LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.02 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l188tip-il-1000000.txt Download as CSV file: xf-l188tip-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9071 0.04822 0.04565 -0.0826 1.0000 0.0123
-14.000 -0.9279 0.04131 0.03853 -0.0885 1.0000 0.0123
-13.750 -0.9406 0.03698 0.03403 -0.0911 1.0000 0.0124
-13.500 -0.9580 0.03435 0.03127 -0.0899 0.9989 0.0125
-13.250 -0.9480 0.03158 0.02830 -0.0926 0.9951 0.0126
-13.000 -0.9349 0.02946 0.02599 -0.0938 0.9909 0.0128
-12.750 -0.9174 0.02773 0.02408 -0.0947 0.9869 0.0130
-12.500 -0.8963 0.02632 0.02250 -0.0957 0.9840 0.0132
-12.250 -0.8783 0.02526 0.02130 -0.0954 0.9788 0.0133
-12.000 -0.8703 0.02285 0.01863 -0.0943 0.9729 0.0136
-11.750 -0.8550 0.02159 0.01725 -0.0934 0.9680 0.0140
-11.500 -0.8357 0.02086 0.01646 -0.0926 0.9635 0.0142
-11.250 -0.8149 0.02032 0.01585 -0.0919 0.9597 0.0145
-11.000 -0.7934 0.01975 0.01521 -0.0913 0.9563 0.0149
-10.750 -0.7717 0.01913 0.01450 -0.0907 0.9527 0.0152
-10.500 -0.7501 0.01844 0.01372 -0.0901 0.9491 0.0156
-10.250 -0.7281 0.01781 0.01298 -0.0894 0.9458 0.0159
-10.000 -0.7052 0.01728 0.01234 -0.0889 0.9428 0.0162
-9.750 -0.6821 0.01661 0.01156 -0.0884 0.9399 0.0165
-9.500 -0.6617 0.01551 0.01038 -0.0877 0.9366 0.0171
-9.250 -0.6376 0.01501 0.00984 -0.0873 0.9335 0.0176
-9.000 -0.6130 0.01460 0.00938 -0.0869 0.9307 0.0180
-8.750 -0.5882 0.01419 0.00891 -0.0865 0.9279 0.0186
-8.500 -0.5627 0.01382 0.00848 -0.0863 0.9252 0.0191
-8.250 -0.5366 0.01350 0.00810 -0.0861 0.9225 0.0197
-8.000 -0.5124 0.01286 0.00739 -0.0857 0.9195 0.0204
-7.750 -0.4874 0.01238 0.00689 -0.0854 0.9166 0.0212
-7.500 -0.4614 0.01206 0.00654 -0.0852 0.9138 0.0219
-7.250 -0.4352 0.01177 0.00620 -0.0849 0.9110 0.0228
-7.000 -0.4085 0.01149 0.00588 -0.0848 0.9083 0.0235
-6.750 -0.3827 0.01104 0.00539 -0.0846 0.9054 0.0246
-6.500 -0.3562 0.01072 0.00507 -0.0845 0.9023 0.0259
-6.250 -0.3293 0.01048 0.00481 -0.0843 0.8993 0.0272
-6.000 -0.3021 0.01028 0.00456 -0.0842 0.8965 0.0283
-5.750 -0.2759 0.00990 0.00416 -0.0840 0.8934 0.0303
-5.500 -0.2485 0.00968 0.00394 -0.0840 0.8903 0.0322
-5.250 -0.2208 0.00952 0.00376 -0.0840 0.8870 0.0338
-5.000 -0.1940 0.00919 0.00344 -0.0838 0.8837 0.0371
-4.750 -0.1663 0.00903 0.00325 -0.0838 0.8806 0.0397
-4.500 -0.1390 0.00879 0.00302 -0.0837 0.8772 0.0437
-4.250 -0.1111 0.00863 0.00286 -0.0838 0.8736 0.0472
-4.000 -0.0836 0.00840 0.00266 -0.0838 0.8698 0.0535
-3.750 -0.0558 0.00822 0.00248 -0.0837 0.8662 0.0604
-3.500 -0.0280 0.00807 0.00233 -0.0838 0.8626 0.0689
-3.250 -0.0002 0.00788 0.00221 -0.0838 0.8587 0.0811
-3.000 0.0276 0.00768 0.00207 -0.0838 0.8543 0.0978
-2.750 0.0553 0.00749 0.00195 -0.0839 0.8503 0.1199
-2.250 0.1103 0.00701 0.00173 -0.0839 0.8413 0.1994
-2.000 0.1370 0.00664 0.00162 -0.0839 0.8363 0.2754
-1.750 0.1627 0.00612 0.00148 -0.0837 0.8316 0.4031
-1.500 0.1884 0.00567 0.00144 -0.0835 0.8261 0.5290
-1.250 0.2157 0.00548 0.00141 -0.0834 0.8204 0.5909
-1.000 0.2434 0.00538 0.00138 -0.0833 0.8152 0.6297
-0.750 0.2714 0.00530 0.00138 -0.0833 0.8088 0.6597
-0.500 0.2994 0.00525 0.00137 -0.0833 0.8027 0.6832
-0.250 0.3276 0.00522 0.00137 -0.0833 0.7964 0.7036
0.000 0.3557 0.00520 0.00137 -0.0833 0.7894 0.7219
0.250 0.3837 0.00519 0.00138 -0.0833 0.7828 0.7379
0.500 0.4114 0.00519 0.00139 -0.0831 0.7730 0.7546
0.750 0.4382 0.00520 0.00139 -0.0828 0.7576 0.7743
1.000 0.4641 0.00522 0.00140 -0.0822 0.7401 0.7981
1.250 0.4908 0.00522 0.00142 -0.0819 0.7271 0.8163
1.500 0.5180 0.00524 0.00145 -0.0817 0.7150 0.8281
2.000 0.5711 0.00529 0.00152 -0.0810 0.6897 0.8604
2.250 0.5965 0.00529 0.00159 -0.0804 0.6763 0.8892
2.500 0.6230 0.00530 0.00168 -0.0799 0.6617 0.9369
2.750 0.6590 0.00543 0.00177 -0.0817 0.6444 0.9711
3.000 0.6963 0.00558 0.00186 -0.0839 0.6241 0.9876
3.250 0.7333 0.00578 0.00196 -0.0861 0.5988 0.9968
3.500 0.7634 0.00601 0.00207 -0.0867 0.5688 1.0000
3.750 0.7843 0.00629 0.00220 -0.0854 0.5335 1.0000
4.000 0.8034 0.00669 0.00238 -0.0837 0.4835 1.0000
4.250 0.8190 0.00733 0.00266 -0.0814 0.4071 1.0000
4.500 0.8346 0.00804 0.00300 -0.0793 0.3320 1.0000
4.750 0.8529 0.00862 0.00331 -0.0776 0.2764 1.0000
5.000 0.8723 0.00914 0.00360 -0.0762 0.2308 1.0000
5.250 0.8931 0.00959 0.00388 -0.0750 0.1955 1.0000
5.500 0.9144 0.01001 0.00415 -0.0739 0.1675 1.0000
5.750 0.9360 0.01040 0.00442 -0.0729 0.1447 1.0000
6.000 0.9581 0.01076 0.00469 -0.0719 0.1270 1.0000
6.250 0.9804 0.01111 0.00496 -0.0710 0.1119 1.0000
6.500 1.0025 0.01147 0.00525 -0.0701 0.0992 1.0000
6.750 1.0244 0.01182 0.00554 -0.0692 0.0883 1.0000
7.000 1.0467 0.01215 0.00583 -0.0683 0.0801 1.0000
7.250 1.0687 0.01249 0.00614 -0.0674 0.0728 1.0000
7.500 1.0896 0.01288 0.00648 -0.0662 0.0655 1.0000
7.750 1.1114 0.01319 0.00679 -0.0653 0.0610 1.0000
8.000 1.1303 0.01362 0.00718 -0.0638 0.0552 1.0000
8.250 1.1509 0.01392 0.00750 -0.0626 0.0524 1.0000
8.500 1.1697 0.01434 0.00789 -0.0612 0.0487 1.0000
8.750 1.1888 0.01475 0.00831 -0.0598 0.0456 1.0000
9.000 1.2085 0.01513 0.00870 -0.0586 0.0430 1.0000
9.250 1.2261 0.01566 0.00921 -0.0570 0.0399 1.0000
9.500 1.2452 0.01608 0.00967 -0.0557 0.0382 1.0000
9.750 1.2643 0.01652 0.01012 -0.0545 0.0364 1.0000
10.000 1.2817 0.01706 0.01066 -0.0531 0.0344 1.0000
10.250 1.2981 0.01768 0.01130 -0.0515 0.0325 1.0000
10.500 1.3170 0.01813 0.01180 -0.0503 0.0313 1.0000
10.750 1.3344 0.01868 0.01236 -0.0490 0.0300 1.0000
11.000 1.3503 0.01934 0.01304 -0.0474 0.0286 1.0000
11.250 1.3637 0.02017 0.01391 -0.0456 0.0273 1.0000
11.500 1.3814 0.02071 0.01450 -0.0444 0.0265 1.0000
11.750 1.3979 0.02134 0.01516 -0.0431 0.0256 1.0000
12.000 1.4135 0.02203 0.01589 -0.0417 0.0246 1.0000
12.250 1.4264 0.02292 0.01680 -0.0401 0.0237 1.0000
12.500 1.4361 0.02405 0.01798 -0.0381 0.0228 1.0000
12.750 1.4513 0.02479 0.01878 -0.0368 0.0223 1.0000
13.000 1.4653 0.02562 0.01967 -0.0354 0.0217 1.0000
13.250 1.4783 0.02653 0.02064 -0.0340 0.0211 1.0000
13.500 1.4910 0.02747 0.02163 -0.0326 0.0205 1.0000
13.750 1.5017 0.02858 0.02277 -0.0311 0.0199 1.0000
14.000 1.5074 0.03009 0.02434 -0.0292 0.0192 1.0000
14.250 1.5140 0.03157 0.02590 -0.0275 0.0187 1.0000
14.500 1.5252 0.03271 0.02712 -0.0262 0.0184 1.0000
14.750 1.5348 0.03400 0.02849 -0.0250 0.0181 1.0000
15.000 1.5432 0.03539 0.02996 -0.0237 0.0177 1.0000
15.250 1.5511 0.03688 0.03151 -0.0225 0.0173 1.0000
15.500 1.5582 0.03847 0.03317 -0.0214 0.0169 1.0000
15.750 1.5639 0.04023 0.03500 -0.0203 0.0166 1.0000
16.000 1.5672 0.04228 0.03712 -0.0192 0.0163 1.0000
16.250 1.5665 0.04480 0.03972 -0.0181 0.0159 1.0000
16.500 1.5587 0.04817 0.04320 -0.0170 0.0155 1.0000
16.750 1.5603 0.05065 0.04579 -0.0165 0.0154 1.0000
17.000 1.5646 0.05291 0.04814 -0.0161 0.0152 1.0000
17.250 1.5669 0.05546 0.05079 -0.0158 0.0149 1.0000
17.500 1.5677 0.05826 0.05370 -0.0157 0.0147 1.0000
17.750 1.5670 0.06133 0.05687 -0.0158 0.0145 1.0000
18.000 1.5645 0.06469 0.06033 -0.0160 0.0143 1.0000
18.250 1.5603 0.06836 0.06411 -0.0165 0.0141 1.0000
18.500 1.5551 0.07229 0.06813 -0.0172 0.0139 1.0000
18.750 1.5484 0.07656 0.07251 -0.0181 0.0137 1.0000
19.000 1.5397 0.08122 0.07728 -0.0194 0.0136 1.0000
19.250 1.5288 0.08633 0.08251 -0.0210 0.0135 1.0000
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Polar data table (+)
Polar graphs
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