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Case 30 :

Total vortex and potential lift coefficients for sharp-edge delta wings at high angles of attack .

 

 

 


Alpha
Analytical
Airloads
Experimental

0
5
10
15
20
25

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
5
10
15
20
25

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
5
10
15
20
25

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
5
10
12
16
18
20
25

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

 

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