PRESSURE COEFFICIENT DATA FOR THE GAW WING


	 	  alpha= -2	    0	      2	       4 	  6   	    8

       x         y
    0.0000    0.0000    0.9806    0.9649    0.7188    0.3613   -0.0857   -0.6041
    0.0036   -0.0126    0.0877    0.6065    0.9324    0.9915    0.9436    0.8197
    0.0306   -0.0293   -0.6798   -0.2415    0.2120    0.4841    0.6664    0.8279
    0.0494   -0.0355   -0.5267   -0.1823    0.1670    0.3842    0.5560    0.6844
    0.0735   -0.0418   -0.4879   -0.1999    0.0912    0.2819    0.4320    0.5632
    0.0962   -0.0462   -0.4541   -0.2157    0.0419    0.2089    0.3520    0.4675
    0.1201   -0.0502   -0.4634   -0.2446   -0.0056    0.1525    0.2772    0.3925
    0.1452   -0.0539   -0.4611   -0.2556   -0.0417    0.1070    0.2248    0.3278
    0.1921   -0.0585   -0.4461   -0.2728   -0.0931    0.0428    0.1433    0.2373
    0.2944   -0.0641   -0.4016   -0.2682   -0.1287   -0.0375    0.0505    0.1214
    0.3746   -0.0653   -0.3629   -0.2718   -0.1452   -0.0712   -0.0007    0.0524
    0.4365   -0.0640   -0.3370   -0.2546   -0.1550   -0.0873   -0.0356    0.0143
    0.5023   -0.0609   -0.3200   -0.2360   -0.1690   -0.1140   -0.0632   -0.0162
    0.6130   -0.0486   -0.2089   -0.1767   -0.1020   -0.0605   -0.0302    0.0028
    0.6569   -0.0415   -0.1066   -0.0977   -0.0744   -0.0209    0.0201    0.0403
    0.7093   -0.0322    0.0061    0.0429    0.0608    0.0446    0.0328    0.0620
    0.8004   -0.0158    0.1387    0.1741    0.1990    0.2119    0.2234    0.1533
    0.8348   -0.0105    0.1773    0.2095    0.2277    0.2422    0.2519    0.2825
    0.8759   -0.0056    0.2272    0.2466    0.2583    0.2645    0.2687    0.2775
    0.9367   -0.0023    0.2491    0.2617    0.2848    0.2801    0.2690    0.2477
    1.0000    0.0000    0.1497    0.1422    0.1018    0.0564   -0.0007   -0.0734
    0.9321    0.0177    0.0161    0.0093   -0.0128   -0.0332   -0.0680   -0.1407
    0.8549    0.0386   -0.0607   -0.0792   -0.0878   -0.0830   -0.0928   -0.1184
    0.8059    0.0514   -0.2036   -0.2173   -0.2273   -0.2182   -0.2040   -0.1979
    0.7552    0.0639   -0.3023   -0.3311   -0.3346   -0.3269   -0.3005   -0.2877
    0.7042    0.0755   -0.4144   -0.4554   -0.4569   -0.4474   -0.4450   -0.4116
    0.6551    0.0851   -0.4940   -0.5434   -0.5770   -0.5824   -0.5855   -0.5363
    0.6013    0.0935   -0.5650   -0.6526   -0.6670   -0.6779   -0.7042   -0.6865
    0.5496    0.0992   -0.5863   -0.6530   -0.7208   -0.7446   -0.7903   -0.7880
    0.5003    0.1027   -0.5950   -0.6838   -0.7537   -0.8083   -0.8459   -0.8686
    0.4492    0.1045   -0.5820   -0.6913   -0.8042   -0.8369   -0.9276   -0.9464
    0.3982    0.1047   -0.5738   -0.6873   -0.7977   -0.8679   -0.9529   -1.0104
    0.3503    0.1036   -0.5627   -0.6814   -0.8226   -0.9270   -1.0302   -1.0516
    0.2992    0.1015   -0.5438   -0.6758   -0.8696   -0.9660   -1.0574   -1.1101
    0.2493    0.0979   -0.5398   -0.6926   -0.8993   -1.0141   -1.1320   -1.2434
    0.2040    0.0930   -0.5065   -0.7062   -0.9236   -1.0807   -1.2336   -1.3169
    0.1487    0.0838   -0.4713   -0.7066   -0.9685   -1.1686   -1.4368   -1.5265
    0.1256    0.0792   -0.4632   -0.7247   -0.9953   -1.2303   -1.5037   -1.7480
    0.0980    0.0725   -0.4060   -0.6757   -1.0806   -1.3186   -1.6001   -1.8846
    0.0734    0.0651   -0.3546   -0.6931   -1.0987   -1.3779   -1.7378   -2.0193
    0.0385    0.0503   -0.1560   -0.5660   -1.1218   -1.5052   -2.0273   -2.4798
    0.0207    0.0383    0.1806   -0.2457   -0.9026   -1.4518   -1.9416   -2.5782
    0.0063    0.0227    0.7271    0.3562   -0.2735   -0.8516   -1.5071   -2.2155
    0.0000    0.0000    0.9806    0.9649    0.7188    0.3613   -0.0857   -0.6041