports

Progress Articles
9/17/2003 First successful test of Sinha deturbulator on a glider
10/18/2003 Further drag reductions on Standard Cirrus wing
  Baseline polar for performance testing
2/8/2004 Progress Report: SSA Convention in Atlanta
2/28/2004 First outer-span test
5/27/2004 Wind tunnel goes into operation
8/31/2004 Stereolithography used for wind tunnel wing sections
12/3/2004 First success on upper surface of Standard Cirrus wing
12/12/2004 More success on upper surface of Standard Cirrus wing
2/18/2005 First Sink-Rate Measurement
(revised 3/13/2005)
2/26/2005 Second Sink-Rate Measurement: Some Encouraging Data
3/19/2005 First Parallel Flight - vs. ASW-28
3/19/2005 Measurements with Full Top Surface Deturbulation
9/12/2005 A Performance Endurance Issue
10/29/2005 It’s Deturbulation Time Again
1/9/2006 Paper Presented at AAIA Annual Conference
2/3/2006 Talk Presented at SSA Annual Convention
5/6/2006 Paper Presented at AAIA Flow Control Conference
7/1/2006 Notes on Endurance and the Temperature/Humidity Issue
10/21/2006 Measurements Show 20% Improvement!
(revised 1/3/07)
12/13/2006 Deturbulator Performance Confirmed!
1/2/2007 Calibrated Airspeeds
12/13/2006 Summary of Johnson Flight Test
(revised 2/10/2007)
12/13/2006 Details of Johnson Flight Test
(revised 12/26/2007)
12/01/2007 Johnson Effect Confirmed
(revised 12/26/2007)
06/7/2008 Third Parallel Flight - vs. Diana 1
(revised 8/3/2008)

Publications and Presentations
1/2006 Sailplane Performance Improvement Using a Flexible Composite Surface Deturbulator - Sinha
(PDF, 1174 KB)
6/2006 Drag Reduction of Natural Laminar Flow Airfoils with a Flexible Surface Deturbulator - Sinha
(PDF, 757 KB)
2/2007 Wing Surface Deturbulators - Johnson
(PowerPoint, 2140 KB)
2/2007 Revolutionary Aerodynamics - Sinha
(PDF, 856 KB)
6/2007 Optimizing Wing Lift to Drag Ratio Enhancement with Flexible-Wall Turbulence Control - Sinha
(PDF, 588 KB)
8/2007 Improving Automotive Fuel Efficiency with Deturbulator Tape - Sinha
(PDF, 1368 KB)

Johnson Effect Confirmed (12/1/2007)

(Click images to expand them.)

The third test flight by Dick Johnson in Caddo Mills, Texas, on 12/13/2006 produced such extortionary results that Dick threw it out of his analysis and no one had a mind to give it a second thought. For three months, I studied that and other "anomalies" in the Johnson data, then argued that they were real. Now, Johnson's third flight has been duplicated! On Saturday, 12/1/07, the same glider, with redesigned deturbulators, essentially duplicated Johnson's third flight. His best L/D was an astounding 64:1, a 90% increase. The new measurement was 56:1, a 67% increase. Unbelievable as this seems, these figures are consistent with Dr. Sinha's objective and now the reality of this achievement can no longer be ignored. Extreme performance is both possible and repeatable!

Note: All large glide ratio vales contain large uncertainties. They should be taken as approximate values. However, the magnitude of these performance increases dwarfs those uncertainties.

Following are the altitude vs. time profiles for both flights taken from a Cambridge 302 flight data recorder. Notice how both profiles flatten out at the start of the 50 kt speed run and return to a poor sink rate after the 50 kt run. Those points are highlighted with blue lines.

Johnson Flight #3 - 12/13/2006
Hendrix Flight - 12/1/2007

Following are the two glide ratio plots superimposed. Notice the close replication of the Johnson data from 40 kts to 60 kts. This validates our different measurement techniques and the pristine atmospheric conditions on the test dates.

Now I present some oil flow patterns taken on 11/17/2007. After a failed test with the same deturbulators, I took these oil flows and used them to indicate a configuration of tapes that might lead to positive performance improvements. The next flight on 12/1/2007 reversed the earlier losses and duplicated Johnson's amazing flight a year earlier. Anyone familiar with such patterns will immediately see that there is no evidence of normal attached turbulent flow on the aft part of the wing where it should be. Likewise, on the front of the wing, the flow pattern is unusual. On a normal wing, these patterns would be drastically different, with laminar flow on the front of the wing rubbing the oil clean then leaving some on the surface as it lift away from the surface only to return in the region of the deturbulator, with a circulation pattern that traps much of the oil in a circulation region just forward of the deturbulator strip. Behind that, the oil would be gathered in streams by the attached turbulent flow. However, in these flows, the oil in both areas appears to have been only gently nudged aft, but not enough to produce significant streaming. Clearly, we have achieved a thinly separated flow over most of the upper wing surface that virtually eliminates skin friction drag.

These images show inner and outer panel sections (different airfoils) after a pattern tow and landing at 50 kts. Seals over the aileron gaps are purposely omitted. However, inner S-seals are installed and the lower gaps have curved mylar seals.

Following is a normal oil flow. Notice the sharply defined transition bubble circulation zone. Contrast the stringy runs of oil with the gently pushed patterns in the images above.

Following are Johnson's 12/13/2006 and my 12/1/2007 flight logs. You are free to download them to analyze as you please. Johnson's airspeed segments may be isolated by referencing indicated pressure altitudes in the table below. My segments were separated by "notching the barograph," as it were, and are also labeled in the top right image (above).

Johnson's flight is the second one in his log file.

File Date Place Pilot
6CDC3R22.IGC 12/13/2006 Caddo Mills, Texas Johnson
7C1C3R24.IGC 12/1/2007 Cherry Valley, Arkansas Hendrix

One last point. I choose to call this phenomenon (a slightly separated boundary flow that essentially eliminates skin friction to yield extraordinary performance improvements) the "Johnson Effect, after the first pilot to demonstrate it in flight." Hence the title of this article.

Jim Hendrix


© Copyright 2003-2008 Jim Hendrix