Analysis of Wind-Tunnel Tests to a Mach Number of 0.90 of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10 Page: 38 of 171
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NACA TN 3790
4. It was possible to predict the effects of propeller normal force
on the longitudinal stability of the model with good accuracy. However,
the propeller slipstream effects on the wing and horizontal tail could not
be predicted with existing methods to any acceptable degree of accuracy.
5. Raising the horizontal tail had little effect on the longitudinal
stability with the propellers removed but was destabilizing with the pro-
6. For an assumed airplane, operating at the power required for
level flight at an altitude of 40,000 feet, calculations indicate only
a small change in the stable variation of tail incidence for trim with
either Mach number or normal acceleration compared to the propellers-off
7. Propulsive efficiencies for the complete model were generally
somewhat higher than the efficiencies of the isolated propeller and
increased with increasing Mach number while the efficiency of the isolated
propeller decreased slightly.
Ames Aeronautical Laboratory
National Advisory Committee for Aeronautics
Moffett Field, Calif., June 14, 1954
1. Edwards, George G., Tinling, Bruce E., and Ackerman, Arthur C.: The
Longitudinal Characteristics at Mach Numbers Up to 0.92 of a Cambered
and Twisted Wing Having 400 of Sweepback and an Aspect Ratio of 10.
NACA Rm A52F18, 1952.
2. Tinling, Bruce E.: The Longitudinal Characteristics at Mach Numbers
Up to 0.9 of a Wing-Fuselage-Tail Combination Having a Wing With
400 of Sweepback and an Aspect Ratio of 10. NACA RM A52119, 1952.
3. Boltz, Frederick W., and Shibata, Harry H.: Pressure Distribution
at Mach Numbers Up to 0.90 on a Cambered and Twisted Wing Having
400 of Sweepback and an Aspect Ratio of 10, Including the Effects
of Fences. NACA RM A52K20, 1953.
4. Tinling, Bruce E., and Lopez, Armando E.: The Effects of Nacelles
and of Extended Split Flaps on the Longitudinal Characteristics of
a Wing-Fuselage-Tail Combination Having a Wing With 100 of Sweepback
and an Aspect Ratio of 10. NACA RM A53D06, 1953.
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Edwards, George G.; Buell, Donald A.; Demele, Fred A. & Sutton, Fred B. Analysis of Wind-Tunnel Tests to a Mach Number of 0.90 of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10, report, September 1956; (https://digital.library.unt.edu/ark:/67531/metadc56014/m1/38/: accessed May 26, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.