Results of tests in the AEDC VKF Tunnel B using the phase change paint technique on 0.04 scale 50 percent forebody models (82-0) of the Rockwell space shuttle orbiter (OH50A)

Heating measurements on Space Shuttle Orbiter models with differentially deflected elevons

Wells, W. L.

May 1983

The phase change paint technique was used to make heat transfer measurements on the windward wing/el...

Use of phase-change paints to study fin-body interference heating /

Gillerlain, Jr., Joseph D., author.
Naval Surface Weapons Center. : White Oak Laboratory.

In recent years the phase-change paint technique has evolved into an accepted diagnostic tool in hig...

Heat-transfer tests on the Rockwell International space shuttle orbiter with and without simulated protuberances

Kaul, C. E.
Carter, L. D.

July 1975

Aerothermodynamic tests on the forward half of the Rockwell International Space Shuttle Orbiter Conf...

Heat transfer phase change paint tests of 0.0175-scale models (nos. 21-0 and 46-0) of the Rockwell International space shuttle orbiter in the AEDC tunnel B hypersonic wind tunnel (test OH25A)

Dye, W. H.

July 1975

Tests were conducted in a hypersonic wind tunnel using various truncated space shuttle orbiter confi...

Heat transfer phase change paint test (OH-42) of a Rockwell International SSV orbiter in the NASA/LRC Mach 8 variable density wind tunnel

Cummings, J.
Lawing, P.
Rich, G.
Craig, C.
Quan, M.
Gorowitz, H.
Dye, W.
Jones, R.
Creel, T. R., Jr.

December 1973

Phase change paint tests of a Rockwell International .00593-scale space shuttle orbiter were conduct...

Results of phase change paint heat transfer tests utilizing 0.040 scale 50% forebody models (No. 82-0) of the Rockwell International space shuttle orbiter in AEDC VKF hypersonic tunnel B (test OH54A)

Dye, W. H.

April 1976

Results of aerodynamic heating tests conducted in October 1974 on a space shuttle orbiter model usin...

Phase change paint tests on Rockwell orbiter/tank and orbiter alone configurations (OH3A/OH3B)

Craig, C.
Quan, M.

April 1974

Wind tunnel tests were conducted on scale models of the space shuttle orbiter and external tank. The...

Results of phase change heat transfer test OH51 using 0.006-scale space shuttle orbiter models 46-0 and 90-0 and partial wing 0.0175-scale model 64-0 in the LaRC 31-inch CFHT

Cummings, J. W.

March 1977

Test OH51 was a phase change paint test conducted in the LaRC 31-inch CFHT utilizing models 46-0, 64...

Heat transfer rate distributions on McDonnell-Douglas booster determined by phase change technique for nominal Mach number of 8

Matthews, R. K.
Warmbrod, J. D.
Martindale, W. R.

April 1972

The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on th...

Heat transfer investigation of Langley Research Center transition models at a Mach number of 8, volume 2

Martindale, W. R.
Matthews, R. K.
Warmbrod, J. D.
Johnson, C. B.

March 1972

The results are presented of a wind tunnel test program to determine aerodynamic heat transfer distr...

Ascent heat transfer rate distribution on the North American Rockwell delta wing orbiter and the General Dynamics/Convair booster at a Mach number of 8 (mated)

Warmbrod, J. D.
Matthews, R. K.
Martindale, W. R.

June 1972

A wind tunnel test program to determine aerodynamic interference heating on the North American Rockw...

Heat transfer distributions on the LMSC 040C and 040A-L4 delta wing orbiters (M equals 8)7

Mcgee, K. W.
Schultz, H. D.
Baker, R. C.

July 1972

The results of a wind tunnel investigation are presented for measuring aerodynamic heat transfer dis...

Results of phase change paint tests of 0.040 scale 50% forebody models (82-0) of the space shuttle orbiter in the AEDC VKF B hypersonic wind tunnel (OH75)

Dye, W. H.

April 1976

Post-test information and data are presented from phase change paint, aerodynamic heating wind tunne...

Heat transfer rate distribution on North American Rockwell delta wing orbiter determined by phase change paint technique at a Mach number of 8, volume 1

Martindale, W. R.
Matthews, R. K.
Warmbrod, J. D.

March 1972

The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on an...

Results of aerodynamic heat transfer tests of a 0.0175-scale model of the Rockwell International Space Shuttle Orbiter 139 (model number 22-0) in the NASA/Ames 3.5-foot hypersonic wind tunnel (test OH6)

Dye, W. H.
Lockman, W. K.

October 1975

The results of a hypersonic wind tunnel test program conducted using a 0.0175 scale thin-skin thermo...

Heating measurements on Space Shuttle Orbiter models with differentially deflected elevons

Wells, W. L.

May 1983

The phase change paint technique was used to make heat transfer measurements on the windward wing/el...

Use of phase-change paints to study fin-body interference heating /

Gillerlain, Jr., Joseph D., author.
Naval Surface Weapons Center. : White Oak Laboratory.

In recent years the phase-change paint technique has evolved into an accepted diagnostic tool in hig...

Heat-transfer tests on the Rockwell International space shuttle orbiter with and without simulated protuberances

Kaul, C. E.
Carter, L. D.

July 1975

Aerothermodynamic tests on the forward half of the Rockwell International Space Shuttle Orbiter Conf...

Heat transfer phase change paint tests of 0.0175-scale models (nos. 21-0 and 46-0) of the Rockwell International space shuttle orbiter in the AEDC tunnel B hypersonic wind tunnel (test OH25A)

Dye, W. H.

July 1975

Tests were conducted in a hypersonic wind tunnel using various truncated space shuttle orbiter confi...

Heat transfer phase change paint test (OH-42) of a Rockwell International SSV orbiter in the NASA/LRC Mach 8 variable density wind tunnel

Cummings, J.
Lawing, P.
Rich, G.
Craig, C.
Quan, M.
Gorowitz, H.
Dye, W.
Jones, R.
Creel, T. R., Jr.

December 1973

Phase change paint tests of a Rockwell International .00593-scale space shuttle orbiter were conduct...

Results of phase change paint heat transfer tests utilizing 0.040 scale 50% forebody models (No. 82-0) of the Rockwell International space shuttle orbiter in AEDC VKF hypersonic tunnel B (test OH54A)

Dye, W. H.

April 1976

Results of aerodynamic heating tests conducted in October 1974 on a space shuttle orbiter model usin...

Phase change paint tests on Rockwell orbiter/tank and orbiter alone configurations (OH3A/OH3B)

Craig, C.
Quan, M.

April 1974

Wind tunnel tests were conducted on scale models of the space shuttle orbiter and external tank. The...

Results of phase change heat transfer test OH51 using 0.006-scale space shuttle orbiter models 46-0 and 90-0 and partial wing 0.0175-scale model 64-0 in the LaRC 31-inch CFHT

Cummings, J. W.

March 1977

Test OH51 was a phase change paint test conducted in the LaRC 31-inch CFHT utilizing models 46-0, 64...

Heat transfer rate distributions on McDonnell-Douglas booster determined by phase change technique for nominal Mach number of 8

Matthews, R. K.
Warmbrod, J. D.
Martindale, W. R.

April 1972

The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on th...

Heat transfer investigation of Langley Research Center transition models at a Mach number of 8, volume 2

Martindale, W. R.
Matthews, R. K.
Warmbrod, J. D.
Johnson, C. B.

March 1972

The results are presented of a wind tunnel test program to determine aerodynamic heat transfer distr...

Ascent heat transfer rate distribution on the North American Rockwell delta wing orbiter and the General Dynamics/Convair booster at a Mach number of 8 (mated)

Warmbrod, J. D.
Matthews, R. K.
Martindale, W. R.

June 1972

A wind tunnel test program to determine aerodynamic interference heating on the North American Rockw...

Heat transfer distributions on the LMSC 040C and 040A-L4 delta wing orbiters (M equals 8)7

Mcgee, K. W.
Schultz, H. D.
Baker, R. C.

July 1972

The results of a wind tunnel investigation are presented for measuring aerodynamic heat transfer dis...

Results of phase change paint tests of 0.040 scale 50% forebody models (82-0) of the space shuttle orbiter in the AEDC VKF B hypersonic wind tunnel (OH75)

Dye, W. H.

April 1976

Post-test information and data are presented from phase change paint, aerodynamic heating wind tunne...

Heat transfer rate distribution on North American Rockwell delta wing orbiter determined by phase change paint technique at a Mach number of 8, volume 1

Martindale, W. R.
Matthews, R. K.
Warmbrod, J. D.

March 1972

The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on an...

Results of aerodynamic heat transfer tests of a 0.0175-scale model of the Rockwell International Space Shuttle Orbiter 139 (model number 22-0) in the NASA/Ames 3.5-foot hypersonic wind tunnel (test OH6)

Dye, W. H.
Lockman, W. K.

October 1975

The results of a hypersonic wind tunnel test program conducted using a 0.0175 scale thin-skin thermo...

Heating measurements on Space Shuttle Orbiter models with differentially deflected elevons

Wells, W. L.

May 1983

The phase change paint technique was used to make heat transfer measurements on the windward wing/el...

Use of phase-change paints to study fin-body interference heating /

Gillerlain, Jr., Joseph D., author.
Naval Surface Weapons Center. : White Oak Laboratory.

In recent years the phase-change paint technique has evolved into an accepted diagnostic tool in hig...

Heat-transfer tests on the Rockwell International space shuttle orbiter with and without simulated protuberances

Kaul, C. E.
Carter, L. D.

July 1975

Aerothermodynamic tests on the forward half of the Rockwell International Space Shuttle Orbiter Conf...

Results of tests in the AEDC VKF Tunnel B using the phase change paint technique on 0.04 scale 50 percent forebody models (82-0) of the Rockwell space shuttle orbiter (OH50A)

Abstract

Extracted data

Results of tests in the AEDC VKF Tunnel B using the phase change paint technique on 0.04 scale 50 percent forebody models (82-0) of the Rockwell space shuttle orbiter (OH50A)

Abstract

Extracted data

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