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- LIMITED MEASUREMENTS OF STATIC LONGITUDINAL STABILITY IN FLIGHT OF DOUGLAS D-558-1 AIRPLANE (BUAERO NO. 37971
Authors: Walter C. Williams
Report Number: NACA-RM-L8E14
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: During airspeed calibration flights of the D-558-1 airplane being used by NACA for high-speed-flight research, some measurements were obtained of the static longitudinal stability up to a Mach number of 0.85. These data showed that the airplane possessed positive static longitudinal stability up to a Mach number of 0.80. A trim change in the nose-down direction occurred for Mach numbers obove 0.82.
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Report declassified: 8 September 1959
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Report Date: June 1949
No. Pages: 10
- STABILITY RESULTS OBTAINED WITH DOUGLAS D-558-1 AIRPLANE (BUAERO NO. 37971) IN FLIGHT UP TO A MACH NUMBER OF 0.89
Authors: William H. Barlow and Howard C. Lilly
Report Number: NACA-RM-L8K03
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Measurements have been made of some of the high-speed characteristics of the D-558-1 airplane up to a Mach number of 0.89. The results of these tests showed that the stabilizer incidence drastically affected the longitudinal trim characteristics above a Mach number of 0.80. With a stabilizer incidence of 2.3 degrees, the airplane became nose heavy above a Mach number of 0.8. With a stabilizer incidence of 1.4 degrees, the airplane became tail heavy above a Mach number of 0.83. The airplane also became right-wing heavy above a Mach number of 0.84 and the airplane felt uncertain laterally to the pilot. The longitudinal stability in accerlerated flight was positive throughout the speed range from a Mach number of 0.50 to 0.80 and increased above a Mach number of 0.675. The buffet boundary was defined up to a Mach number of 0.84 and was similar to that for the Bell XS-1 airplane with the same wing section, 65-110.
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Report declassified: 2 December 1954
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Report Date: April 1949
No. Pages: 42
- STABILITY AND CONTROL DATA OBTAINED FROM FIRST FLIGHT OF X-4 AIRPLANE
Authors: Hubert M. Drake
Report Number: NACA-RM-L9A31
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NACA instrumentation has been istalled in the X-4 airplanes to obtain stability and control data during the Northrop conducted acceptance tests. The results of the first flight of the X-4 number 1 airplane are presented in this report. These data were obtained for a center-of-gravity position of about 22 percent of the mean aerodynamic chord. A maximum indicated airspeed and pressure altitude of 290 miles per hour and 11,000 feet, respectively, were obtained during the flight. Results of the flight indicated that the airplane is slightly unstable, stick fixed, in gear-up, flaps-up configuration for a center-of-gravity position at 21.4 percent of the mean aerodynamic chord. The pilot reported that it was difficult to maintain steady flight in this configuration. There was no indication of a snaking or lateral oscillation for the speed range covered. For gear-down configuration at low lift coefficients with the center of gravity at 22.4 and 21.6
percent of the mean aerodynamic chord the airplane was longitudinally stable; however, at high lift coefficients, it was indicated that the airplane was longitudinally unstable. The rudder effectiveness appeared to be low in the gear-down, low-speed condition. The maximum rate of rudder motion of 25 degrees per second available with the present control system was considered by the pilot to be too slow.
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Report declassified: 14 June 1951
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Report Date: February 1949
No. Pages: 12
- STABILITY AND CONTROL DATA OBTAINED FROM FIRST FLIGHT OF X-4 AIRPLANE , Research Memorandum
Authors: Hubert M. Drake
Report Number: NACA-RM-L9D13
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the Northrop conducted acceptance tests. The results of the first flight of the X-4 number 1 airplane are presented in this report. These data were obtained for a center-of-gravity position of about 22 percent of the mean aerodynamic chord. A maximum indicated airspeed and pressure altitude of 290 miles per hour and 11,000 feet, respectively, were obtained during the flight. Results of the flight indicated that the airplane is slightly unstable, stick fixed, in gear-up, flaps-up configuration for a center-of-gravity position at 21.4 percent of the mean aerodynamic chord. The pilot reported that it was difficult to maintain steady flight in this configuration. There was no indication of a snaking or lateral oscillation for the speed range covered. For gear-down configuration at low lift coefficients with the center of gravity at 22.4 and 21.6
percent of the mean aerodynamic chord the airplane was longitudinally stable; however, at high lift coefficients, it was indicated that the airplane was longitudinally unstable. The rudder effectiveness appeared to be low in the gear-down, low-speed condition. The maximum rate of rudder motion of 25 degrees per second available with the present control system was considered by the pilot to be too slow.
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Report Date: June 1949
- STABILITY AND CONTROL DATA OBTAINED FROM FIRST FLIGHT OF X-4 AIRPLANE , Research Memorandum
Authors: Hubert M. Drake
Report Number: NACA-RM-L9D13
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the Northrop conducted acceptance tests. The results of the first flight of the X-4 number 1 airplane are presented in this report. These data were obtained for a center-of-gravity position of about 22 percent of the mean aerodynamic chord. A maximum indicated airspeed and pressure altitude of 290 miles per hour and 11,000 feet, respectively, were obtained during the flight. Results of the flight indicated that the airplane is slightly unstable, stick fixed, in gear-up, flaps-up configuration for a center-of-gravity position at 21.4 percent of the mean aerodynamic chord. The pilot reported that it was difficult to maintain steady flight in this configuration. There was no indication of a snaking or lateral oscillation for the speed range covered. For gear-down configuration at low lift coefficients with the center of gravity at 22.4 and 21.6
percent of the mean aerodynamic chord the airplane was longitudinally stable; however, at high lift coefficients, it was indicated that the airplane was longitudinally unstable. The rudder effectiveness appeared to be low in the gear-down, low-speed condition. The maximum rate of rudder motion of 25 degrees per second available with the present control system was considered by the pilot to be too slow.
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Report Date: June 1949
- MEASURED CHARACTERISTICS OF THE DOUGLAS D-558-1 AIRPLANE (BUAERO NO. 37971) IN TWO LANDINGS
Authors: Hubert M. Drake
Report Number: NACA-RM-L9D20A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Records were obtained of two landings of the Douglas D-558-1 airplane made during the stability and control investigation. These two records show that the maximum normal-force coefficient used during the landings, 0.95, was considerably below the maximum, 1.2, estimated to be available. The approaches were made at 150 percent of the possible minimum speed, and the actual contacts were at about 115 percent of minimum speed. The rate of descent in the approach was 1200 to 1800 feet per minute at the start of the landing flare.
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Report declassified: 9 September 1954
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Report Date: June 1949
No. Pages: 7
- RESULTS OBTAINED FROM SECOND FLIGHT OF X-4 AIRPLANE (A.F. NO. 46-676)
Authors: Walter C. Williams
Report Number: NACA-RM-L9F21
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the Northrop conducted acceptance tests. The results of the second flight of the X-4 number 1 airplane are presented in this report. This flight was made with the center of gravity at 19.7 percent of the mean aerodynamic chord and with the rudder-boost system removed. The results of the flight showed that the longitudinal stability was positive in the clean condition and in the gear-down flaps-up condition. Records taken during landing approach and in a steady run at 170 miles per hour showed that the lateral oscillation is poorly damped. The pilot reported that the rudder control was adequate.
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Report declassified: 15 May 1951
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Report Date: July 1949
No. Pages: 14
- PRELIMINARY MEASUREMENTS OF THE DYNAMIC LATERAL STABILITY CHARACTERISTICS OF THE DOUGLAS D-558-II (BUAERO NO. 37974) AIRPLANE
Authors: Sigurd S. Sjoberg
Report Number: NACA-RM-L9G18
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: This paper presents some data on the dynamic lateral stability characteristics of the Douglas D-558-II (BuAero No. 37974) airplane. For the airplane in the clean condition, the lateral oscillations are lightly damped. In the landing condition, the airplane performs a constant-amplitude lateral oscillation.
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Report declassified: 29 May 1957
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Report Date: August 1949
No. Pages: 9
- MEASUREMENTS OF AILERON EFFECTIVNESS OF THE BELL X-1 AIRPLANE AT MACH NUMBERS BETWEEN 0.9 AND 1.06
Authors: Hubert M. Drake
Report Number: NACA-RM-L9G19A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Abrupt rudder-fixed aileron rolls have been made with the Bell X-1 airplane in powered flight at Mach numbers between 0.90 and 1.06 at about 40,000 feet pressure altitude. These aileron rolls indicate that the aileron effectiveness for large deflections at M = 0.94 is only one-fourth the value at M = 0.82, and the effectiveness at M = 1.06 is slightly greater than at M = 0.94.
Distribution/Availability: Unclassified - Unlimited
Report declassified: 20 October 1955
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Report Date: August 1949
No. Pages: 7
- RESULTS OBTAINED FROM THIRD FLIGHT OF NORTHROP X-4 AIRPLANE (A.F. NO. 46-676)
Authors: Walter C. Williams
Report Number: NACA-RM-L9G20A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NACA instrumentation has been installed in the Northrop X-4 airplane to obtain stability and control data during the Northrop conducted acceptance tests. The results of the third flight of the X-4 number 1 airplane are presented in this paper. The results of this flight showed that the directional stability as measured in steadily increasing sideslips was positive and high and that the lateral stability was positive.
Distribution/Availability: Unclassified - Unlimited
Report declassified: 28 June 1951
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Report Date: September 1949
No. Pages: 14
- THE STATIC-PRESSURE ERROR OF WING AND FUSELAGE AIRSPEED INSTALLATIONS OF THE X-1 AIRPLANES IN TRANSONIC FLIGHT , Research Memorandum
Authors: Harold R. Goodman and Roxanah B. Yancey
Report Number: NACA-RM-L9G22
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Measurements were made in the transonic speed ranges of the static-pressure position error at a distance of 0.96 chord ahead of the wing tip of both the 8-percent-thick-wing and the l0-percent-thick-wing X-l airplanes, and at a point 0.6 maximum fuselage diameter ahead of the fuselage nose of the X-l airplanes.
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Report Date: July 1949
- STABILITY AND CONTROL DATA OBTAINED FROM FOURTH AND FIFTH FLIGHTS OF THE NORTHROP X-4 AIRPLANE (A.F. NO. 46-676)
Authors: George M. Valentine
Report Number: NACA-RM-L9G25A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: NACA instrumentation has been installed in the Northrop X-4 airplane to obtain stability and control data during the Northrop conducted acceptance tests. The results of the fourth and fifth flights of the Northrop X-4 number 1 airplane are presented in this paper. These data were obtained for a center-of-gravity position of approximately 19.5 percent of the mean aerodynamic chord. The results of this flight showed that the directional stability as measured in steadily increasing sideslips was positive and high and that the effective dihedral was positive. The results also show the airplane to be longitudinally stable, stick fixed, with the center of gravity at 19.5 percent of the mean aerodynamic chord.
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Report declassified: 15 May 1951
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Report Date: August 1949
No. Pages: 23
- PRELIMINARY FLIGHT MEASUREMENTS OF THE STATIC LONGITUDINAL STABILITY AND STALLING CHARACTERISTICS OF THE DOUGLAS D-558-II RESEARCH AIRPLANE (BUAERO NO. 37974) , Research Memorandum
Authors: S. A. Sjoberg and R. A. Champine
Report Number: NACA-RM-L9H31A
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Contains results of brief flight measurements of the static longitudinal stability and stalling characteristics of the Douglas D-558-II (BuAero No. 37974) research airplane.
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Report Date: October 1949
- THE STATIC-PRESSURE ERROR OF A WING AIRSPEED INSTALLATION OF THE MCDONNELL XF-88 AIRPLANE IN DIVES TO TRANSONIC SPEEDS , Research Memorandum
Authors: Harold R. Goodman
Report Number: NACA-RM-SL9I12
Performing Organization: NASA Dryden Flight Research Center, Edwards, CA
Abstract: Measurements were made, in dives to transonic speeds, of the static-pressure position error at a distance of one chord ahead of the wing tip of the McDonnell XF-88 airplane. The airplane incorporates a wing which is swept back 35• along the 0.25-chord line and utilizes a 65-series airfoil with a 9-percent-thick section perpendicular to the 0.25-chord line. The section in the stream direction is approximately 8 percent thick. Data up to a Mach number of about 0.97 were obtained within an airplane normal-force-coefficient range from about 0.05 to about 0.68. Data at Mach numbers above about 0.97 were obtained within an airplane normal-force-coefficient range from about 0.05 to about 0.38.
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Report Date: September 1949
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