XFOIL Version 6.96 Calculated polar for: LOCKHEED L-188 TIP 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -1.0811 0.04804 0.04508 -0.0815 1.0000 0.0089 -15.750 -1.1017 0.04117 0.03801 -0.0871 1.0000 0.0089 -15.500 -1.1104 0.03691 0.03360 -0.0899 1.0000 0.0090 -15.250 -1.1143 0.03377 0.03033 -0.0914 1.0000 0.0090 -15.000 -1.1152 0.03141 0.02784 -0.0917 1.0000 0.0091 -14.750 -1.1070 0.02946 0.02577 -0.0926 0.9905 0.0092 -14.500 -1.0949 0.02788 0.02407 -0.0929 0.9810 0.0093 -14.250 -1.0838 0.02664 0.02271 -0.0922 0.9719 0.0094 -14.000 -1.0710 0.02552 0.02148 -0.0912 0.9648 0.0096 -13.750 -1.0568 0.02450 0.02035 -0.0903 0.9587 0.0097 -13.500 -1.0411 0.02355 0.01928 -0.0894 0.9535 0.0098 -13.250 -1.0241 0.02266 0.01828 -0.0885 0.9483 0.0100 -13.000 -1.0062 0.02183 0.01734 -0.0877 0.9439 0.0102 -12.750 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0.8873 0.0160 -8.000 -0.5274 0.01179 0.00597 -0.0819 0.8844 0.0163 -7.750 -0.5011 0.01144 0.00558 -0.0817 0.8816 0.0170 -7.500 -0.4745 0.01115 0.00526 -0.0816 0.8789 0.0176 -7.250 -0.4474 0.01088 0.00498 -0.0816 0.8763 0.0184 -7.000 -0.4201 0.01064 0.00471 -0.0816 0.8735 0.0191 -6.750 -0.3927 0.01042 0.00446 -0.0817 0.8703 0.0199 -6.500 -0.3657 0.01014 0.00417 -0.0816 0.8673 0.0210 -6.250 -0.3384 0.00992 0.00393 -0.0816 0.8643 0.0221 -6.000 -0.3109 0.00972 0.00371 -0.0816 0.8614 0.0232 -5.500 -0.2556 0.00930 0.00328 -0.0817 0.8546 0.0260 -5.250 -0.2278 0.00913 0.00309 -0.0817 0.8510 0.0278 -5.000 -0.2002 0.00895 0.00290 -0.0817 0.8476 0.0297 -4.750 -0.1723 0.00878 0.00273 -0.0818 0.8441 0.0321 -4.500 -0.1442 0.00863 0.00257 -0.0819 0.8400 0.0343 -4.250 -0.1164 0.00846 0.00241 -0.0820 0.8356 0.0375 -4.000 -0.0884 0.00833 0.00227 -0.0820 0.8315 0.0410 -3.750 -0.0603 0.00817 0.00214 -0.0821 0.8272 0.0457 -3.500 -0.0323 0.00803 0.00201 -0.0822 0.8220 0.0509 -3.250 -0.0043 0.00791 0.00189 -0.0822 0.8169 0.0569 -3.000 0.0238 0.00777 0.00178 -0.0823 0.8117 0.0649 -2.750 0.0519 0.00763 0.00168 -0.0824 0.8056 0.0750 -2.500 0.0798 0.00752 0.00158 -0.0825 0.7998 0.0867 -2.250 0.1079 0.00739 0.00150 -0.0826 0.7932 0.1021 -2.000 0.1357 0.00726 0.00141 -0.0826 0.7865 0.1218 -1.750 0.1635 0.00712 0.00135 -0.0827 0.7800 0.1489 -1.500 0.1911 0.00697 0.00128 -0.0827 0.7727 0.1826 -1.250 0.2186 0.00677 0.00122 -0.0827 0.7661 0.2310 -0.750 0.2720 0.00619 0.00110 -0.0827 0.7520 0.3957 -0.500 0.2985 0.00588 0.00108 -0.0826 0.7448 0.4976 -0.250 0.3256 0.00574 0.00109 -0.0825 0.7381 0.5557 0.000 0.3535 0.00566 0.00111 -0.0825 0.7310 0.5953 0.250 0.3811 0.00563 0.00113 -0.0825 0.7238 0.6252 0.500 0.4085 0.00561 0.00116 -0.0823 0.7125 0.6547 0.750 0.4342 0.00566 0.00121 -0.0819 0.6896 0.6875 1.250 0.4851 0.00582 0.00134 -0.0808 0.6391 0.7477 1.500 0.5119 0.00593 0.00140 -0.0806 0.6199 0.7570 1.750 0.5384 0.00605 0.00146 -0.0803 0.5995 0.7650 2.000 0.5646 0.00620 0.00153 -0.0800 0.5770 0.7737 2.250 0.5904 0.00636 0.00163 -0.0796 0.5513 0.7819 2.500 0.6156 0.00658 0.00173 -0.0791 0.5199 0.7913 2.750 0.6394 0.00687 0.00188 -0.0784 0.4772 0.8005 3.000 0.6609 0.00733 0.00209 -0.0773 0.4135 0.8110 3.250 0.6817 0.00784 0.00235 -0.0761 0.3491 0.8239 3.500 0.7032 0.00825 0.00260 -0.0751 0.2979 0.8408 3.750 0.7245 0.00857 0.00283 -0.0739 0.2550 0.8705 4.000 0.7462 0.00882 0.00309 -0.0726 0.2198 0.9382 4.250 0.7817 0.00922 0.00335 -0.0746 0.1858 0.9855 4.500 0.8108 0.00958 0.00357 -0.0752 0.1600 1.0000 4.750 0.8337 0.00988 0.00378 -0.0744 0.1418 1.0000 5.000 0.8569 0.01017 0.00399 -0.0736 0.1262 1.0000 5.250 0.8801 0.01046 0.00420 -0.0729 0.1122 1.0000 5.500 0.9032 0.01076 0.00443 -0.0721 0.1002 1.0000 5.750 0.9266 0.01104 0.00466 -0.0714 0.0902 1.0000 6.000 0.9501 0.01130 0.00489 -0.0707 0.0827 1.0000 6.250 0.9730 0.01160 0.00514 -0.0699 0.0747 1.0000 6.500 0.9961 0.01189 0.00540 -0.0691 0.0682 1.0000 6.750 1.0189 0.01218 0.00566 -0.0684 0.0628 1.0000 7.000 1.0414 0.01249 0.00594 -0.0675 0.0573 1.0000 7.250 1.0639 0.01279 0.00623 -0.0667 0.0532 1.0000 7.500 1.0859 0.01311 0.00652 -0.0658 0.0493 1.0000 7.750 1.1072 0.01344 0.00684 -0.0647 0.0457 1.0000 8.000 1.1278 0.01375 0.00715 -0.0635 0.0428 1.0000 8.250 1.1474 0.01411 0.00749 -0.0622 0.0398 1.0000 8.500 1.1676 0.01445 0.00784 -0.0610 0.0379 1.0000 8.750 1.1875 0.01481 0.00821 -0.0598 0.0358 1.0000 9.000 1.2065 0.01523 0.00862 -0.0584 0.0333 1.0000 9.250 1.2263 0.01561 0.00902 -0.0572 0.0318 1.0000 9.500 1.2457 0.01603 0.00945 -0.0560 0.0302 1.0000 9.750 1.2644 0.01649 0.00991 -0.0547 0.0286 1.0000 10.000 1.2828 0.01696 0.01040 -0.0534 0.0272 1.0000 10.250 1.3016 0.01742 0.01088 -0.0522 0.0261 1.0000 10.500 1.3198 0.01792 0.01140 -0.0510 0.0248 1.0000 10.750 1.3370 0.01847 0.01197 -0.0496 0.0236 1.0000 11.000 1.3542 0.01905 0.01257 -0.0482 0.0227 1.0000 11.250 1.3717 0.01959 0.01316 -0.0470 0.0220 1.0000 11.500 1.3885 0.02018 0.01378 -0.0457 0.0212 1.0000 11.750 1.4047 0.02082 0.01444 -0.0443 0.0203 1.0000 12.000 1.4200 0.02153 0.01517 -0.0429 0.0194 1.0000 12.250 1.4352 0.02225 0.01593 -0.0415 0.0187 1.0000 12.500 1.4506 0.02296 0.01669 -0.0401 0.0182 1.0000 12.750 1.4656 0.02370 0.01748 -0.0388 0.0177 1.0000 13.000 1.4797 0.02451 0.01834 -0.0374 0.0172 1.0000 13.250 1.4932 0.02537 0.01924 -0.0360 0.0166 1.0000 13.500 1.5057 0.02631 0.02022 -0.0345 0.0161 1.0000 13.750 1.5171 0.02736 0.02131 -0.0330 0.0156 1.0000 14.000 1.5293 0.02835 0.02236 -0.0316 0.0152 1.0000 14.250 1.5413 0.02935 0.02343 -0.0303 0.0149 1.0000 14.500 1.5524 0.03045 0.02459 -0.0290 0.0145 1.0000 14.750 1.5627 0.03163 0.02583 -0.0276 0.0141 1.0000 15.000 1.5723 0.03289 0.02715 -0.0263 0.0138 1.0000 15.250 1.5809 0.03424 0.02856 -0.0250 0.0134 1.0000 15.500 1.5884 0.03571 0.03010 -0.0237 0.0131 1.0000 15.750 1.5946 0.03734 0.03179 -0.0225 0.0128 1.0000 16.000 1.5994 0.03916 0.03368 -0.0212 0.0125 1.0000 16.250 1.6060 0.04085 0.03546 -0.0202 0.0123 1.0000 16.500 1.6117 0.04267 0.03737 -0.0193 0.0122 1.0000 16.750 1.6165 0.04463 0.03942 -0.0185 0.0120 1.0000 17.000 1.6207 0.04673 0.04160 -0.0178 0.0117 1.0000 17.250 1.6239 0.04897 0.04393 -0.0171 0.0115 1.0000 17.500 1.6260 0.05138 0.04643 -0.0166 0.0113 1.0000 17.750 1.6272 0.05398 0.04911 -0.0163 0.0111 1.0000 18.000 1.6272 0.05679 0.05201 -0.0161 0.0109 1.0000 18.250 1.6257 0.05986 0.05517 -0.0160 0.0107 1.0000 18.500 1.6227 0.06320 0.05861 -0.0162 0.0105 1.0000 18.750 1.6174 0.06691 0.06242 -0.0165 0.0104 1.0000 19.000 1.6098 0.07107 0.06669 -0.0172 0.0102 1.0000 19.250 1.6003 0.07565 0.07138 -0.0181 0.0101 1.0000