Case 32 :
Total vortex and potential lift coefficients for sharp-edge delta wings at high angles of attack .
Alpha |
Analytical
|
Airloads
|
Experimental
|
|---|---|---|---|
0 |
0
0.0950 0.2300 0.3900 0.5700 0.7600 |
0
0.0870 0.2180 0.3770 0.5450 0.6980 |
0
0.1000 0.2300 0.3850 0.5800 0.7000 |
Alpha |
Analytical
|
Airloads
|
Experimental
|
|---|---|---|---|
0 |
0
0.1350 0.3200 0.5200 0.7400 0.9800 |
0
0.1377 0.3177 0.5242 0.7363 0.9316 |
0
0.1300 0.3000 0.5000 0.7150 0.9200 |
Alpha |
Analytical
|
Airloads
|
Experimental
|
|---|---|---|---|
0 |
0
0.1800 0.3900 0.6350 0.8800 1.1400 |
0
0.1803 0.4000 0.6489 0.8990 1.1300 |
0
0.1800 0.3900 0.6250 0.8900 1.1000 |
Alpha |
Analytical
|
Airloads
|
Experimental
|
|---|---|---|---|
0 |
0 0.2120 0.4600 0.5670 0.7900 0.9000 1.0100 1.2800 |
0
0.2160 0.4741 0.5850 0.8130 0.9280 1.0415 1.3210 |
0 0.2000 0.4400 0.5500 0.7500 0.8500 0.9500 1.0900 |