XFOIL Version 6.96 Calculated polar for: KC-135 BL200.76 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4875 0.08048 0.07888 -0.0338 1.0000 0.0106 -9.000 -0.4988 0.07415 0.07258 -0.0403 1.0000 0.0106 -8.750 -0.5154 0.06987 0.06826 -0.0427 1.0000 0.0105 -8.500 -0.5322 0.06662 0.06498 -0.0413 1.0000 0.0106 -8.250 -0.5409 0.06313 0.06143 -0.0404 1.0000 0.0107 -8.000 -0.5473 0.05989 0.05811 -0.0387 1.0000 0.0110 -7.750 -0.5318 0.05479 0.05279 -0.0402 0.9938 0.0120 -7.500 -0.5131 0.05017 0.04799 -0.0424 0.9845 0.0121 -6.750 -0.4538 0.03417 0.03116 -0.0487 0.9443 0.0128 -6.500 -0.4324 0.03252 0.02936 -0.0489 0.9236 0.0133 -4.750 -0.2994 0.01413 0.00879 -0.0365 0.8310 0.0146 -4.500 -0.2746 0.01289 0.00737 -0.0357 0.8232 0.0150 -4.250 -0.2497 0.01203 0.00639 -0.0351 0.8151 0.0154 -4.000 -0.2249 0.01137 0.00563 -0.0345 0.8077 0.0159 -3.750 -0.1990 0.01110 0.00530 -0.0341 0.8001 0.0163 -3.500 -0.1788 0.00992 0.00403 -0.0326 0.7932 0.0177 -3.250 -0.1541 0.00957 0.00365 -0.0321 0.7860 0.0184 -3.000 -0.1293 0.00927 0.00329 -0.0315 0.7794 0.0192 -2.750 -0.1039 0.00899 0.00299 -0.0310 0.7725 0.0203 -2.500 -0.0786 0.00875 0.00269 -0.0305 0.7663 0.0213 -2.250 -0.0532 0.00846 0.00235 -0.0301 0.7598 0.0227 -2.000 -0.0280 0.00819 0.00204 -0.0296 0.7536 0.0256 -1.750 -0.0014 0.00805 0.00188 -0.0293 0.7475 0.0283 -1.500 0.0246 0.00787 0.00164 -0.0289 0.7406 0.0321 -1.250 0.0510 0.00773 0.00150 -0.0287 0.7333 0.0383 -1.000 0.0774 0.00761 0.00137 -0.0284 0.7261 0.0492 -0.750 0.1015 0.00720 0.00124 -0.0278 0.7186 0.1566 -0.500 0.1110 0.00552 0.00102 -0.0249 0.7111 0.6328 -0.250 0.1362 0.00540 0.00102 -0.0243 0.7031 0.6795 0.250 0.1885 0.00532 0.00100 -0.0235 0.6859 0.7247 0.500 0.2150 0.00530 0.00100 -0.0233 0.6801 0.7422 0.750 0.2420 0.00526 0.00101 -0.0231 0.6743 0.7590 1.000 0.2682 0.00522 0.00102 -0.0227 0.6676 0.7801 1.250 0.2945 0.00518 0.00104 -0.0224 0.6610 0.8001 1.500 0.3213 0.00516 0.00106 -0.0222 0.6541 0.8142 1.750 0.3478 0.00514 0.00109 -0.0219 0.6465 0.8307 2.000 0.3741 0.00513 0.00112 -0.0216 0.6382 0.8494 2.250 0.4005 0.00511 0.00116 -0.0212 0.6294 0.8695 2.500 0.4267 0.00511 0.00121 -0.0208 0.6188 0.8916 2.750 0.4536 0.00513 0.00128 -0.0206 0.6063 0.9141 3.000 0.4829 0.00519 0.00136 -0.0209 0.5916 0.9341 3.250 0.5149 0.00528 0.00144 -0.0219 0.5730 0.9493 3.500 0.5481 0.00545 0.00154 -0.0232 0.5437 0.9602 3.750 0.5776 0.00584 0.00168 -0.0239 0.4771 0.9705 4.000 0.6093 0.00656 0.00197 -0.0254 0.3760 0.9759 4.250 0.6372 0.00710 0.00224 -0.0259 0.3119 0.9834 4.500 0.6708 0.00759 0.00249 -0.0276 0.2582 0.9866 4.750 0.7037 0.00797 0.00273 -0.0292 0.2243 0.9904 5.000 0.7360 0.00827 0.00295 -0.0305 0.2036 0.9942 5.250 0.7706 0.00858 0.00316 -0.0324 0.1789 0.9969 5.500 0.8043 0.00899 0.00341 -0.0342 0.1422 0.9994 5.750 0.8244 0.00959 0.00377 -0.0332 0.0962 1.0000 6.000 0.8374 0.01033 0.00423 -0.0307 0.0479 1.0000 6.250 0.8552 0.01076 0.00460 -0.0289 0.0346 1.0000 6.500 0.8740 0.01116 0.00497 -0.0273 0.0283 1.0000 6.750 0.8945 0.01145 0.00529 -0.0260 0.0258 1.0000 7.000 0.9132 0.01189 0.00573 -0.0244 0.0223 1.0000 7.250 0.9330 0.01225 0.00614 -0.0230 0.0203 1.0000 7.500 0.9534 0.01258 0.00649 -0.0218 0.0186 1.0000 7.750 0.9720 0.01306 0.00697 -0.0203 0.0165 1.0000 8.000 0.9900 0.01359 0.00757 -0.0186 0.0150 1.0000 8.250 1.0102 0.01394 0.00795 -0.0174 0.0141 1.0000 8.500 1.0294 0.01437 0.00841 -0.0160 0.0132 1.0000 8.750 1.0475 0.01487 0.00893 -0.0145 0.0122 1.0000 9.000 1.0576 0.01597 0.01013 -0.0117 0.0112 1.0000 9.250 1.0755 0.01645 0.01069 -0.0102 0.0110 1.0000 9.500 1.0928 0.01698 0.01127 -0.0086 0.0106 1.0000 9.750 1.1074 0.01767 0.01204 -0.0066 0.0103 1.0000 10.000 1.1229 0.01827 0.01269 -0.0048 0.0099 1.0000 10.250 1.1346 0.01893 0.01342 -0.0024 0.0096 1.0000 10.500 1.1470 0.01950 0.01403 -0.0001 0.0092 1.0000 10.750 1.1588 0.02013 0.01472 0.0022 0.0089 1.0000 11.000 1.1681 0.02097 0.01562 0.0046 0.0085 1.0000 11.250 1.1715 0.02232 0.01706 0.0076 0.0083 1.0000 11.500 1.1671 0.02451 0.01942 0.0113 0.0080 1.0000 11.750 1.1782 0.02540 0.02040 0.0129 0.0078 1.0000 12.000 1.1859 0.02665 0.02176 0.0147 0.0077 1.0000 12.250 1.1942 0.02786 0.02309 0.0163 0.0076 1.0000 12.500 1.2006 0.02930 0.02464 0.0179 0.0074 1.0000 12.750 1.2052 0.03095 0.02641 0.0194 0.0073 1.0000 13.000 1.2066 0.03300 0.02862 0.0209 0.0073 1.0000 13.250 1.2084 0.03503 0.03077 0.0221 0.0071 1.0000 13.500 1.2116 0.03693 0.03279 0.0230 0.0070 1.0000 13.750 1.2142 0.03895 0.03492 0.0236 0.0068 1.0000 14.000 1.2089 0.04198 0.03811 0.0243 0.0068 1.0000 14.250 1.2030 0.04515 0.04144 0.0247 0.0067 1.0000 14.500 1.1960 0.04860 0.04504 0.0246 0.0066 1.0000 14.750 1.1910 0.05194 0.04851 0.0242 0.0065 1.0000 15.000 1.1804 0.05615 0.05287 0.0233 0.0065 1.0000 15.250 1.1821 0.05897 0.05575 0.0221 0.0063 1.0000 15.500 1.1624 0.06499 0.06198 0.0202 0.0064 1.0000 15.750 1.1568 0.06935 0.06643 0.0180 0.0063 1.0000 16.000 1.1176 0.07960 0.07696 0.0135 0.0065 1.0000 16.250 1.1224 0.08286 0.08025 0.0113 0.0063 1.0000 16.500 1.0872 0.09377 0.09140 0.0055 0.0064 1.0000 16.750 1.0688 0.10191 0.09966 0.0008 0.0063 1.0000 17.000 1.0145 0.11834 0.11635 -0.0081 0.0067 1.0000 17.250 0.9600 0.13634 0.13455 -0.0178 0.0069 1.0000