An elementary analysis of the adaptation of the Beams' experimental concept to a delta G/G detector to be used in space
Modified inertial angular acceleration balance torque for detecting gravitational changes
Blood, B. E.↗
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Results for “Deltas”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Mass spectrometry in structural and stereochemical problems. CLXXXII. Investigations in the 10-Phenyl-2-decalone system - The synthesis and electron impact promoted phenyl migration of trans-10-phenyl- delta superscript three-2-octalone
Electron impact promoted phenyl migration of trans phenyloctalone, considering mass spectrometry and stereochemistry
Djerassi, C.↗
Electric field excitation of O2/super 1 delta sub g/ in auroras
Auroral enhancement of IR oxygen band, considering electric field excitation mechanisms
Walker, J. C. G.↗
Newtonian aerodynamics for blunted delta- shaped lifting bodies
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Brakensiek, R. R.↗
Sizing data for multiple stages. Expended and reusable operating modes. Tabular listing of configuration Delta V capabilities, appendix A Project technical report, task E-94
One way velocity increments obtainable from one and two stage propulsive configurations for expended and reusable modes - tables
Bratkowski, R. J.↗
Flow fields over sharp edged delta wings with attached shocks
Analysis of supersonic and hypersonic flow of inviscid ideal gas over conical wings with sharp leading edges and attached shock waves by three dimensional method of characteristics
Beeman, E. R., Jr.↗
An attempted measurement of an O2 /1 Delta /0-/3 Sigma g minus/ nighttime emission profile in a zero degree latitude region
Attempted rocket-borne radiometer observations of molecular oxygen nighttime emission in near infrared at zero deg latitude
Welker, J. E.↗
Space shuttle: Static stability and control investigation of the NAR-GDVC straight wing booster (B-8H modified) with the straight wing orbiter (130G) or delta wing orbiter (134B)
Trisonic wind tunnel tests on static stability and controllability of NAR/GD space shuttle and booster
Allen, E. C.↗
Space shuttle: Static aerodynamic and control investigation of an expendable second stage with payload alone and with delta wing booster (B-15B-1)
Aerodynamic force and moment coefficients for scale model of expendable second stage modified S-2 alone and mounted piggyback on space shuttle booster from Mach 0.6 to 4.96
Allen, E. C.↗
The delta and pi effects of phosphines, pyridines, and amines in LW/CO/5 complexes
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Stewart, R. P.↗
A wind tunnel investigation to evaluate the aerodynamic performance of three different airplane configurations having arrow-wing and delta-wing plan forms at a Mach number of 2.91
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Grimaud, J. E.↗
Free flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four engine delta wing configuration
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Falanga, R. A.↗
Space shuttle: Stability and control effectiveness of the MDAC parametric delta canard booster at Mach 0.38. Volume 1: Canard parametric variations
A 0.015 scale model of a modified version of the MDAC space shuttle booster was tested in the Naval Ship Research and Development Center 7 x 10 foot transonic wind tunnel, to obtain force, static stability, and control effectiveness data. Data were obtained for a cruise Mach Number of 0.38, altitude of 10,000 ft, and Reynolds Number per foot of approximately 2 x one million. The model was tested through an angle of attack range of -4 deg to 15 deg at zero degree angle of sideslip, and at an angle of sideslip range of -6 deg to 6 deg at fixed angles of attack of 0 deg, 6 deg, and 15 deg. Other test variables were elevon deflections, canard deflections, aileron deflections, rudder deflections, wing dihedral angle, canard incidence angle, wing incidence angle, canard position, wing position, wing and canard control flap size and dorsal fin size.
Bradley, D.↗
Space shuttle: Aerodynamic heating tests of the MDAC delta wing orbiter and canard booster
Design of an efficient thermal protection system for the space shuttle orbiter and booster is discussed, based on knowledge of the thermal environment to be experienced by the vehicles in all flight phases. The complex configurations of these vehicles limit the level of confidence which can be associated with purely analytical thermal environment predictions. Tests were conducted during April and May 1971 using an orbiter and booster model at a 96-in. hypersonic shock tunnel. Both models were tested separately as well as together. A sufficiently large range in Reynolds number was covered so that laminar, transitional, and turbulent data could be obtained.
Andresen, T. L.↗
Surface pressure and inviscid flow field properties of the McDonnell-Douglas delta-wing orbiter for nominal Mach number of 8, Volume 1
The results of a wind tunnel test program to determine the surface pressures and flow distribution on the McDonnell Douglas Orbiter configuration are presented. Tests were conducted in hypersonic wind tunnel at Mach 8. The freestream unit Reynolds number was 3.7 time one million per foot. Angle of attack was varied from 10 degrees to 60 degrees in 10 degree increments.
Warmbrod, J. D.↗