S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 500,000 Max Cl/Cd: 107.54 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-il-500000.txt Download as CSV file: xf-s1221-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S1221 w/o flap
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3065 0.09567 0.09353 -0.0233 1.0000 0.0227
-7.500 -0.3132 0.09092 0.08883 -0.0252 1.0000 0.0228
-7.250 -0.3126 0.08830 0.08624 -0.0242 1.0000 0.0230
-7.000 -0.3088 0.08667 0.08465 -0.0229 1.0000 0.0232
-6.750 -0.2952 0.08390 0.08189 -0.0252 0.9987 0.0235
-6.500 -0.2698 0.08057 0.07857 -0.0305 0.9955 0.0244
-6.250 -0.2521 0.07611 0.07412 -0.0363 0.9913 0.0251
-6.000 -0.2389 0.04472 0.04241 -0.0894 0.9776 0.0277
-5.750 -0.2152 0.04331 0.04112 -0.0889 0.9708 0.0281
-5.500 -0.1755 0.03840 0.03607 -0.0996 0.9627 0.0290
-5.250 -0.1085 0.02902 0.02582 -0.1215 0.9546 0.0335
-4.500 0.1152 0.01361 0.00838 -0.1557 0.8730 0.0195
-4.250 0.1854 0.01306 0.00693 -0.1645 0.7217 0.0193
-4.000 0.2129 0.01266 0.00624 -0.1644 0.6717 0.0194
-3.750 0.2420 0.01227 0.00564 -0.1647 0.6269 0.0198
-3.500 0.2715 0.01200 0.00515 -0.1651 0.5858 0.0204
-3.250 0.3019 0.01177 0.00471 -0.1656 0.5530 0.0213
-3.000 0.3330 0.01156 0.00432 -0.1662 0.5279 0.0223
-2.750 0.3651 0.01128 0.00389 -0.1671 0.5076 0.0236
-2.500 0.3962 0.01113 0.00361 -0.1677 0.4909 0.0259
-2.250 0.4275 0.01097 0.00334 -0.1683 0.4767 0.0306
-2.000 0.4683 0.00994 0.00290 -0.1718 0.4635 0.2315
-1.750 0.4972 0.01004 0.00295 -0.1718 0.4521 0.2672
-1.500 0.5260 0.01013 0.00299 -0.1717 0.4419 0.2843
-1.250 0.5542 0.01030 0.00308 -0.1715 0.4324 0.3022
-1.000 0.5827 0.01045 0.00320 -0.1713 0.4240 0.3206
-0.750 0.6110 0.01061 0.00327 -0.1712 0.4162 0.3319
-0.500 0.6400 0.01066 0.00329 -0.1711 0.4092 0.3385
-0.250 0.6686 0.01078 0.00330 -0.1710 0.4024 0.3428
0.000 0.6977 0.01080 0.00330 -0.1711 0.3962 0.3474
0.250 0.7267 0.01085 0.00333 -0.1710 0.3900 0.3518
0.500 0.7551 0.01097 0.00337 -0.1709 0.3842 0.3566
0.750 0.7841 0.01104 0.00341 -0.1709 0.3793 0.3618
1.000 0.8132 0.01108 0.00348 -0.1709 0.3745 0.3680
1.250 0.8417 0.01120 0.00354 -0.1709 0.3699 0.3745
1.500 0.8703 0.01134 0.00365 -0.1708 0.3653 0.3814
1.750 0.8993 0.01138 0.00373 -0.1709 0.3614 0.3899
2.000 0.9282 0.01146 0.00383 -0.1709 0.3575 0.3991
2.250 0.9568 0.01159 0.00394 -0.1708 0.3539 0.4103
2.500 0.9852 0.01178 0.00412 -0.1708 0.3500 0.4230
2.750 1.0142 0.01185 0.00426 -0.1708 0.3471 0.4385
3.000 1.0431 0.01192 0.00440 -0.1709 0.3438 0.4570
3.250 1.0719 0.01202 0.00454 -0.1709 0.3405 0.4784
3.500 1.1007 0.01215 0.00472 -0.1710 0.3375 0.5035
3.750 1.1292 0.01236 0.00496 -0.1710 0.3343 0.5336
4.000 1.1583 0.01247 0.00519 -0.1712 0.3318 0.5707
4.250 1.1877 0.01252 0.00540 -0.1713 0.3292 0.6201
4.500 1.2167 0.01254 0.00566 -0.1714 0.3262 0.7044
4.750 1.2436 0.01260 0.00590 -0.1710 0.3235 0.7906
5.000 1.2677 0.01268 0.00611 -0.1699 0.3209 0.8572
5.250 1.2836 0.01273 0.00623 -0.1671 0.3181 1.0000
5.500 1.3118 0.01293 0.00645 -0.1670 0.3155 1.0000
5.750 1.3399 0.01308 0.00664 -0.1670 0.3127 1.0000
6.000 1.3677 0.01326 0.00683 -0.1668 0.3096 1.0000
6.250 1.3952 0.01345 0.00702 -0.1667 0.3063 1.0000
6.500 1.4223 0.01377 0.00728 -0.1665 0.3026 1.0000
6.750 1.4496 0.01399 0.00754 -0.1663 0.2995 1.0000
7.000 1.4770 0.01415 0.00776 -0.1661 0.2965 1.0000
7.250 1.5041 0.01434 0.00798 -0.1659 0.2933 1.0000
7.500 1.5309 0.01455 0.00821 -0.1656 0.2900 1.0000
7.750 1.5571 0.01494 0.00855 -0.1653 0.2860 1.0000
8.000 1.5839 0.01508 0.00878 -0.1650 0.2827 1.0000
8.250 1.6105 0.01521 0.00898 -0.1647 0.2785 1.0000
8.500 1.6367 0.01539 0.00918 -0.1644 0.2740 1.0000
8.750 1.6622 0.01568 0.00947 -0.1639 0.2689 1.0000
9.000 1.6888 0.01575 0.00964 -0.1636 0.2634 1.0000
9.250 1.7145 0.01596 0.00987 -0.1632 0.2582 1.0000
9.500 1.7398 0.01624 0.01018 -0.1627 0.2531 1.0000
9.750 1.7658 0.01642 0.01045 -0.1624 0.2476 1.0000
10.000 1.7905 0.01671 0.01074 -0.1618 0.2414 1.0000
10.250 1.8159 0.01694 0.01106 -0.1614 0.2345 1.0000
10.500 1.8398 0.01730 0.01140 -0.1607 0.2261 1.0000
10.750 1.8644 0.01761 0.01178 -0.1602 0.2170 1.0000
11.000 1.8875 0.01805 0.01223 -0.1595 0.2063 1.0000
11.250 1.9093 0.01862 0.01277 -0.1586 0.1930 1.0000
11.500 1.9299 0.01931 0.01343 -0.1575 0.1777 1.0000
11.750 1.9486 0.02018 0.01424 -0.1562 0.1611 1.0000
12.000 1.9652 0.02121 0.01520 -0.1547 0.1451 1.0000
12.250 1.9802 0.02236 0.01629 -0.1529 0.1303 1.0000
12.500 1.9938 0.02355 0.01745 -0.1509 0.1166 1.0000
12.750 2.0052 0.02484 0.01871 -0.1487 0.1039 1.0000
13.000 2.0142 0.02620 0.02005 -0.1460 0.0931 1.0000
13.250 2.0187 0.02755 0.02143 -0.1426 0.0841 1.0000
13.500 2.0204 0.02902 0.02294 -0.1389 0.0769 1.0000
14.000 2.0183 0.03257 0.02659 -0.1318 0.0657 1.0000
14.250 2.0117 0.03494 0.02901 -0.1283 0.0615 1.0000
14.500 2.0073 0.03733 0.03151 -0.1256 0.0585 1.0000
14.750 2.0001 0.04024 0.03453 -0.1234 0.0559 1.0000
15.000 1.9871 0.04418 0.03859 -0.1221 0.0538 1.0000
15.250 1.9692 0.04950 0.04406 -0.1223 0.0522 1.0000
15.500 1.9516 0.05561 0.05033 -0.1236 0.0509 1.0000
15.750 1.9348 0.06205 0.05696 -0.1255 0.0500 1.0000
16.000 1.9140 0.06942 0.06451 -0.1279 0.0491 1.0000
16.250 1.8894 0.07750 0.07277 -0.1306 0.0485 1.0000
16.500 1.8633 0.08589 0.08132 -0.1333 0.0480 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S1221 w/o flap (s1221-il)