LDS-2 AIRFOIL (lds2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LDS-2 AIRFOIL (lds2-il) Reynolds number: 100,000 Max Cl/Cd: 52.7 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lds2-il-100000.txt Download as CSV file: xf-lds2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LDS-2 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4224 0.09343 0.08842 -0.0362 1.0000 0.1407
-9.000 -0.4181 0.09066 0.08569 -0.0358 1.0000 0.1471
-8.750 -0.4799 0.08630 0.08157 -0.0437 1.0000 0.1517
-8.500 -0.4285 0.08390 0.07909 -0.0368 1.0000 0.1581
-8.250 -0.4478 0.08080 0.07612 -0.0380 1.0000 0.1648
-8.000 -0.5172 0.07744 0.07292 -0.0404 1.0000 0.1670
-7.750 -0.4727 0.07511 0.07066 -0.0354 1.0000 0.1735
-7.500 -0.4978 0.07269 0.06834 -0.0337 1.0000 0.1790
-7.250 -0.5753 0.07137 0.06690 -0.0315 1.0000 0.1828
-7.000 -0.5370 0.06844 0.06422 -0.0273 1.0000 0.1887
-6.750 -0.5997 0.06737 0.06284 -0.0257 1.0000 0.1989
-6.500 -0.5685 0.06421 0.06003 -0.0217 1.0000 0.2035
-5.750 -0.5929 0.04136 0.03468 -0.0217 1.0000 0.0897
-5.500 -0.5659 0.03721 0.02942 -0.0218 0.9956 0.0796
-5.250 -0.5318 0.03464 0.02648 -0.0234 0.9900 0.0783
-5.000 -0.4970 0.03172 0.02325 -0.0252 0.9852 0.0769
-4.750 -0.4642 0.02963 0.02078 -0.0262 0.9794 0.0767
-4.500 -0.4258 0.02844 0.01914 -0.0281 0.9740 0.0791
-4.250 -0.3948 0.02641 0.01711 -0.0291 0.9682 0.0822
-4.000 -0.3574 0.02519 0.01583 -0.0309 0.9630 0.0855
-3.750 -0.3245 0.02437 0.01490 -0.0318 0.9570 0.0909
-3.500 -0.2927 0.02326 0.01394 -0.0328 0.9509 0.0987
-3.250 -0.2554 0.02239 0.01313 -0.0346 0.9461 0.1096
-3.000 -0.2340 0.02169 0.01253 -0.0337 0.9377 0.1273
-2.750 -0.2074 0.01967 0.01170 -0.0343 0.9327 0.3007
-2.500 -0.1988 0.01887 0.01220 -0.0299 0.9247 0.6178
-2.250 -0.1711 0.01886 0.01239 -0.0290 0.9183 0.6973
-2.000 -0.1420 0.01893 0.01261 -0.0283 0.9128 0.7615
-1.750 -0.1201 0.01911 0.01301 -0.0256 0.9056 0.8356
-1.500 -0.0656 0.01967 0.01362 -0.0283 0.9027 0.9129
-1.250 0.0120 0.01996 0.01369 -0.0376 0.9009 0.9368
-1.000 0.0937 0.02009 0.01361 -0.0481 0.8997 0.9546
-0.750 0.1682 0.02011 0.01347 -0.0576 0.8965 0.9729
-0.500 0.2447 0.01994 0.01318 -0.0677 0.8929 0.9885
-0.250 0.3118 0.01961 0.01275 -0.0763 0.8890 1.0000
0.000 0.3463 0.01936 0.01241 -0.0786 0.8832 1.0000
0.250 0.3435 0.01967 0.01266 -0.0743 0.8704 1.0000
0.500 0.3540 0.01997 0.01289 -0.0720 0.8606 1.0000
0.750 0.3826 0.02002 0.01288 -0.0724 0.8535 1.0000
1.000 0.3933 0.02045 0.01326 -0.0699 0.8436 1.0000
1.250 0.4274 0.02041 0.01319 -0.0709 0.8369 1.0000
1.500 0.4430 0.02070 0.01345 -0.0687 0.8256 1.0000
1.750 0.4882 0.02023 0.01296 -0.0709 0.8190 1.0000
2.000 0.5031 0.02048 0.01320 -0.0684 0.8065 1.0000
2.250 0.5285 0.02048 0.01319 -0.0675 0.7965 1.0000
2.500 0.5662 0.01992 0.01263 -0.0679 0.7870 1.0000
2.750 0.5874 0.01984 0.01256 -0.0660 0.7736 1.0000
3.000 0.6115 0.01968 0.01241 -0.0644 0.7612 1.0000
3.250 0.6415 0.01929 0.01202 -0.0636 0.7503 1.0000
3.500 0.6712 0.01884 0.01158 -0.0627 0.7383 1.0000
3.750 0.6942 0.01861 0.01137 -0.0608 0.7236 1.0000
4.000 0.7185 0.01830 0.01107 -0.0591 0.7083 1.0000
4.250 0.7432 0.01798 0.01078 -0.0574 0.6924 1.0000
4.500 0.7685 0.01762 0.01042 -0.0558 0.6754 1.0000
4.750 0.7925 0.01730 0.01010 -0.0540 0.6566 1.0000
5.000 0.8121 0.01712 0.00998 -0.0516 0.6338 1.0000
5.250 0.8351 0.01681 0.00964 -0.0496 0.6090 1.0000
5.500 0.8538 0.01665 0.00946 -0.0471 0.5774 1.0000
5.750 0.8699 0.01660 0.00937 -0.0441 0.5349 1.0000
6.000 0.8827 0.01675 0.00932 -0.0407 0.4729 1.0000
6.250 0.8897 0.01746 0.00947 -0.0365 0.3915 1.0000
6.500 0.8941 0.01866 0.01010 -0.0324 0.3216 1.0000
6.750 0.9017 0.01996 0.01096 -0.0291 0.2754 1.0000
7.000 0.9132 0.02113 0.01185 -0.0266 0.2428 1.0000
7.250 0.9276 0.02228 0.01274 -0.0245 0.2192 1.0000
7.500 0.9448 0.02337 0.01371 -0.0229 0.1998 1.0000
7.750 0.9637 0.02448 0.01471 -0.0216 0.1844 1.0000
8.000 0.9849 0.02566 0.01581 -0.0207 0.1718 1.0000
8.250 1.0088 0.02695 0.01693 -0.0204 0.1609 1.0000
8.500 1.0285 0.02800 0.01813 -0.0191 0.1515 1.0000
8.750 1.0545 0.02950 0.01955 -0.0191 0.1436 1.0000
9.000 1.0750 0.03068 0.02089 -0.0181 0.1365 1.0000
9.250 1.1009 0.03235 0.02248 -0.0182 0.1300 1.0000
9.500 1.1196 0.03375 0.02415 -0.0169 0.1247 1.0000
9.750 1.1417 0.03523 0.02567 -0.0163 0.1198 1.0000
10.000 1.1618 0.03729 0.02788 -0.0156 0.1154 1.0000
10.250 1.1750 0.03898 0.02990 -0.0137 0.1115 1.0000
10.500 1.1919 0.04078 0.03187 -0.0125 0.1080 1.0000
10.750 1.2146 0.04315 0.03418 -0.0126 0.1043 1.0000
11.000 1.2174 0.04545 0.03693 -0.0096 0.1020 1.0000
11.250 1.2175 0.04783 0.03973 -0.0065 0.1000 1.0000
11.500 1.2165 0.05047 0.04272 -0.0036 0.0983 1.0000
11.750 1.2140 0.05307 0.04561 -0.0007 0.0966 1.0000
12.000 1.2160 0.05529 0.04798 0.0016 0.0945 1.0000
12.250 1.2381 0.05789 0.05049 0.0012 0.0914 1.0000
12.500 1.2270 0.06181 0.05463 0.0041 0.0906 1.0000
12.750 1.2053 0.06484 0.05794 0.0080 0.0904 1.0000
13.000 1.1811 0.06838 0.06174 0.0110 0.0903 1.0000
13.250 1.1553 0.07251 0.06609 0.0129 0.0904 1.0000
13.500 1.1301 0.07730 0.07109 0.0137 0.0905 1.0000
13.750 1.1018 0.08290 0.07687 0.0135 0.0907 1.0000
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