XFOIL Version 6.96 Calculated polar for: SD7003-085-88 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.8808 0.04117 0.03903 -0.0436 1.0000 0.0064 -11.000 -0.9022 0.03646 0.03407 -0.0442 1.0000 0.0063 -10.750 -0.9072 0.03242 0.02971 -0.0443 1.0000 0.0064 -10.500 -0.9040 0.02901 0.02598 -0.0439 1.0000 0.0065 -10.250 -0.8942 0.02628 0.02296 -0.0432 1.0000 0.0065 -10.000 -0.8783 0.02442 0.02087 -0.0426 1.0000 0.0067 -9.750 -0.8602 0.02287 0.01912 -0.0420 1.0000 0.0068 -9.500 -0.8404 0.02159 0.01766 -0.0413 1.0000 0.0069 -9.250 -0.8250 0.01918 0.01492 -0.0404 1.0000 0.0072 -9.000 -0.8068 0.01736 0.01288 -0.0395 1.0000 0.0074 -8.750 -0.7853 0.01630 0.01171 -0.0388 1.0000 0.0077 -8.500 -0.7623 0.01557 0.01090 -0.0382 1.0000 0.0080 -8.250 -0.7392 0.01487 0.01011 -0.0375 1.0000 0.0082 -8.000 -0.7157 0.01420 0.00936 -0.0368 1.0000 0.0085 -7.750 -0.6922 0.01354 0.00860 -0.0361 1.0000 0.0088 -7.500 -0.6684 0.01292 0.00790 -0.0354 1.0000 0.0091 -7.250 -0.6444 0.01236 0.00728 -0.0347 1.0000 0.0094 -7.000 -0.6200 0.01193 0.00678 -0.0340 1.0000 0.0097 -6.750 -0.5971 0.01101 0.00577 -0.0332 1.0000 0.0107 -6.500 -0.5725 0.01065 0.00539 -0.0325 1.0000 0.0116 -6.250 -0.5479 0.01032 0.00502 -0.0318 1.0000 0.0126 -6.000 -0.5237 0.00981 0.00445 -0.0311 1.0000 0.0141 -5.750 -0.4996 0.00945 0.00410 -0.0303 1.0000 0.0161 -5.500 -0.4753 0.00909 0.00370 -0.0295 1.0000 0.0188 -5.250 -0.4508 0.00882 0.00344 -0.0288 1.0000 0.0221 -5.000 -0.4167 0.00849 0.00314 -0.0302 0.9983 0.0271 -4.750 -0.3800 0.00822 0.00289 -0.0321 0.9958 0.0330 -4.500 -0.3435 0.00803 0.00271 -0.0339 0.9933 0.0389 -4.250 -0.3084 0.00776 0.00249 -0.0354 0.9895 0.0475 -4.000 -0.2716 0.00752 0.00230 -0.0373 0.9858 0.0568 -3.750 -0.2341 0.00731 0.00212 -0.0393 0.9824 0.0665 -3.500 -0.2015 0.00710 0.00194 -0.0401 0.9739 0.0765 -3.250 -0.1682 0.00687 0.00176 -0.0412 0.9632 0.0913 -3.000 -0.1354 0.00663 0.00160 -0.0421 0.9475 0.1135 -2.750 -0.1053 0.00641 0.00143 -0.0424 0.9238 0.1432 -2.500 -0.0788 0.00621 0.00129 -0.0419 0.8936 0.1827 -2.250 -0.0530 0.00606 0.00118 -0.0413 0.8624 0.2254 -2.000 -0.0269 0.00593 0.00109 -0.0408 0.8321 0.2713 -1.750 -0.0007 0.00580 0.00101 -0.0403 0.8023 0.3239 -1.500 0.0258 0.00568 0.00095 -0.0400 0.7732 0.3760 -1.250 0.0523 0.00555 0.00089 -0.0396 0.7452 0.4378 -1.000 0.0789 0.00540 0.00086 -0.0393 0.7180 0.5062 -0.750 0.1057 0.00530 0.00084 -0.0390 0.6906 0.5664 -0.500 0.1325 0.00521 0.00084 -0.0387 0.6638 0.6301 -0.250 0.1592 0.00514 0.00085 -0.0383 0.6378 0.6888 0.000 0.1859 0.00513 0.00087 -0.0379 0.6115 0.7351 0.250 0.2124 0.00513 0.00090 -0.0374 0.5853 0.7748 0.500 0.2391 0.00516 0.00093 -0.0370 0.5596 0.8090 0.750 0.2653 0.00519 0.00097 -0.0364 0.5340 0.8402 1.000 0.2911 0.00524 0.00101 -0.0357 0.5095 0.8704 1.250 0.3161 0.00529 0.00106 -0.0349 0.4853 0.9007 1.500 0.3403 0.00534 0.00110 -0.0338 0.4620 0.9318 1.750 0.3681 0.00542 0.00113 -0.0335 0.4381 0.9643 2.000 0.4053 0.00555 0.00116 -0.0355 0.4109 0.9923 2.250 0.4350 0.00570 0.00121 -0.0358 0.3879 1.0000 2.500 0.4621 0.00588 0.00129 -0.0357 0.3646 1.0000 2.750 0.4895 0.00604 0.00136 -0.0355 0.3438 1.0000 3.250 0.5441 0.00641 0.00156 -0.0352 0.3007 1.0000 3.500 0.5714 0.00660 0.00166 -0.0350 0.2814 1.0000 3.750 0.5986 0.00681 0.00178 -0.0349 0.2609 1.0000 4.000 0.6258 0.00701 0.00192 -0.0347 0.2422 1.0000 4.250 0.6529 0.00724 0.00206 -0.0346 0.2225 1.0000 4.500 0.6800 0.00747 0.00222 -0.0344 0.2056 1.0000 4.750 0.7071 0.00770 0.00239 -0.0342 0.1890 1.0000 5.000 0.7341 0.00793 0.00256 -0.0341 0.1742 1.0000 5.250 0.7611 0.00816 0.00275 -0.0339 0.1601 1.0000 5.500 0.7879 0.00842 0.00295 -0.0337 0.1458 1.0000 5.750 0.8146 0.00869 0.00317 -0.0335 0.1319 1.0000 6.000 0.8411 0.00899 0.00340 -0.0333 0.1162 1.0000 6.250 0.8676 0.00929 0.00364 -0.0331 0.1036 1.0000 6.500 0.8940 0.00959 0.00390 -0.0328 0.0932 1.0000 7.000 0.9465 0.01022 0.00446 -0.0323 0.0741 1.0000 7.250 0.9727 0.01054 0.00476 -0.0321 0.0653 1.0000 7.500 0.9985 0.01090 0.00510 -0.0318 0.0569 1.0000 7.750 1.0240 0.01130 0.00546 -0.0315 0.0486 1.0000 8.000 1.0497 0.01167 0.00581 -0.0312 0.0422 1.0000 8.250 1.0748 0.01210 0.00623 -0.0308 0.0349 1.0000 8.500 1.0994 0.01263 0.00672 -0.0304 0.0274 1.0000 8.750 1.1234 0.01322 0.00730 -0.0299 0.0216 1.0000 9.000 1.1478 0.01374 0.00783 -0.0294 0.0189 1.0000 9.250 1.1711 0.01444 0.00857 -0.0287 0.0166 1.0000 9.500 1.1955 0.01490 0.00909 -0.0283 0.0156 1.0000 9.750 1.2193 0.01543 0.00966 -0.0278 0.0146 1.0000 10.000 1.2419 0.01611 0.01040 -0.0271 0.0135 1.0000 10.250 1.2619 0.01715 0.01154 -0.0262 0.0124 1.0000 10.500 1.2850 0.01769 0.01216 -0.0256 0.0121 1.0000 10.750 1.3072 0.01830 0.01285 -0.0249 0.0116 1.0000 11.000 1.3289 0.01895 0.01356 -0.0242 0.0111 1.0000 11.250 1.3499 0.01964 0.01431 -0.0235 0.0105 1.0000 11.500 1.3694 0.02047 0.01521 -0.0226 0.0100 1.0000 11.750 1.3837 0.02181 0.01666 -0.0211 0.0094 1.0000 12.000 1.3960 0.02325 0.01824 -0.0194 0.0090 1.0000 12.250 1.4140 0.02401 0.01910 -0.0184 0.0088 1.0000 12.500 1.4296 0.02493 0.02011 -0.0171 0.0086 1.0000 12.750 1.4429 0.02597 0.02125 -0.0156 0.0083 1.0000 13.000 1.4550 0.02697 0.02234 -0.0140 0.0080 1.0000 13.250 1.4601 0.02809 0.02356 -0.0114 0.0078 1.0000 13.500 1.4627 0.02933 0.02490 -0.0088 0.0076 1.0000 13.750 1.4637 0.03079 0.02645 -0.0067 0.0074 1.0000 14.000 1.4628 0.03261 0.02837 -0.0050 0.0073 1.0000 14.250 1.4577 0.03509 0.03096 -0.0040 0.0072 1.0000 14.500 1.4503 0.03823 0.03423 -0.0040 0.0070 1.0000 14.750 1.4416 0.04206 0.03817 -0.0050 0.0069 1.0000 15.000 1.4220 0.04794 0.04423 -0.0076 0.0067 1.0000 15.250 1.4065 0.05392 0.05036 -0.0108 0.0067 1.0000 15.500 1.3852 0.06124 0.05784 -0.0150 0.0066 1.0000 15.750 1.3663 0.06847 0.06523 -0.0191 0.0066 1.0000 16.000 1.3419 0.07689 0.07379 -0.0240 0.0066 1.0000 16.250 1.3275 0.08374 0.08075 -0.0279 0.0067 1.0000 16.500 1.3064 0.09197 0.08911 -0.0326 0.0067 1.0000 16.750 1.2847 0.10059 0.09786 -0.0376 0.0067 1.0000