LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il) Reynolds number: 100,000 Max Cl/Cd: 39.84 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-l7769-il-100000-n5.txt Download as CSV file: xf-l7769-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LISSAMAN 7769 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4065 0.11385 0.10783 0.0103 0.5753 0.0726
-9.000 -0.4091 0.11104 0.10505 0.0069 0.5732 0.0731
-8.750 -0.4090 0.10788 0.10191 0.0041 0.5710 0.0732
-8.500 -0.4089 0.10458 0.09863 0.0013 0.5687 0.0734
-8.250 -0.4099 0.10128 0.09534 -0.0016 0.5667 0.0735
-8.000 -0.3853 0.09676 0.09074 0.0014 0.5636 0.0747
-7.750 -0.3718 0.09374 0.08771 0.0016 0.5606 0.0759
-7.500 -0.3667 0.09060 0.08460 0.0001 0.5579 0.0763
-7.000 -0.3794 0.07747 0.07139 -0.0125 0.5552 0.0540
-6.750 -0.3679 0.07425 0.06814 -0.0140 0.5527 0.0533
-6.500 -0.3567 0.07051 0.06434 -0.0165 0.5505 0.0527
-6.250 -0.3449 0.06634 0.06005 -0.0197 0.5487 0.0523
-6.000 -0.3313 0.06181 0.05534 -0.0233 0.5470 0.0526
-5.750 -0.3151 0.05725 0.05061 -0.0265 0.5449 0.0528
-5.500 -0.2970 0.05298 0.04616 -0.0290 0.5423 0.0525
-5.250 -0.2774 0.04876 0.04170 -0.0311 0.5396 0.0520
-5.000 -0.2566 0.04440 0.03700 -0.0329 0.5372 0.0517
-4.750 -0.2347 0.03995 0.03212 -0.0342 0.5348 0.0517
-4.500 -0.2118 0.03576 0.02741 -0.0350 0.5327 0.0520
-4.250 -0.1878 0.03181 0.02272 -0.0355 0.5309 0.0537
-4.000 -0.1622 0.02956 0.02003 -0.0356 0.5285 0.0549
-3.750 -0.1355 0.02838 0.01869 -0.0356 0.5257 0.0558
-3.500 -0.1086 0.02722 0.01734 -0.0356 0.5230 0.0568
-3.250 -0.0815 0.02614 0.01603 -0.0355 0.5205 0.0580
-3.000 -0.0541 0.02511 0.01476 -0.0353 0.5181 0.0596
-2.750 -0.0267 0.02415 0.01353 -0.0350 0.5160 0.0617
-2.500 0.0006 0.02352 0.01276 -0.0347 0.5140 0.0645
-2.250 0.0282 0.02325 0.01249 -0.0346 0.5114 0.0680
-2.000 0.0562 0.02273 0.01189 -0.0345 0.5085 0.0725
-1.750 0.0837 0.02237 0.01157 -0.0344 0.5060 0.0768
-1.500 0.1113 0.02203 0.01119 -0.0341 0.5037 0.0843
-1.250 0.1387 0.02190 0.01110 -0.0340 0.5016 0.0940
-1.000 0.1663 0.02186 0.01105 -0.0337 0.4997 0.1069
-0.750 0.1937 0.02183 0.01095 -0.0335 0.4979 0.1196
-0.500 0.2212 0.02190 0.01097 -0.0333 0.4961 0.1339
-0.250 0.2488 0.02209 0.01125 -0.0335 0.4929 0.1503
0.000 0.2760 0.02209 0.01133 -0.0334 0.4902 0.1627
0.250 0.3032 0.02211 0.01132 -0.0333 0.4880 0.1719
0.500 0.3299 0.02204 0.01133 -0.0331 0.4859 0.1814
0.750 0.3571 0.02203 0.01133 -0.0329 0.4841 0.1920
1.000 0.3844 0.02205 0.01131 -0.0327 0.4824 0.2035
1.250 0.4117 0.02202 0.01129 -0.0324 0.4808 0.2194
1.500 0.4390 0.02209 0.01151 -0.0325 0.4786 0.2469
1.750 0.4802 0.02056 0.01205 -0.0353 0.4752 1.0000
2.000 0.5067 0.02106 0.01247 -0.0353 0.4727 1.0000
2.250 0.5331 0.02152 0.01284 -0.0351 0.4704 1.0000
2.500 0.5595 0.02188 0.01311 -0.0349 0.4682 1.0000
2.750 0.5859 0.02218 0.01331 -0.0345 0.4663 1.0000
3.000 0.6124 0.02246 0.01350 -0.0342 0.4647 1.0000
3.250 0.6388 0.02277 0.01373 -0.0338 0.4634 1.0000
3.500 0.6634 0.02387 0.01498 -0.0344 0.4591 1.0000
3.750 0.6886 0.02456 0.01571 -0.0345 0.4556 1.0000
4.000 0.7142 0.02506 0.01622 -0.0344 0.4530 1.0000
4.250 0.7401 0.02542 0.01656 -0.0341 0.4508 1.0000
4.500 0.7665 0.02562 0.01672 -0.0336 0.4489 1.0000
4.750 0.7934 0.02564 0.01667 -0.0330 0.4472 1.0000
5.000 0.8148 0.02699 0.01825 -0.0337 0.4395 1.0000
5.250 0.8407 0.02714 0.01842 -0.0333 0.4360 1.0000
5.500 0.8675 0.02708 0.01832 -0.0326 0.4335 1.0000
5.750 0.8948 0.02697 0.01817 -0.0319 0.4317 1.0000
6.000 0.9137 0.02866 0.02011 -0.0327 0.4243 1.0000
6.250 0.9386 0.02897 0.02048 -0.0323 0.4206 1.0000
6.500 0.9654 0.02888 0.02040 -0.0317 0.4181 1.0000
6.750 0.9935 0.02853 0.02004 -0.0309 0.4161 1.0000
7.000 1.0091 0.03042 0.02222 -0.0316 0.4073 1.0000
7.250 1.0359 0.03017 0.02199 -0.0309 0.4038 1.0000
7.500 1.0660 0.02932 0.02113 -0.0298 0.4012 1.0000
7.750 1.0816 0.03083 0.02289 -0.0302 0.3917 1.0000
8.000 1.1106 0.03009 0.02217 -0.0293 0.3878 1.0000
8.500 1.1537 0.03093 0.02329 -0.0286 0.3743 1.0000
8.750 1.1844 0.02999 0.02237 -0.0276 0.3709 1.0000
9.000 1.1944 0.03190 0.02454 -0.0279 0.3601 1.0000
9.250 1.2262 0.03078 0.02344 -0.0268 0.3560 1.0000
9.500 1.2325 0.03291 0.02582 -0.0272 0.3440 1.0000
9.750 1.2352 0.03535 0.02843 -0.0277 0.3321 1.0000
10.000 1.2232 0.03955 0.03272 -0.0294 0.3186 1.0000
10.250 1.2602 0.03760 0.03083 -0.0277 0.3129 1.0000
10.500 1.2438 0.04168 0.03493 -0.0284 0.2996 1.0000
10.750 1.2418 0.04422 0.03750 -0.0283 0.2876 1.0000
11.000 1.2521 0.04536 0.03864 -0.0278 0.2770 1.0000
11.250 1.2738 0.04509 0.03837 -0.0267 0.2675 1.0000
11.500 1.2847 0.04610 0.03935 -0.0260 0.2568 1.0000
11.750 1.2881 0.04806 0.04129 -0.0256 0.2458 1.0000
12.000 1.2934 0.04974 0.04292 -0.0252 0.2345 1.0000
12.250 1.2975 0.05153 0.04461 -0.0247 0.2228 1.0000
12.500 1.2970 0.05394 0.04696 -0.0246 0.2111 1.0000
12.750 1.2896 0.05740 0.05042 -0.0252 0.1994 1.0000
13.000 1.2839 0.06067 0.05367 -0.0256 0.1881 1.0000
13.250 1.2788 0.06392 0.05687 -0.0262 0.1771 1.0000
13.500 1.2742 0.06727 0.06020 -0.0269 0.1668 1.0000
13.750 1.2696 0.07097 0.06397 -0.0279 0.1573 1.0000
14.000 1.2689 0.07412 0.06713 -0.0286 0.1493 1.0000
14.250 1.2667 0.07766 0.07072 -0.0295 0.1412 1.0000
14.500 1.2649 0.08120 0.07432 -0.0305 0.1335 1.0000
14.750 1.2620 0.08492 0.07804 -0.0316 0.1256 1.0000
15.000 1.2582 0.08899 0.08222 -0.0330 0.1174 1.0000
15.250 1.2532 0.09327 0.08652 -0.0345 0.1091 1.0000
15.500 1.2476 0.09776 0.09108 -0.0361 0.1006 1.0000
15.750 1.2416 0.10246 0.09585 -0.0379 0.0917 1.0000
16.000 1.2340 0.10750 0.10093 -0.0400 0.0826 1.0000
16.250 1.2255 0.11281 0.10625 -0.0422 0.0737 1.0000
16.500 1.2160 0.11841 0.11183 -0.0447 0.0657 1.0000
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