LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.56 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188tip-il-1000000-n5.txt Download as CSV file: xf-l188tip-il-1000000-n5.csv |
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 -0.9869 0.02106 0.01646 -0.0871 0.9402 0.0103
-12.500 -0.9663 0.02035 0.01565 -0.0865 0.9363 0.0105
-12.250 -0.9449 0.01971 0.01491 -0.0860 0.9326 0.0106
-12.000 -0.9246 0.01894 0.01404 -0.0854 0.9291 0.0108
-11.750 -0.9034 0.01821 0.01323 -0.0848 0.9259 0.0111
-11.500 -0.8804 0.01761 0.01257 -0.0845 0.9229 0.0114
-11.250 -0.8570 0.01706 0.01196 -0.0842 0.9199 0.0117
-11.000 -0.8332 0.01655 0.01138 -0.0839 0.9168 0.0119
-10.750 -0.8092 0.01606 0.01082 -0.0836 0.9139 0.0122
-10.500 -0.7850 0.01559 0.01028 -0.0833 0.9111 0.0125
-10.250 -0.7602 0.01513 0.00975 -0.0831 0.9086 0.0127
-10.000 -0.7350 0.01469 0.00925 -0.0829 0.9060 0.0130
-9.750 -0.7096 0.01429 0.00878 -0.0827 0.9032 0.0132
-9.500 -0.6845 0.01383 0.00827 -0.0825 0.9004 0.0135
-9.250 -0.6593 0.01339 0.00777 -0.0823 0.8977 0.0140
-9.000 -0.6336 0.01303 0.00737 -0.0821 0.8951 0.0145
-8.750 -0.6072 0.01270 0.00701 -0.0820 0.8927 0.0150
-8.500 -0.5806 0.01239 0.00667 -0.0820 0.8900 0.0155
-8.250 -0.5541 0.01208 0.00632 -0.0819 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
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