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NASA-CR-151971
Delta method, an empirical drag buildup technique
Year: 1978
Abstract: An empirical drag correlation technique was developed from analysis of 19 subsonic and supersonic military aircraft and 15 advanced or supercritical airfoil configurations which can be applied in conceptual and advanced aircraft design activities. The Delta Method may be used for estimating the clean wing drag polar for cruise and maneuver conditions up to buffet onset, and to approximately Mach 2.0. This technique incorporates a unique capability of predicting the off-design performance of advanced or supercritical airfoil sections. The buffet onset limit may also be estimated. The method is applicable to wind tunnel models as well as to full scale configurations. This technique has been converted into a computer code for use on the IBM 360 and CDC 7600 computer facilities at NASA AMES. Results obtained using this method to predict known aircraft characteristics are good and agreement can be obtained within a degree of accuracy judged to be sufficient for the initial processes of preliminary design.
Subject: AERODYNAMIC DRAG
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:19:26Z | |
| date available | 2017-09-04T15:19:26Z | |
| date copyright | 01/01/1978 | |
| date issued | 1978 | |
| identifier other | MTHOEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/19229 | |
| description abstract | An empirical drag correlation technique was developed from analysis of 19 subsonic and supersonic military aircraft and 15 advanced or supercritical airfoil configurations which can be applied in conceptual and advanced aircraft design activities. The Delta Method may be used for estimating the clean wing drag polar for cruise and maneuver conditions up to buffet onset, and to approximately Mach 2.0. This technique incorporates a unique capability of predicting the off-design performance of advanced or supercritical airfoil sections. The buffet onset limit may also be estimated. The method is applicable to wind tunnel models as well as to full scale configurations. This technique has been converted into a computer code for use on the IBM 360 and CDC 7600 computer facilities at NASA AMES. Results obtained using this method to predict known aircraft characteristics are good and agreement can be obtained within a degree of accuracy judged to be sufficient for the initial processes of preliminary design. | |
| language | English | |
| title | NASA-CR-151971 | num |
| title | Delta method, an empirical drag buildup technique | en |
| type | standard | |
| page | 184 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1978 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC DRAG | |
| subject keywords | COMPUTER PROGRAMS | |
| subject keywords | CORRELATION | |
| subject keywords | FLIGHT CHARACTERISTICS | |
| subject keywords | GRAPHS (CHARTS) | |
| subject keywords | MILITARY AIRCRAFT | |
| subject keywords | PERFORMANCE PREDICTION | |
| subject keywords | SUPERCRITICAL WINGS |