PROGRAM PANELv2 Revised version of Moran code modifications by W.H. Mason INPUT NLOWER,NUPPER (nupper and nlower MUST be equal, and nupper + nlower MUST be less than 100) 40,40 for internally generated ordinates, enter 0 to read an external file of ordinates, enter 1 1 Enter name of file to be read: gaw1.pan Input file name:gaw1.pan File title: GAW1 - THEORETICAL ORDINATES NU = 38 NL = 38 Upper surface ordinates index X/C Y/C 38 0.000000 0.000000 39 0.002000 0.013000 40 0.005000 0.020350 41 0.012500 0.030690 42 0.025000 0.041650 43 0.037500 0.049740 44 0.050000 0.056000 45 0.075000 0.065610 46 0.100000 0.073090 47 0.125000 0.079090 48 0.150000 0.084130 49 0.175000 0.088480 50 0.200000 0.092090 51 0.250000 0.097780 52 0.300000 0.101690 53 0.350000 0.104090 54 0.400000 0.105000 55 0.450000 0.104560 56 0.500000 0.102690 57 0.550000 0.099170 58 0.575000 0.096740 59 0.600000 0.093740 60 0.625000 0.090130 61 0.650000 0.086040 62 0.675000 0.081440 63 0.700000 0.076390 64 0.725000 0.070960 65 0.750000 0.065170 66 0.775000 0.059130 67 0.800000 0.052910 68 0.825000 0.046440 69 0.850000 0.039830 70 0.875000 0.033130 71 0.900000 0.026390 72 0.925000 0.019650 73 0.950000 0.012870 74 0.975000 0.006040 75 1.000000 -0.000740 Lower surface ordinates index X/C Y/C 38 0.000000 0.000000 37 0.002000 -0.009740 36 0.005000 -0.014440 35 0.012500 -0.020520 34 0.025000 -0.026910 33 0.037500 -0.031910 32 0.050000 -0.035690 31 0.075000 -0.042090 30 0.100000 -0.047000 29 0.125000 -0.050870 28 0.150000 -0.054260 27 0.175000 -0.057000 26 0.200000 -0.059260 25 0.250000 -0.062650 24 0.300000 -0.064480 23 0.350000 -0.065170 22 0.400000 -0.064830 21 0.450000 -0.063440 20 0.500000 -0.060910 19 0.550000 -0.056830 18 0.575000 -0.053960 17 0.600000 -0.050610 16 0.625000 -0.046780 15 0.650000 -0.042650 14 0.675000 -0.038300 13 0.700000 -0.033830 12 0.725000 -0.029300 11 0.750000 -0.024610 10 0.775000 -0.020300 9 0.800000 -0.015870 8 0.825000 -0.011910 7 0.850000 -0.008520 6 0.875000 -0.005650 5 0.900000 -0.003520 4 0.925000 -0.002480 3 0.950000 -0.002570 2 0.975000 -0.003960 1 1.000000 -0.007830 internally generated estimate of leading edge point X(IN)= 0.00200 Y(IN)= -0.00974 IN= 37 XC= 0.02136 YC= -0.00069 leading edge radious, RN = 0.02137 Airfoil shape after interpolation in slopy2 I X Y dY/dX 1 1.00000 -0.00783 -0.20440 2 0.99846 -0.00752 -0.19879 3 0.99384 -0.00664 -0.18137 4 0.98618 -0.00537 -0.15044 5 0.97553 -0.00401 -0.10315 6 0.96194 -0.00300 -0.05058 7 0.94550 -0.00248 -0.01697 8 0.92632 -0.00246 0.01577 9 0.90451 -0.00325 0.05653 10 0.88020 -0.00513 0.09610 11 0.85355 -0.00808 0.12293 12 0.82472 -0.01195 0.14645 13 0.79389 -0.01694 0.17692 14 0.76125 -0.02265 0.17042 15 0.72700 -0.02893 0.18827 16 0.69134 -0.03538 0.17927 17 0.65451 -0.04188 0.17160 18 0.61672 -0.04809 0.15625 19 0.57822 -0.05356 0.12693 20 0.53923 -0.05789 0.09288 21 0.50000 -0.06091 0.06366 22 0.46077 -0.06300 0.04346 23 0.42178 -0.06436 0.02638 24 0.38328 -0.06506 0.01022 25 0.34549 -0.06515 -0.00540 26 0.30866 -0.06467 -0.02049 27 0.27300 -0.06366 -0.03711 28 0.23875 -0.06203 -0.05922 29 0.20611 -0.05976 -0.07942 30 0.17528 -0.05703 -0.09830 31 0.14645 -0.05381 -0.12751 32 0.11980 -0.05011 -0.14721 33 0.09549 -0.04621 -0.17860 34 0.07368 -0.04179 -0.23093 35 0.05450 -0.03693 -0.27172 36 0.03806 -0.03210 -0.34047 37 0.02447 -0.02667 -0.44665 38 0.01382 -0.02131 -0.58795 39 0.00616 -0.01569 -0.99951 40 0.00154 -0.00864 -2.62162 41 0.00000 0.00000 -51.15408 42 0.00154 0.01144 51.67010 43 0.00616 0.02240 3.61813 44 0.01382 0.03207 1.65629 45 0.02447 0.04126 1.02313 46 0.03806 0.05005 0.74407 47 0.05450 0.05796 0.55767 48 0.07368 0.06517 0.42184 49 0.09549 0.07186 0.33808 50 0.11980 0.07794 0.27773 51 0.14645 0.08346 0.22582 52 0.17528 0.08852 0.19111 53 0.20611 0.09289 0.15839 54 0.23875 0.09666 0.12792 55 0.27300 0.09978 0.10354 56 0.30866 0.10221 0.07915 57 0.34549 0.10394 0.05769 58 0.38328 0.10485 0.03569 59 0.42178 0.10497 0.01334 60 0.46077 0.10429 -0.00698 61 0.50000 0.10269 -0.02859 62 0.53923 0.10007 -0.05335 63 0.57822 0.09639 -0.08013 64 0.61672 0.09138 -0.11084 65 0.65451 0.08525 -0.14833 66 0.69134 0.07818 -0.17759 67 0.72700 0.07051 -0.20459 68 0.76125 0.06248 -0.22600 69 0.79389 0.05445 -0.24141 70 0.82472 0.04651 -0.25101 71 0.85355 0.03888 -0.26228 72 0.88020 0.03173 -0.26695 73 0.90451 0.02517 -0.26948 74 0.92632 0.01929 -0.26948 75 0.94550 0.01409 -0.27014 76 0.96194 0.00961 -0.27205 77 0.97553 0.00590 -0.27349 78 0.98618 0.00300 -0.27251 79 0.99384 0.00092 -0.27123 80 0.99846 -0.00032 -0.27057 81 1.00000 -0.00074 -0.27028 do you want to modify this airfoil? (Y/N): y do you want to add a bump to this airfoil? (Y/N): y upper (1) or lower(0) surface? 1 input begining, middle and end of bump .02,.5,.9 input size of bump: + adds to thickness - subtracts from thickness .04 Airfoil modification I X/C Y/C baseline delta Y/C Y/C 41 0.00000 0.00000 0.00000 0.00000 42 0.00154 0.01144 0.00000 0.01144 43 0.00616 0.02240 0.00000 0.02240 44 0.01382 0.03207 0.00000 0.03207 45 0.02447 0.04126 0.00000 0.04126 46 0.03806 0.05005 0.00002 0.05007 47 0.05450 0.05796 0.00011 0.05806 48 0.07368 0.06517 0.00038 0.06554 49 0.09549 0.07186 0.00097 0.07284 50 0.11980 0.07794 0.00207 0.08001 51 0.14645 0.08346 0.00383 0.08729 52 0.17528 0.08852 0.00638 0.09490 53 0.20611 0.09289 0.00977 0.10266 54 0.23875 0.09666 0.01394 0.11061 55 0.27300 0.09978 0.01872 0.11850 56 0.30866 0.10221 0.02380 0.12601 57 0.34549 0.10394 0.02881 0.13275 58 0.38328 0.10485 0.03332 0.13817 59 0.42178 0.10497 0.03690 0.14187 60 0.46077 0.10429 0.03920 0.14349 61 0.50000 0.10269 0.04000 0.14269 62 0.53923 0.10007 0.03886 0.13893 63 0.57822 0.09639 0.03558 0.13197 64 0.61672 0.09138 0.03063 0.12201 65 0.65451 0.08525 0.02463 0.10988 66 0.69134 0.07818 0.01835 0.09653 67 0.72700 0.07051 0.01246 0.08297 68 0.76125 0.06248 0.00754 0.07002 69 0.79389 0.05445 0.00390 0.05835 70 0.82472 0.04651 0.00159 0.04810 71 0.85355 0.03888 0.00042 0.03930 72 0.88020 0.03173 0.00004 0.03176 73 0.90451 0.02517 0.00000 0.02517 74 0.92632 0.01929 0.00000 0.01929 75 0.94550 0.01409 0.00000 0.01409 76 0.96194 0.00961 0.00000 0.00961 77 0.97553 0.00590 0.00000 0.00590 78 0.98618 0.00300 0.00000 0.00300 79 0.99384 0.00092 0.00000 0.00092 80 0.99846 -0.00032 0.00000 -0.00032 do you want to deflect the trailing edge? (Y/N): y What is the x/c of the start of the deflection? .75 what is the deflection, in degrees? 10. Lower Surface deflected i x(i) y-old delta y y-new 1 1.00000 -0.00783 0.04408 -0.05191 2 0.99846 -0.00752 0.04381 -0.05133 3 0.99384 -0.00664 0.04300 -0.04964 4 0.98618 -0.00537 0.04165 -0.04702 5 0.97553 -0.00401 0.03977 -0.04378 6 0.96194 -0.00300 0.03737 -0.04037 7 0.94550 -0.00248 0.03447 -0.03695 8 0.92632 -0.00246 0.03109 -0.03355 9 0.90451 -0.00325 0.02724 -0.03049 10 0.88020 -0.00513 0.02296 -0.02809 11 0.85355 -0.00808 0.01826 -0.02634 12 0.82472 -0.01195 0.01318 -0.02513 13 0.79389 -0.01694 0.00774 -0.02468 14 0.76125 -0.02265 0.00198 -0.02464 Upper Surface deflected i x(i) y-old delta y y-new 68 0.76125 0.07002 0.00198 0.06803 69 0.79389 0.05835 0.00774 0.05061 70 0.82472 0.04810 0.01318 0.03492 71 0.85355 0.03930 0.01826 0.02104 72 0.88020 0.03176 0.02296 0.00881 73 0.90451 0.02517 0.02724 -0.00207 74 0.92632 0.01929 0.03109 -0.01180 75 0.94550 0.01409 0.03447 -0.02038 76 0.96194 0.00961 0.03737 -0.02776 77 0.97553 0.00590 0.03977 -0.03387 78 0.98618 0.00300 0.04165 -0.03865 79 0.99384 0.00092 0.04300 -0.04207 80 0.99846 -0.00032 0.04381 -0.04413 81 1.00000 -0.00074 0.04408 -0.04482 setting up coefficient matrix - takes some time Computing LU decomposition - may take awhile input alpha in degrees 0. Pressure and Velocity distributions I X Y CP U/Ue 1 0.9992 -0.0516 0.37763 -0.7889 2 0.9962 -0.0505 0.45708 -0.7368 3 0.9900 -0.0483 0.53402 -0.6826 4 0.9809 -0.0454 0.55667 -0.6658 5 0.9687 -0.0421 0.53751 -0.6801 6 0.9537 -0.0387 0.51304 -0.6978 7 0.9359 -0.0352 0.50776 -0.7016 8 0.9154 -0.0320 0.50451 -0.7039 9 0.8924 -0.0293 0.49611 -0.7099 10 0.8669 -0.0272 0.48838 -0.7153 11 0.8391 -0.0257 0.48631 -0.7167 12 0.8093 -0.0249 0.48368 -0.7186 13 0.7776 -0.0247 0.51496 -0.6965 14 0.7441 -0.0268 0.48013 -0.7210 15 0.7092 -0.0322 0.40968 -0.7683 16 0.6729 -0.0386 0.33108 -0.8179 17 0.6356 -0.0450 0.26092 -0.8597 18 0.5975 -0.0508 0.19781 -0.8957 19 0.5587 -0.0557 0.14895 -0.9225 20 0.5196 -0.0594 0.12263 -0.9367 21 0.4804 -0.0620 0.11325 -0.9417 22 0.4413 -0.0637 0.10923 -0.9438 23 0.4025 -0.0647 0.10799 -0.9445 24 0.3644 -0.0651 0.10961 -0.9436 25 0.3271 -0.0649 0.11382 -0.9414 26 0.2908 -0.0642 0.11916 -0.9385 27 0.2559 -0.0628 0.12851 -0.9335 28 0.2224 -0.0609 0.14645 -0.9239 29 0.1907 -0.0584 0.16864 -0.9118 30 0.1609 -0.0554 0.19500 -0.8972 31 0.1331 -0.0520 0.23201 -0.8763 32 0.1076 -0.0482 0.26794 -0.8556 33 0.0846 -0.0440 0.31759 -0.8261 34 0.0641 -0.0394 0.39187 -0.7798 35 0.0463 -0.0345 0.46303 -0.7328 36 0.0313 -0.0294 0.57954 -0.6484 37 0.0191 -0.0240 0.70705 -0.5412 38 0.0100 -0.0185 0.86176 -0.3718 39 0.0038 -0.0122 0.99962 -0.0196 40 0.0008 -0.0043 0.81049 0.4353 41 0.0008 0.0057 0.29580 0.8392 42 0.0038 0.0169 -0.42407 1.1933 43 0.0100 0.0272 -1.05194 1.4325 44 0.0191 0.0367 -1.30777 1.5191 45 0.0313 0.0457 -1.40822 1.5518 46 0.0463 0.0541 -1.39680 1.5482 47 0.0641 0.0618 -1.29021 1.5133 48 0.0846 0.0692 -1.18736 1.4790 49 0.1076 0.0764 -1.10614 1.4513 50 0.1331 0.0836 -1.04696 1.4307 51 0.1609 0.0911 -1.03033 1.4249 52 0.1907 0.0988 -1.04766 1.4310 53 0.2224 0.1066 -1.09252 1.4466 54 0.2559 0.1146 -1.17298 1.4741 55 0.2908 0.1223 -1.28043 1.5101 56 0.3271 0.1294 -1.40974 1.5523 57 0.3644 0.1355 -1.54676 1.5959 58 0.4025 0.1400 -1.67346 1.6351 59 0.4413 0.1427 -1.78036 1.6674 60 0.4804 0.1431 -1.85955 1.6910 61 0.5196 0.1408 -1.87643 1.6960 62 0.5587 0.1355 -1.78839 1.6698 63 0.5975 0.1270 -1.59340 1.6104 64 0.6356 0.1159 -1.34951 1.5328 65 0.6729 0.1032 -1.12062 1.4562 66 0.7092 0.0898 -0.98347 1.4084 67 0.7441 0.0755 -0.85019 1.3602 68 0.7776 0.0593 -0.53604 1.2394 69 0.8093 0.0428 -0.32002 1.1489 70 0.8391 0.0280 -0.19968 1.0953 71 0.8669 0.0149 -0.12618 1.0612 72 0.8924 0.0034 -0.07229 1.0355 73 0.9154 -0.0069 -0.02233 1.0111 74 0.9359 -0.0161 0.02161 0.9891 75 0.9537 -0.0241 0.05928 0.9699 76 0.9687 -0.0308 0.08434 0.9569 77 0.9809 -0.0363 0.09935 0.9490 78 0.9900 -0.0404 0.14105 0.9268 79 0.9962 -0.0431 0.23806 0.8729 80 0.9992 -0.0445 0.37763 0.7889 I X Y CP U/Ue AT ALPHA = 0.000 CL = 1.36463 CM(l.e.) = -0.60306 Cm(c/4) = -0.26190 CD = -0.00236 (theoretically zero) send output to a file? (Y/N): y enter file name: gaw1.out enter file title: feb 22, 1995 test gaw1, us mod, te deflected Another angle of attack? (Y/N): n STOP