LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 500,000 Max Cl/Cd: 91.9 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l188tip-il-500000-n5.txt Download as CSV file: xf-l188tip-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8578 0.04966 0.04643 -0.0821 1.0000 0.0124
-13.500 -0.8822 0.04258 0.03912 -0.0878 1.0000 0.0124
-13.250 -0.9013 0.03870 0.03507 -0.0886 1.0000 0.0124
-13.000 -0.9005 0.03501 0.03112 -0.0919 0.9919 0.0126
-12.750 -0.8942 0.03232 0.02818 -0.0932 0.9847 0.0128
-12.500 -0.8848 0.03020 0.02581 -0.0934 0.9781 0.0130
-12.250 -0.8703 0.02835 0.02372 -0.0937 0.9734 0.0132
-12.000 -0.8544 0.02682 0.02197 -0.0936 0.9688 0.0133
-11.750 -0.8400 0.02540 0.02042 -0.0929 0.9634 0.0136
-11.500 -0.8212 0.02432 0.01923 -0.0926 0.9594 0.0138
-11.250 -0.8013 0.02342 0.01822 -0.0922 0.9558 0.0141
-11.000 -0.7817 0.02260 0.01730 -0.0916 0.9514 0.0144
-10.750 -0.7613 0.02180 0.01639 -0.0910 0.9475 0.0147
-10.500 -0.7401 0.02100 0.01547 -0.0905 0.9442 0.0150
-10.250 -0.7185 0.02022 0.01456 -0.0900 0.9411 0.0154
-10.000 -0.6965 0.01951 0.01371 -0.0895 0.9375 0.0159
-9.750 -0.6738 0.01886 0.01293 -0.0890 0.9339 0.0163
-9.500 -0.6517 0.01812 0.01211 -0.0884 0.9306 0.0168
-9.250 -0.6283 0.01755 0.01148 -0.0880 0.9278 0.0172
-9.000 -0.6041 0.01705 0.01090 -0.0877 0.9250 0.0177
-8.750 -0.5800 0.01653 0.01032 -0.0873 0.9216 0.0183
-8.500 -0.5556 0.01601 0.00973 -0.0870 0.9184 0.0189
-8.250 -0.5310 0.01552 0.00914 -0.0866 0.9153 0.0194
-8.000 -0.5062 0.01504 0.00857 -0.0862 0.9125 0.0200
-7.750 -0.4813 0.01456 0.00806 -0.0859 0.9099 0.0209
-7.500 -0.4557 0.01421 0.00768 -0.0857 0.9066 0.0217
-7.250 -0.4300 0.01384 0.00726 -0.0855 0.9032 0.0227
-7.000 -0.4042 0.01347 0.00682 -0.0852 0.9000 0.0236
-6.750 -0.3786 0.01305 0.00637 -0.0850 0.8971 0.0245
-6.500 -0.3525 0.01272 0.00600 -0.0847 0.8944 0.0257
-6.250 -0.3261 0.01243 0.00568 -0.0846 0.8911 0.0271
-6.000 -0.2995 0.01216 0.00537 -0.0845 0.8875 0.0285
-5.750 -0.2733 0.01183 0.00504 -0.0843 0.8840 0.0304
-5.500 -0.2464 0.01157 0.00475 -0.0841 0.8810 0.0323
-5.250 -0.2194 0.01133 0.00445 -0.0840 0.8781 0.0342
-5.000 -0.1927 0.01106 0.00421 -0.0839 0.8742 0.0368
-4.750 -0.1656 0.01086 0.00398 -0.0838 0.8703 0.0398
-4.500 -0.1386 0.01061 0.00375 -0.0837 0.8666 0.0435
-4.250 -0.1111 0.01043 0.00352 -0.0837 0.8634 0.0473
-4.000 -0.0839 0.01021 0.00334 -0.0836 0.8594 0.0528
-3.750 -0.0566 0.01002 0.00316 -0.0836 0.8550 0.0586
-3.500 -0.0291 0.00984 0.00299 -0.0835 0.8508 0.0662
-3.250 -0.0016 0.00965 0.00281 -0.0835 0.8472 0.0762
-3.000 0.0258 0.00947 0.00268 -0.0835 0.8425 0.0883
-2.750 0.0532 0.00929 0.00255 -0.0834 0.8375 0.1043
-2.500 0.0807 0.00908 0.00241 -0.0834 0.8330 0.1266
-2.250 0.1080 0.00887 0.00230 -0.0834 0.8284 0.1556
-2.000 0.1350 0.00862 0.00220 -0.0834 0.8226 0.1980
-1.750 0.1618 0.00830 0.00207 -0.0833 0.8174 0.2610
-1.500 0.1877 0.00787 0.00196 -0.0832 0.8119 0.3591
-1.250 0.2126 0.00737 0.00189 -0.0829 0.8056 0.4916
-0.750 0.2661 0.00701 0.00187 -0.0824 0.7935 0.6118
-0.500 0.2934 0.00694 0.00186 -0.0822 0.7871 0.6455
-0.250 0.3209 0.00688 0.00187 -0.0821 0.7808 0.6731
0.000 0.3482 0.00684 0.00189 -0.0819 0.7739 0.7004
0.250 0.3751 0.00680 0.00192 -0.0816 0.7675 0.7331
0.500 0.4017 0.00676 0.00197 -0.0811 0.7603 0.7661
0.750 0.4290 0.00676 0.00197 -0.0809 0.7537 0.7834
1.250 0.4840 0.00679 0.00200 -0.0806 0.7344 0.8027
1.500 0.5096 0.00685 0.00199 -0.0801 0.7116 0.8131
1.750 0.5348 0.00694 0.00200 -0.0794 0.6866 0.8251
2.000 0.5604 0.00699 0.00205 -0.0788 0.6689 0.8388
2.250 0.5858 0.00705 0.00211 -0.0782 0.6516 0.8569
2.500 0.6107 0.00712 0.00220 -0.0774 0.6329 0.8825
2.750 0.6382 0.00723 0.00231 -0.0772 0.6123 0.9200
3.000 0.6734 0.00741 0.00244 -0.0789 0.5857 0.9565
3.250 0.7067 0.00769 0.00257 -0.0802 0.5522 0.9831
3.500 0.7380 0.00808 0.00276 -0.0813 0.5057 0.9997
3.750 0.7553 0.00858 0.00298 -0.0793 0.4479 1.0000
4.000 0.7700 0.00928 0.00331 -0.0770 0.3746 1.0000
4.250 0.7868 0.00992 0.00365 -0.0751 0.3141 1.0000
4.500 0.8051 0.01050 0.00397 -0.0735 0.2647 1.0000
4.750 0.8248 0.01100 0.00428 -0.0721 0.2255 1.0000
5.000 0.8452 0.01145 0.00458 -0.0709 0.1943 1.0000
5.250 0.8661 0.01188 0.00488 -0.0698 0.1691 1.0000
5.500 0.8874 0.01228 0.00517 -0.0687 0.1484 1.0000
5.750 0.9087 0.01267 0.00548 -0.0677 0.1312 1.0000
6.000 0.9301 0.01305 0.00579 -0.0667 0.1167 1.0000
6.250 0.9515 0.01342 0.00610 -0.0657 0.1047 1.0000
6.500 0.9728 0.01379 0.00643 -0.0646 0.0945 1.0000
6.750 0.9937 0.01418 0.00677 -0.0635 0.0859 1.0000
7.000 1.0144 0.01456 0.00712 -0.0624 0.0782 1.0000
7.250 1.0341 0.01493 0.00747 -0.0611 0.0720 1.0000
7.500 1.0530 0.01535 0.00787 -0.0596 0.0660 1.0000
7.750 1.0726 0.01573 0.00826 -0.0583 0.0615 1.0000
8.000 1.0913 0.01618 0.00869 -0.0569 0.0567 1.0000
8.250 1.1105 0.01661 0.00913 -0.0556 0.0531 1.0000
8.500 1.1294 0.01707 0.00960 -0.0543 0.0497 1.0000
8.750 1.1473 0.01760 0.01011 -0.0529 0.0463 1.0000
9.000 1.1663 0.01805 0.01061 -0.0517 0.0438 1.0000
9.250 1.1842 0.01859 0.01116 -0.0503 0.0412 1.0000
9.500 1.2013 0.01919 0.01176 -0.0489 0.0390 1.0000
9.750 1.2194 0.01972 0.01234 -0.0476 0.0373 1.0000
10.000 1.2366 0.02031 0.01296 -0.0463 0.0353 1.0000
10.250 1.2528 0.02098 0.01365 -0.0448 0.0335 1.0000
10.500 1.2691 0.02164 0.01435 -0.0434 0.0321 1.0000
10.750 1.2855 0.02230 0.01506 -0.0421 0.0308 1.0000
11.000 1.3011 0.02302 0.01583 -0.0407 0.0295 1.0000
11.250 1.3157 0.02382 0.01665 -0.0393 0.0283 1.0000
11.500 1.3295 0.02468 0.01756 -0.0377 0.0272 1.0000
11.750 1.3444 0.02547 0.01842 -0.0364 0.0262 1.0000
12.000 1.3585 0.02633 0.01934 -0.0350 0.0252 1.0000
12.250 1.3716 0.02726 0.02032 -0.0336 0.0244 1.0000
12.500 1.3837 0.02828 0.02139 -0.0321 0.0236 1.0000
12.750 1.3938 0.02948 0.02263 -0.0305 0.0228 1.0000
13.000 1.4060 0.03052 0.02376 -0.0291 0.0222 1.0000
13.250 1.4171 0.03165 0.02497 -0.0278 0.0216 1.0000
13.500 1.4279 0.03283 0.02624 -0.0264 0.0209 1.0000
13.750 1.4378 0.03410 0.02758 -0.0252 0.0203 1.0000
14.000 1.4463 0.03551 0.02905 -0.0238 0.0197 1.0000
14.250 1.4529 0.03711 0.03071 -0.0225 0.0192 1.0000
14.500 1.4582 0.03888 0.03256 -0.0211 0.0188 1.0000
14.750 1.4652 0.04052 0.03431 -0.0200 0.0184 1.0000
15.000 1.4710 0.04230 0.03620 -0.0189 0.0181 1.0000
15.250 1.4761 0.04421 0.03822 -0.0180 0.0177 1.0000
15.500 1.4807 0.04624 0.04036 -0.0171 0.0173 1.0000
15.750 1.4847 0.04839 0.04261 -0.0164 0.0169 1.0000
16.000 1.4878 0.05069 0.04500 -0.0158 0.0165 1.0000
16.250 1.4893 0.05323 0.04763 -0.0154 0.0162 1.0000
16.500 1.4891 0.05607 0.05056 -0.0151 0.0159 1.0000
16.750 1.4863 0.05931 0.05390 -0.0150 0.0156 1.0000
17.000 1.4827 0.06275 0.05746 -0.0151 0.0154 1.0000
17.250 1.4804 0.06612 0.06096 -0.0153 0.0152 1.0000
17.500 1.4766 0.06980 0.06479 -0.0158 0.0150 1.0000
17.750 1.4714 0.07380 0.06892 -0.0166 0.0148 1.0000
18.000 1.4645 0.07818 0.07344 -0.0176 0.0146 1.0000
18.250 1.4562 0.08286 0.07826 -0.0189 0.0144 1.0000
18.500 1.4462 0.08796 0.08350 -0.0206 0.0143 1.0000
18.750 1.4349 0.09344 0.08912 -0.0226 0.0141 1.0000
19.000 1.4219 0.09939 0.09521 -0.0251 0.0140 1.0000
19.250 1.4072 0.10574 0.10171 -0.0279 0.0139 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED L-188 TIP AIRFOIL (l188tip-il)