DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-21 AIRFOIL (dae21-il) Reynolds number: 1,000,000 Max Cl/Cd: 173.55 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae21-il-1000000.txt Download as CSV file: xf-dae21-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: DAE-21 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0377 0.08638 0.08355 -0.0769 0.7247 0.0130
-8.250 -0.0300 0.08379 0.08097 -0.0781 0.7223 0.0132
-8.000 -0.0226 0.08120 0.07838 -0.0793 0.7200 0.0135
-7.750 0.0006 0.06429 0.06165 -0.0745 0.7092 0.0148
-7.500 0.0017 0.06024 0.05761 -0.0756 0.7071 0.0149
-7.250 0.0087 0.05755 0.05493 -0.0763 0.7048 0.0150
-7.000 0.0168 0.05517 0.05256 -0.0768 0.7024 0.0151
-6.750 0.0229 0.05268 0.05006 -0.0775 0.7000 0.0153
-6.500 0.0259 0.05021 0.04757 -0.0780 0.6971 0.0154
-6.250 0.0294 0.04769 0.04509 -0.0789 0.6951 0.0157
-6.000 0.0370 0.04458 0.04199 -0.0814 0.6927 0.0160
-5.750 0.0465 0.04112 0.03853 -0.0848 0.6904 0.0164
-5.500 0.0584 0.03693 0.03433 -0.0897 0.6881 0.0170
-5.000 0.1099 0.03515 0.03204 -0.1210 0.6899 0.0181
-4.750 0.1343 0.03290 0.02971 -0.1230 0.6875 0.0183
-4.500 0.1621 0.01968 0.01535 -0.1295 0.6855 0.0179
-4.250 0.1882 0.01733 0.01283 -0.1303 0.6829 0.0170
-4.000 0.2156 0.01431 0.00926 -0.1309 0.6802 0.0167
-3.750 0.2440 0.01280 0.00747 -0.1312 0.6781 0.0168
-3.500 0.2727 0.01191 0.00640 -0.1313 0.6757 0.0171
-3.250 0.3016 0.01147 0.00582 -0.1315 0.6730 0.0177
-3.000 0.3300 0.01057 0.00479 -0.1316 0.6704 0.0182
-2.750 0.3585 0.01014 0.00432 -0.1317 0.6677 0.0188
-2.500 0.3870 0.00988 0.00399 -0.1318 0.6645 0.0194
-2.250 0.4160 0.00956 0.00366 -0.1320 0.6622 0.0201
-2.000 0.4449 0.00929 0.00335 -0.1321 0.6594 0.0207
-1.750 0.4738 0.00897 0.00300 -0.1322 0.6565 0.0215
-1.500 0.5025 0.00869 0.00271 -0.1324 0.6536 0.0225
-1.250 0.5313 0.00858 0.00256 -0.1325 0.6504 0.0240
-1.000 0.5602 0.00843 0.00238 -0.1326 0.6474 0.0253
-0.750 0.5892 0.00822 0.00220 -0.1328 0.6443 0.0271
-0.500 0.6182 0.00811 0.00208 -0.1330 0.6411 0.0291
-0.250 0.6471 0.00797 0.00193 -0.1331 0.6377 0.0331
0.000 0.6758 0.00787 0.00183 -0.1332 0.6342 0.0417
0.250 0.7046 0.00768 0.00178 -0.1334 0.6309 0.0810
0.500 0.7333 0.00744 0.00177 -0.1337 0.6274 0.1650
0.750 0.7617 0.00718 0.00179 -0.1340 0.6236 0.2819
1.000 0.7898 0.00695 0.00184 -0.1342 0.6197 0.4099
1.250 0.8176 0.00674 0.00191 -0.1343 0.6157 0.5427
1.500 0.8451 0.00583 0.00201 -0.1343 0.6118 1.0000
1.750 0.8738 0.00588 0.00202 -0.1344 0.6073 1.0000
2.000 0.9021 0.00598 0.00204 -0.1345 0.6026 1.0000
2.250 0.9307 0.00603 0.00207 -0.1346 0.5982 1.0000
2.500 0.9593 0.00609 0.00210 -0.1348 0.5932 1.0000
2.750 0.9874 0.00618 0.00214 -0.1348 0.5879 1.0000
3.000 1.0157 0.00626 0.00220 -0.1349 0.5828 1.0000
3.250 1.0440 0.00633 0.00225 -0.1351 0.5769 1.0000
3.500 1.0717 0.00645 0.00232 -0.1351 0.5709 1.0000
3.750 1.1000 0.00652 0.00239 -0.1352 0.5650 1.0000
4.000 1.1277 0.00663 0.00247 -0.1353 0.5583 1.0000
4.250 1.1553 0.00675 0.00256 -0.1353 0.5518 1.0000
4.500 1.1830 0.00686 0.00266 -0.1354 0.5444 1.0000
4.750 1.2101 0.00700 0.00277 -0.1354 0.5370 1.0000
5.000 1.2374 0.00713 0.00288 -0.1354 0.5283 1.0000
5.250 1.2642 0.00729 0.00301 -0.1353 0.5196 1.0000
5.500 1.2905 0.00748 0.00316 -0.1352 0.5095 1.0000
5.750 1.3171 0.00765 0.00331 -0.1351 0.4996 1.0000
6.000 1.3429 0.00786 0.00349 -0.1349 0.4891 1.0000
6.500 1.3934 0.00834 0.00390 -0.1344 0.4644 1.0000
6.750 1.4181 0.00861 0.00412 -0.1341 0.4512 1.0000
7.000 1.4419 0.00892 0.00438 -0.1336 0.4366 1.0000
7.250 1.4651 0.00925 0.00466 -0.1331 0.4218 1.0000
7.500 1.4877 0.00961 0.00496 -0.1324 0.4067 1.0000
7.750 1.5092 0.01000 0.00530 -0.1316 0.3906 1.0000
8.000 1.5296 0.01043 0.00567 -0.1307 0.3739 1.0000
8.250 1.5482 0.01092 0.00608 -0.1294 0.3558 1.0000
8.500 1.5652 0.01145 0.00653 -0.1280 0.3383 1.0000
8.750 1.5794 0.01205 0.00705 -0.1260 0.3198 1.0000
9.000 1.5901 0.01265 0.00758 -0.1235 0.3034 1.0000
9.250 1.5955 0.01335 0.00823 -0.1201 0.2881 1.0000
9.500 1.6006 0.01421 0.00903 -0.1170 0.2728 1.0000
9.750 1.6069 0.01517 0.00994 -0.1144 0.2580 1.0000
10.000 1.6130 0.01625 0.01096 -0.1120 0.2421 1.0000
10.250 1.6192 0.01741 0.01206 -0.1098 0.2269 1.0000
10.500 1.6257 0.01861 0.01321 -0.1077 0.2128 1.0000
10.750 1.6317 0.01990 0.01444 -0.1056 0.1986 1.0000
11.000 1.6372 0.02125 0.01574 -0.1036 0.1848 1.0000
11.250 1.6427 0.02266 0.01710 -0.1017 0.1715 1.0000
11.500 1.6476 0.02414 0.01853 -0.0998 0.1584 1.0000
11.750 1.6527 0.02565 0.01999 -0.0981 0.1461 1.0000
12.000 1.6574 0.02722 0.02152 -0.0963 0.1345 1.0000
12.250 1.6617 0.02886 0.02314 -0.0947 0.1237 1.0000
12.500 1.6666 0.03049 0.02474 -0.0931 0.1144 1.0000
12.750 1.6693 0.03234 0.02655 -0.0915 0.1047 1.0000
13.000 1.6746 0.03405 0.02825 -0.0902 0.0966 1.0000
13.250 1.6794 0.03586 0.03005 -0.0889 0.0889 1.0000
13.500 1.6830 0.03784 0.03201 -0.0877 0.0818 1.0000
13.750 1.6883 0.03970 0.03388 -0.0866 0.0756 1.0000
14.000 1.6923 0.04174 0.03592 -0.0856 0.0695 1.0000
14.250 1.6961 0.04385 0.03803 -0.0846 0.0641 1.0000
14.500 1.7008 0.04593 0.04013 -0.0837 0.0594 1.0000
14.750 1.7034 0.04826 0.04246 -0.0829 0.0547 1.0000
15.000 1.7087 0.05037 0.04461 -0.0822 0.0512 1.0000
15.250 1.7101 0.05293 0.04718 -0.0815 0.0472 1.0000
15.500 1.7152 0.05514 0.04944 -0.0810 0.0443 1.0000
15.750 1.7161 0.05789 0.05220 -0.0805 0.0411 1.0000
16.000 1.7204 0.06027 0.05464 -0.0801 0.0386 1.0000
16.250 1.7214 0.06311 0.05751 -0.0798 0.0361 1.0000
16.500 1.7225 0.06597 0.06042 -0.0796 0.0338 1.0000
16.750 1.7250 0.06872 0.06322 -0.0794 0.0320 1.0000
17.000 1.7239 0.07199 0.06654 -0.0794 0.0300 1.0000
17.250 1.7251 0.07500 0.06961 -0.0794 0.0286 1.0000
17.500 1.7260 0.07811 0.07279 -0.0796 0.0273 1.0000
17.750 1.7245 0.08160 0.07635 -0.0799 0.0260 1.0000
18.000 1.7205 0.08553 0.08033 -0.0803 0.0246 1.0000
18.250 1.7220 0.08869 0.08357 -0.0807 0.0238 1.0000
18.500 1.7208 0.09227 0.08724 -0.0813 0.0228 1.0000
18.750 1.7184 0.09609 0.09111 -0.0820 0.0219 1.0000
19.000 1.7118 0.10066 0.09575 -0.0830 0.0210 1.0000
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Polar data table (+)
Polar graphs
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