| Description: | Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils. |
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| Creator(s): | |
| Creation Date: | April 1, 1946 |
| Partner(s): |
UNT Libraries Government Documents Department
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| Collection(s): |
National Advisory Committee for Aeronautics Collection
Technical Report Archive and Image Library
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| Usage: |
Total Uses: 109
Past 30 days: 10
Yesterday: 1
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| Creator (Author): | ||
| Original Creation Date: | April 1, 1946 | |
| Description: | Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils. |
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| Keyword(s): | aerodynamics | |
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| Serial Title: | NACA Wartime Reports | |
| Serial Title: | NACA Advanced Confidential Report | |
| Serial Title: | NACA Aircraft Circulars | |
| Partner: |
UNT Libraries Government Documents Department
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| Collection: |
National Advisory Committee for Aeronautics Collection
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| Collection: |
Technical Report Archive and Image Library
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| Identifier: |
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| Resource Type: | Report | |
| Format: | Text | |
| Rights: |
Access:
Public
License:
Public Domain
Statement:
No Copyright, Unclassified, Unlimited, Publicly available
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