LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il) Reynolds number: 200,000 Max Cl/Cd: 72.58 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l7769-il-200000.txt Download as CSV file: xf-l7769-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4057 0.11413 0.10940 0.0144 0.5854 0.0574
-9.250 -0.4109 0.11154 0.10684 0.0101 0.5838 0.0596
-9.000 -0.4274 0.10923 0.10459 0.0037 0.5828 0.0601
-8.750 -0.4174 0.10428 0.09963 0.0035 0.5803 0.0606
-8.500 -0.3967 0.10068 0.09595 0.0054 0.5774 0.0614
-8.250 -0.3823 0.09792 0.09317 0.0058 0.5748 0.0626
-8.000 -0.3736 0.09514 0.09043 0.0049 0.5721 0.0640
-7.750 -0.3681 0.09228 0.08759 0.0034 0.5695 0.0658
-7.500 -0.3683 0.08936 0.08470 0.0009 0.5673 0.0680
-7.250 -0.3915 0.08582 0.08116 -0.0131 0.5669 0.0698
-7.000 -0.3840 0.08066 0.07599 -0.0145 0.5647 0.0704
-6.750 -0.3694 0.07771 0.07303 -0.0121 0.5621 0.0710
-6.500 -0.3552 0.07522 0.07050 -0.0112 0.5599 0.0720
-6.250 -0.3414 0.07250 0.06780 -0.0120 0.5576 0.0732
-6.000 -0.3275 0.06950 0.06479 -0.0141 0.5551 0.0751
-5.750 -0.3121 0.06588 0.06110 -0.0185 0.5529 0.0786
-5.500 -0.2963 0.06000 0.05493 -0.0260 0.5512 0.0821
-5.250 -0.2789 0.05770 0.05265 -0.0253 0.5487 0.0832
-5.000 -0.2600 0.05543 0.05033 -0.0255 0.5465 0.0848
-4.750 -0.2394 0.05291 0.04769 -0.0266 0.5445 0.0874
-4.500 -0.2124 0.04866 0.04284 -0.0313 0.5427 0.0943
-4.250 -0.1916 0.04587 0.04014 -0.0315 0.5398 0.0953
-4.000 -0.1664 0.03488 0.02809 -0.0339 0.5383 0.0705
-3.750 -0.1420 0.03347 0.02671 -0.0341 0.5357 0.0717
-3.500 -0.1165 0.02973 0.02256 -0.0341 0.5335 0.0665
-3.250 -0.0908 0.02529 0.01738 -0.0339 0.5316 0.0636
-3.000 -0.0637 0.02348 0.01518 -0.0335 0.5297 0.0639
-2.750 -0.0364 0.02239 0.01382 -0.0332 0.5279 0.0649
-2.500 -0.0086 0.02168 0.01294 -0.0330 0.5259 0.0669
-2.250 0.0199 0.02112 0.01223 -0.0329 0.5232 0.0694
-2.000 0.0476 0.02030 0.01139 -0.0327 0.5203 0.0719
-1.750 0.0754 0.01993 0.01104 -0.0325 0.5177 0.0751
-1.500 0.1033 0.01957 0.01060 -0.0322 0.5156 0.0798
-1.250 0.1308 0.01923 0.01029 -0.0319 0.5138 0.0866
-1.000 0.1584 0.01914 0.01021 -0.0316 0.5121 0.0989
-0.750 0.1862 0.01931 0.01035 -0.0314 0.5105 0.1173
-0.500 0.2144 0.01949 0.01061 -0.0315 0.5082 0.1327
-0.250 0.2422 0.01961 0.01082 -0.0316 0.5055 0.1450
0.000 0.2699 0.01966 0.01090 -0.0316 0.5027 0.1564
0.250 0.2975 0.01974 0.01099 -0.0315 0.5004 0.1698
0.500 0.3249 0.01977 0.01105 -0.0314 0.4986 0.1833
0.750 0.3518 0.01962 0.01100 -0.0312 0.4970 0.1942
1.000 0.3788 0.01958 0.01099 -0.0309 0.4956 0.2051
1.250 0.4056 0.01966 0.01110 -0.0307 0.4942 0.2191
1.500 0.4324 0.01992 0.01157 -0.0309 0.4914 0.2371
2.000 0.5012 0.01869 0.01248 -0.0339 0.4856 1.0000
2.250 0.5278 0.01911 0.01281 -0.0337 0.4835 1.0000
2.500 0.5545 0.01938 0.01299 -0.0334 0.4816 1.0000
2.750 0.5813 0.01957 0.01308 -0.0329 0.4800 1.0000
3.000 0.6080 0.01986 0.01328 -0.0325 0.4785 1.0000
3.250 0.6341 0.02039 0.01377 -0.0323 0.4769 1.0000
3.500 0.6589 0.02158 0.01516 -0.0331 0.4715 1.0000
3.750 0.6852 0.02190 0.01547 -0.0329 0.4679 1.0000
4.000 0.7125 0.02173 0.01523 -0.0322 0.4653 1.0000
4.250 0.7403 0.02149 0.01487 -0.0315 0.4632 1.0000
4.500 0.7675 0.02147 0.01476 -0.0308 0.4614 1.0000
4.750 0.7905 0.02286 0.01640 -0.0316 0.4551 1.0000
5.000 0.8166 0.02319 0.01676 -0.0314 0.4517 1.0000
5.250 0.8439 0.02315 0.01669 -0.0309 0.4494 1.0000
5.500 0.8718 0.02296 0.01644 -0.0303 0.4476 1.0000
5.750 0.8997 0.02281 0.01623 -0.0297 0.4459 1.0000
6.000 0.9211 0.02419 0.01787 -0.0302 0.4388 1.0000
6.250 0.9485 0.02401 0.01769 -0.0297 0.4352 1.0000
6.500 0.9781 0.02326 0.01686 -0.0289 0.4326 1.0000
6.750 1.0084 0.02240 0.01590 -0.0281 0.4303 1.0000
7.000 1.0314 0.02309 0.01679 -0.0281 0.4233 1.0000
7.250 1.0592 0.02282 0.01653 -0.0277 0.4194 1.0000
7.500 1.0885 0.02224 0.01593 -0.0271 0.4167 1.0000
7.750 1.1185 0.02161 0.01520 -0.0265 0.4143 1.0000
8.000 1.1410 0.02219 0.01605 -0.0264 0.4064 1.0000
8.250 1.1698 0.02170 0.01555 -0.0259 0.4025 1.0000
8.500 1.2001 0.02100 0.01479 -0.0254 0.3995 1.0000
8.750 1.2237 0.02126 0.01528 -0.0252 0.3912 1.0000
9.000 1.2531 0.02056 0.01456 -0.0246 0.3861 1.0000
9.250 1.2789 0.02041 0.01456 -0.0243 0.3780 1.0000
9.500 1.3081 0.01959 0.01370 -0.0237 0.3699 1.0000
9.750 1.3337 0.01928 0.01351 -0.0233 0.3568 1.0000
10.000 1.3594 0.01900 0.01329 -0.0229 0.3413 1.0000
10.250 1.3833 0.01906 0.01342 -0.0226 0.3206 1.0000
10.500 1.4050 0.01936 0.01365 -0.0221 0.2932 1.0000
10.750 1.4221 0.02023 0.01437 -0.0215 0.2645 1.0000
11.000 1.4351 0.02156 0.01558 -0.0209 0.2413 1.0000
11.250 1.4448 0.02313 0.01708 -0.0202 0.2235 1.0000
11.500 1.4510 0.02493 0.01886 -0.0195 0.2087 1.0000
11.750 1.4518 0.02712 0.02109 -0.0191 0.1965 1.0000
12.000 1.4426 0.03040 0.02445 -0.0196 0.1877 1.0000
12.250 1.4324 0.03388 0.02791 -0.0201 0.1798 1.0000
12.500 1.4259 0.03703 0.03111 -0.0204 0.1707 1.0000
12.750 1.4176 0.04032 0.03442 -0.0207 0.1621 1.0000
13.000 1.4085 0.04371 0.03780 -0.0210 0.1537 1.0000
13.250 1.4008 0.04707 0.04120 -0.0214 0.1440 1.0000
13.500 1.3906 0.05073 0.04485 -0.0219 0.1341 1.0000
13.750 1.3792 0.05460 0.04869 -0.0225 0.1242 1.0000
14.000 1.3665 0.05884 0.05289 -0.0235 0.1122 1.0000
14.250 1.3543 0.06336 0.05739 -0.0246 0.0963 1.0000
14.500 1.3381 0.06859 0.06251 -0.0262 0.0791 1.0000
14.750 1.3223 0.07392 0.06772 -0.0278 0.0663 1.0000
15.000 1.3084 0.07915 0.07287 -0.0293 0.0578 1.0000
15.250 1.3013 0.08351 0.07725 -0.0306 0.0525 1.0000
15.500 1.2911 0.08840 0.08209 -0.0321 0.0490 1.0000
15.750 1.2884 0.09229 0.08606 -0.0333 0.0458 1.0000
16.000 1.2841 0.09643 0.09022 -0.0346 0.0436 1.0000
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