91,591 Overhead view. McDonnell XF-88B Experimental Jet Fighter. Langley used this aircraft in the mid-1950s to explore the potential of a supersonic propeller. Photographed in Engineer in Charge A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 508. **Note see L57-2259 for eye level view.

Smoke Flow Investigation XF7C-1 (Cowling Exhaust J.1 Type)

Wing Covering and Doping

YH 32 Helicopter

Photographed on: 08 05 1958. -- Impact test conducted by Langley's Hydrodynamics Division. The Division conducted a series of impact studies with full scale and model capsules of the original capsule shape A. Joseph Shortal wrote (Vol. 3, p. 16): The basic design of the capsule was made by M.A. Faget and his coworkers at PARD during the winter of 1957-1958. It was natural, then, that extensive use was made of the facilities at Wallops during the development of the spacecraft. The tests at Wallops consisted of 26 full-size capsules, either launched from the ground by rocket power or dropped from airplanes at high altitude and 28 scaled models, either rocket boosted or released from balloons. Emphasis in the Wallops program was on dynamic stability and aerodynamic heating of the capsule, and effectiveness of the pilot-escape and parachute-recovery systems. The biggest part of the Wallops program was the series of full-size capsules, rocket launched with the Little Joe booster, developed especially for Mercury. -- Published in Joseph A. Shortal, History of Wallops Station: Origins and Activities Through 1949, (Wallops Island, VA: National Aeronautics and Space Administration, Wallops Station, nd), Comment Edition.

L57-5383 Hot-air jets employing ceramic heat exchangers played an important role at Langley in the study of materials for ballistic missile nose cones and re-entry vehicles. Here a model is being tested in one of theses jets at 4000 degrees Fahrenheit in 1957. Photograph published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 477.

Photographed on: 12 09 58. -- Mercury capsule details, capsule in cargo bay of C-130 airplane prior to drop test, equipment in C130 for doing drop test.

North American F-100 C airplane used in sonic boom investigation at Wallops, October 7, 1958. Photograph published in: A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 672. -- Aircraft number: NACA 42024. Side view, 3/4 view from front, 3/4 view from rear, rear view, and two front views.

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

WS-110A "Brown Bomber"

William J. O Sullivan at desk with folded subsatellite, 30 inch subsatellite, 12 foot subsatellite, and corner reflector.

Looking South from inside the diffuser of the 40x80 foot wind tunnel at NACA's Ames Research Center. Construction began in late 1941, the mammoth construction task sorely taxing the resources of the new center. Two and a half years later, in dune 1944, the 40 x 80-foot full-scale tunnel went into operation.

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

Investigation of cambered propeller design for VTOL/STOL airplane. 3/4 front view of complete configuration, 0 deg.

Water Type Muffler Test

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

40x80 wind tunnel manometers control room at NACA's Ames Research Center. Control panel (called the bench board) showing five of the seven scale heads which measured the forces on the model (ie. Lift, drag, side force etc.)

Water Type Muffler Test

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

Test #9.

Robert Champine in X-Series Pressure Suit. Photograph published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 305.

This scale-model of North American's initial X-15 design was tested in North American and NACA wind tunnels note the conventional tail and fuselage side-tunnels that extend far toward the aircraft nose. North American engineers would determine that the variable wedge-angle stabilizer created a weight issue, and aeronautical testing by Langley engineers confirmed that the side-tunnels made the design less stable.

WS-110A "Brown Bomber"

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

Wood Mock-up of Arrow- Wing Bomber to Show Wing Contours

Brown Arrow Wing Bomber

Runway surface Patrick Henry Airport April 23, 1957

Wood Mock-up of Arrow- Wing Bomber to Show Wing Contours

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

General Research Model in 300 MOH 7x10

WS-110A "Brown Bomber"

This scale-model of North American's initial X-15 design was tested in North American and NACA wind tunnels note the conventional tail and fuselage side-tunnels that extend far toward the aircraft nose. North American engineers would determine that the variable wedge-angle stabilizer created a weight issue, and aeronautical testing by Langley engineers confirmed that the side-tunnels made the design less stable.

North American F-100 C airplane used in sonic boom investigation at Wallops, October 7, 1958. Photograph published in: A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 672. -- Aircraft number: NACA 42024. Side view, 3/4 view from front, 3/4 view from rear, rear view, and two front views.

**Note also copied and numbered as L90-3749. -- L57-4827 caption: Take off of a five-stage missile research rocket from Wallops Island in 1957. The first two stages propelled the model to about 100,000 feet the last three stages were fired on a descending path to simulate the reentry conditions of ballistic missiles. -- Photograph published in Winds of Change, 75th Anniversary NASA publication (page 72), by James Schultz. -- Photograph also published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen (page 380).

Water Type Muffler Test

Application of blowing-type boundry-layer control to the leading-and trailing-edge flaps of a Change Vought XF8U-1 wing

Inflation Tests of the Echo 1 Satellite in Weeksville, N.C. 1958-L-03603 Image Langley engineers Edwin Kilgore (center), Norman Crabill (right) and an unidentified man take a peek inside the vast balloon during inflation tests. Page. 183 Space Flight Revolution NASA Langley Research Center From Sputnik to Apollo. NASA SP-4308.

17-foot test section in contraction cone of 300-MPH 7 x 10-Foot Tunnel (7 x 10-Foot test section in background).

11-Inch Hypersonic Tunnel: various models tested in the tunnel.

Reeves Electronic analog computer (REAC), Ames' first electronic computing machine, was acquired in 1949 to perform control simulation analysis.

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

Experimental investigation of boundary-layer control to helicopter rotor blades to increase forward speed capabilities. 3/4 front view. Shaft angle - 35deg. John Mc.Cloud in picture. He was a good guy.

Clark Y Airfoil. 3/4 front view of 8x48 foot Clark Y Airfoil mounted (inverted) in the 40x80 foot wind tunnel at NACA's Ames Research Center.

McDonnell F2H-3 Banshee: To more clearly mark the operators of this McDonnell F2H-3 Banshee, the VY of Navy has been painted out and the appropriate lettering to spell NACA has been applied. Note that the second A is of a different shape than the first. The Banjo retained Navy titles on the wings, however.

William J. O Sullivan at desk with folded subsatellite, 30 inch subsatellite, 12 foot subsatellite, and corner reflector.

North American F-100 C airplane used in sonic boom investigation at Wallops, October 7, 1958. Photograph published in: A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 672. -- Aircraft number: NACA 42024. Side view, 3/4 view from front, 3/4 view from rear, rear view, and two front views.

Instrumentation in Full Scale Tunnel

Inflation Tests of the Echo 1 Satellite in Weeksville, N.C. 1958-L-03603 Image Langley engineers Edwin Kilgore (center), Norman Crabill (right) and an unidentified man take a peek inside the vast balloon during inflation tests. Page. 183 Space Flight Revolution NASA Langley Research Center From Sputnik to Apollo. NASA SP-4308.

Installation of the Douglas A-26B airplane in the 40x80 foot wind tunnel at NACA's Ames Research Center. Airplane being centered over tunnel opening.

WS-110A "Brown Bomber"

Various Components of Goodyear Inflatable Airplane in Full Scale Tunnel building 643 Test 238

Drawing of the 8-Foot Transonic Pressure Tunnel.

Wood Mock-up of Arrow Wing Bomber to Show Wing Contours

Brown Arrow Wing Bomber

Publicity Shot of close up of Nacell, Drive Nacel and cooling vent in nose for wind tunnel in NACA Ames 40x80 foot Wind Tunnel.

Vertical model flying in Langley Research Center's Full Scale Tunnel.

E118-2587 Model

Grumman F9F-2 Panther: Originally built as a F9F-3, this Grumman F9F-2 Panther has a Pratt and Whitney J42 turbojet power plant, hence the designation change. This Panther underwent handling quality tests, serving long enough at Langley to witness the change from the NACA to NASA.

Investigation of cambered propeller design for VTOL/STOL airplane. 3/4 front view of Curtis VTOL propeller.

Various Components of Goodyear Inflatable Airplane in Full Scale Tunnel building 643 Test 238

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

North American X-15 Drop Model

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

North American F-100 C airplane used in sonic boom investigation at Wallops, October 7, 1958. Photograph published in: A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 672. -- Aircraft number: NACA 42024. Side view, 3/4 view from front, 3/4 view from rear, rear view, and two front views.

Douglas BTD-1 airplane 3/4 front view from below in Ames 40x80 foot Wind Tunnel, unseated, horizontal tail on.

Views of F-8U Crusader Aircraft at NASA Langley

L57-700 In the reentry flight path of this nose cone model of a Jupiter Intermediate range ballistic missile (IRBM) was tested in the Unitary Plan Wind Tunnel. Photograph published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 475.

3/4 front view from below of the Ryan FR-1 airplane mounted in the NACA Ames 40x80 foot wind tunnel. Production configuration.

(07/07/1943) Construction view from inside the contraction framing of the 40x80 foot wind tunnel with a blimp flying in the background.

Foreword, front view of McDonnell Model XV-1 Convertiplane in the Ames 40x80 Foot Wind Tunnel. The McDonnell XV-1 was an experimental compound gyroplane developed for a joint research program between the United States Air Force and the United States Army to explore technologies to develop an aircraft that could take off and land like a helicopter but fly at faster airspeeds, similar to a conventional airplane. The XV-1 would reach a speed of 200 mph (322 km/h), faster than any previous rotorcraft, but the program was terminated due to the tip-jet noise and complexity of the technology which gave only a modest gain in performance.

8-Foot Transonic Pressure Tunnel (TPT): Sample of Schlieren results Left - Mach 1.03 Right - Mach 1.20.

Phase SB Propeller installed on F88B

Local for Hypersonic Continuous Flow Facility

A 1/10th Scale Model of the X-15 research plane is prepared in Langley's 7 x 10 Foot Wind Tunnel for studies relating to spin characteristics. -- Photograph published in Winds of Change, 75th Anniversary NASA publication (page 66), by James Schultz.

(03/12/1943) Aerial view of the site from the 40x80 wind tunnel At NASA Ames Research Center. Site includes the 16 foot and 7x10 wind tunnels in the background. Building 200 also under construction. Framing for the drive fans of the 40x80 in scene.

Scale model of Mercury capsule shape A, indicating the position of the astronaut.

A one-twentieth scale model of the X-15 originally suspended beneath the wing of a B-52 is observed by a scientist of the National Aeronautics and Space Administration (NASA) as it leaves the bomber model in tests to determine the release characteristics and drop motion of the research airplane. Caption: The aerodynamics of air launching the North American X-15 being investigated in the 300MPH Low Speed 7x10 Tunnel, about 1957. Photograph published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 366. Photograph also published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication. Page 49.

Experimental investigation of boundary layer control to helicopter rotor blades to increase forward speed capabilities. 3/4 overhead view. Shaft angle - 35deg.

Computers' at work in 16ft wind tunnel - calculating test data

Ryan #92 deflected slipstream VTOL/STOL airplane with flaps undeflected.

Motor and propeller blades in 40x80ft wind tunnel. Six 40-foot-diameter fans, each powered by a 6000-horsepower electric motor maintained airflow at 230 mph or less (these are still tornado velocities).

Interior view of the slotted throat test section installed in the 8-Foot High Speed Tunnel (HST) in 1950. The slotted region is about 160 inches in length. In this photograph, the sting-type model support is seen straight on. In a NASA report, the test section is described as follows: The test section of the Langley 8-foot transonic tunnel is dodecagonal in cross section and has a cross-sectional area of about 43 square feet. Longitudinal slots are located between each of the 12 wall panels to allow continuous operation through the transonic speed range. The slots contain about 11 percent of the total periphery of the test section. Six of the twelve panels have windows in them to allow for schlieren observations. The entire test section is enclosed in a hemispherical shaped chamber. John Becker noted that the tunnel s final achievement was the development and use in routine operations of the first transonic slotted throat. The investigations of wing-body shapes in this tunnel led to Whitcomb s discovery of the transonic area rule. James Hansen described the origins of the the slotted throat as follows: In 1946 Langley physicist Ray H. Wright conceived a way to do transonic research effectively in a wind tunnel by placing slots in the throat of the test section. The concept for what became known as the slotted-throat or slotted-wall tunnel came to Wright not as a solution to the chronic transonic problem, but as a way to get rid of wall interference (i.e., the mutual effect of two or more meeting waves or vibrations of any kind caused by solid boundaries) at subsonic speeds. For most of the year before Wright came up with this idea, he had been trying to develop a theoretical understanding of wall interference in the 8-Foot HST, which was then being repowered for Mach 1 capability. When Wright presented these ideas to John Stack, the response was enthusiastic but neither Wright nor Stack thought of slotted-throats as a solution to the transonic problem, only the wall interference problem. It was an accidental discovery which showed that slotted throats might solve the transonic problem. Most engineers were skeptical but Stack persisted. Initially, plans were to modify the 16-Foot tunnel but in the spring of 1948, Stack announced that the 8-Foot HST would also be modified. As Hansen notes: The 8-Foot HST began regular transonic operations for research purposes on 6 October 1950. The concept was a success and led to plans for a new wind tunnel which would be known as the 8-Foot Transonic Pressure Tunnel. -- Published in U.S., National Advisory Committee for Aeronautics, Characteristics of Nine Research Wind Tunnels of the Langley Aeronautical Laboratory, 1957, pp. 17, 22 James R. Hansen, Engineer in Charge, NASA SP-4305, p. 454 and Chapter 11, The Slotted Tunnel and the Area Rule.

James Hansen describes the work on Project Echo s air density experiment known as the Sub-Satellite. Before launch engineers subjected the sub-satellite to many tests. Here, the sub-satellite is shown prior to tests to determine the capacity of the 30-inch Sub-Satellite to withstand the high temperature of direct sunlight in space, Langley researchers subjected it to 450 F heat test. Results indicated that the aluminum-covered Mylar plastic would effectively reflect the dangerous heat. -- Published in James R. Hansen, Spaceflight Revolution: NASA Langley Research Center From Sputnik to Apollo, NASA SP-4308, p. 168.

3/4 rear view of the Ryan FR-1 airplane mounted in the NACA Ames 40x80 foot wind tunnel from below. Production configuration.

L57-989: Man and woman shown working with IBM type T04 electronic data processing machine.

Modified Bell X-1 model pioneered variable-sweep studies in 1947. Photograph published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication, page 52.

Fig. 68 Unitary Wind Tunnel Display

Water Type Muffler Test

NACA Ames 40x80 foot wind tunnel (South West).

Detail and Launcher Pictures of E128-2955 (Ascon Rocket)

Water Type Muffler Test

Various Components of Goodyear Inflatable Airplane in Full Scale Tunnel building 643 Test 238

Testing of Mercury Capsule Shape A by the Hydrodynamics Division of Langley. Joseph Shortal wrote (vol. 3, p. 19): The Hydrodynamics Division provided assistance in determining landing loads. In this connection, after PARD engineers had unofficially approached that division to make some water impact tests with the boilerplate capsule, J.B. Parkinson, Hydrodynamics Chief visited Shortal to find out if the request had his support. Finding out that it did, Parkinson said, Its your capsule. If you want us to drop it in the water, we will do it. From Shortal (Vol. 3, p. 16): The basic design of the capsule was made by M.A. Faget and his coworkers at PARD during the winter of 1957-1958. It was natural, then, that extensive use was made of the facilities at Wallops during the development of the spacecraft. The tests at Wallops consisted of 26 full-size capsules, either launched from the ground by rocket power or dropped from airplanes at high altitude and 28 scaled models, either rocket boosted or released from balloons. Emphasis in the Wallops program was on dynamic stability and aerodynamic heating of the capsule, and effectiveness of the pilot-escape and parachute-recovery systems. The biggest part of the Wallops program was the series of full-size capsules, rocket launched with the Little Joe booster, developed especially for Mercury. -- Published in Joseph A. Shortal, History of Wallops Station: Origins and Activities Through 1949, (Wallops Island, VA: National Aeronautics and Space Administration, Wallops Station, nd), Comment Edition.

Water Type Muffler Test

3/4 rear view from below of Douglas BTD-1 airplane in Ames 40x80 foot Wind Tunnel, unseated, horizontal tail on.

F86 D 959

A one-twentieth scale model of the X-15 originally suspended beneath the wing of a B-52 is observed by a scientist of the National Aeronautics and Space Administration (NASA) as it leaves the bomber model in tests to determine the release characteristics and drop motion of the research airplane. Caption: The aerodynamics of air launching the North American X-15 being investigated in the 300MPH Low Speed 7x10 Tunnel, about 1957. Photograph published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 366. Photograph also published in Sixty Years of Aeronautical Research 1917-1977 By David A. Anderton. A NASA publication. Page 49.

Engineer W.J. O Sullivan, Jr., seated beside 30 inch subsatellite. He holds inflation bottle and folded duplicate copy, July 1957.

North American F-100 C airplane used in sonic boom investigation at Wallops, October 7, 1958. Photograph published in: A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 672. -- Aircraft number: NACA 42024. Side view, 3/4 view from front, 3/4 view from rear, rear view, and two front views.