S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 500,000 Max Cl/Cd: 109.97 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-il-500000-n5.txt Download as CSV file: xf-s1221-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2647 0.08401 0.08172 -0.0408 0.9886 0.0102
-7.500 -0.3482 0.05994 0.05762 -0.0529 0.9803 0.0097
-7.250 -0.3733 0.04314 0.04058 -0.0739 0.9627 0.0095
-6.750 -0.2691 0.02333 0.01939 -0.1199 0.9391 0.0096
-6.500 -0.2203 0.02024 0.01591 -0.1273 0.9245 0.0099
-6.250 -0.0596 0.01688 0.01171 -0.1577 0.8101 0.0105
-6.000 -0.0324 0.01645 0.01064 -0.1581 0.7090 0.0106
-5.750 -0.0048 0.01579 0.00966 -0.1586 0.6671 0.0107
-5.500 0.0238 0.01519 0.00880 -0.1591 0.6277 0.0108
-5.250 0.0528 0.01467 0.00801 -0.1596 0.5899 0.0110
-5.000 0.0827 0.01418 0.00731 -0.1603 0.5591 0.0112
-4.750 0.1133 0.01375 0.00668 -0.1611 0.5340 0.0114
-4.500 0.1444 0.01334 0.00611 -0.1619 0.5133 0.0116
-4.250 0.1757 0.01298 0.00560 -0.1627 0.4959 0.0120
-4.000 0.2070 0.01268 0.00516 -0.1635 0.4809 0.0123
-3.750 0.2389 0.01235 0.00470 -0.1644 0.4668 0.0127
-3.500 0.2706 0.01207 0.00431 -0.1652 0.4540 0.0132
-3.250 0.3017 0.01187 0.00402 -0.1658 0.4431 0.0138
-2.500 0.3938 0.01144 0.00332 -0.1672 0.4163 0.0174
-2.250 0.4245 0.01131 0.00313 -0.1676 0.4089 0.0199
-2.000 0.4555 0.01118 0.00296 -0.1681 0.4014 0.0301
-1.750 0.4885 0.01085 0.00277 -0.1693 0.3947 0.0860
-1.500 0.5230 0.01039 0.00264 -0.1710 0.3872 0.2082
-1.250 0.5526 0.01040 0.00270 -0.1712 0.3808 0.2554
-1.000 0.5818 0.01044 0.00277 -0.1713 0.3749 0.2825
-0.750 0.6106 0.01052 0.00281 -0.1712 0.3693 0.2967
-0.500 0.6395 0.01059 0.00283 -0.1712 0.3645 0.3033
-0.250 0.6684 0.01064 0.00283 -0.1711 0.3599 0.3068
0.000 0.6973 0.01070 0.00284 -0.1711 0.3550 0.3099
0.250 0.7261 0.01078 0.00287 -0.1711 0.3503 0.3135
0.500 0.7551 0.01084 0.00291 -0.1710 0.3461 0.3181
0.750 0.7839 0.01091 0.00295 -0.1710 0.3417 0.3227
1.000 0.8125 0.01100 0.00301 -0.1709 0.3378 0.3268
1.250 0.8411 0.01109 0.00308 -0.1708 0.3341 0.3317
1.500 0.8699 0.01117 0.00316 -0.1708 0.3309 0.3373
1.750 0.8985 0.01125 0.00323 -0.1707 0.3273 0.3429
2.000 0.9272 0.01134 0.00332 -0.1707 0.3237 0.3494
2.250 0.9556 0.01145 0.00343 -0.1706 0.3206 0.3569
2.500 0.9839 0.01158 0.00355 -0.1705 0.3177 0.3650
2.750 1.0124 0.01167 0.00367 -0.1705 0.3153 0.3750
3.000 1.0410 0.01176 0.00380 -0.1704 0.3125 0.3854
3.250 1.0694 0.01186 0.00393 -0.1704 0.3095 0.3965
3.500 1.0977 0.01198 0.00408 -0.1703 0.3067 0.4092
3.750 1.1258 0.01212 0.00424 -0.1702 0.3042 0.4231
4.000 1.1539 0.01228 0.00442 -0.1701 0.3017 0.4384
4.250 1.1822 0.01239 0.00460 -0.1701 0.2998 0.4557
4.500 1.2106 0.01249 0.00477 -0.1700 0.2975 0.4752
4.750 1.2390 0.01261 0.00497 -0.1700 0.2948 0.4980
5.000 1.2673 0.01273 0.00517 -0.1700 0.2923 0.5259
5.250 1.2955 0.01287 0.00539 -0.1700 0.2898 0.5579
5.500 1.3236 0.01303 0.00563 -0.1700 0.2870 0.5959
5.750 1.3521 0.01314 0.00589 -0.1700 0.2844 0.6479
6.000 1.3804 0.01318 0.00617 -0.1700 0.2816 0.7326
6.250 1.4073 0.01328 0.00641 -0.1696 0.2782 0.7907
6.500 1.4327 0.01339 0.00662 -0.1690 0.2745 0.8382
6.750 1.4521 0.01344 0.00678 -0.1670 0.2712 0.9137
7.000 1.4758 0.01357 0.00696 -0.1660 0.2684 1.0000
7.250 1.5031 0.01375 0.00719 -0.1658 0.2653 1.0000
7.500 1.5301 0.01395 0.00743 -0.1656 0.2618 1.0000
7.750 1.5567 0.01419 0.00768 -0.1653 0.2577 1.0000
8.000 1.5831 0.01445 0.00794 -0.1650 0.2536 1.0000
8.250 1.6099 0.01464 0.00818 -0.1647 0.2483 1.0000
8.500 1.6359 0.01491 0.00845 -0.1643 0.2421 1.0000
8.750 1.6619 0.01516 0.00873 -0.1640 0.2347 1.0000
9.000 1.6871 0.01550 0.00903 -0.1635 0.2251 1.0000
9.250 1.7125 0.01581 0.00937 -0.1631 0.2159 1.0000
9.500 1.7372 0.01620 0.00975 -0.1626 0.2066 1.0000
9.750 1.7612 0.01666 0.01018 -0.1620 0.1966 1.0000
10.000 1.7847 0.01716 0.01067 -0.1613 0.1848 1.0000
10.250 1.8069 0.01779 0.01124 -0.1605 0.1704 1.0000
10.500 1.8281 0.01853 0.01192 -0.1595 0.1549 1.0000
10.750 1.8486 0.01931 0.01266 -0.1585 0.1411 1.0000
11.000 1.8684 0.02014 0.01346 -0.1573 0.1284 1.0000
11.250 1.8871 0.02104 0.01432 -0.1561 0.1161 1.0000
11.500 1.9051 0.02197 0.01522 -0.1547 0.1051 1.0000
11.750 1.9227 0.02287 0.01613 -0.1532 0.0954 1.0000
12.000 1.9394 0.02380 0.01707 -0.1517 0.0872 1.0000
12.250 1.9540 0.02485 0.01813 -0.1498 0.0793 1.0000
12.500 1.9669 0.02596 0.01925 -0.1478 0.0718 1.0000
12.750 1.9774 0.02711 0.02043 -0.1453 0.0654 1.0000
13.250 1.9868 0.02967 0.02308 -0.1387 0.0557 1.0000
13.500 1.9884 0.03123 0.02470 -0.1353 0.0520 1.0000
13.750 1.9911 0.03278 0.02634 -0.1323 0.0491 1.0000
14.000 1.9906 0.03466 0.02830 -0.1294 0.0463 1.0000
14.250 1.9859 0.03703 0.03075 -0.1265 0.0439 1.0000
14.500 1.9821 0.03956 0.03341 -0.1244 0.0422 1.0000
14.750 1.9759 0.04264 0.03661 -0.1229 0.0406 1.0000
15.000 1.9651 0.04673 0.04083 -0.1224 0.0389 1.0000
15.250 1.9521 0.05179 0.04604 -0.1231 0.0380 1.0000
15.500 1.9342 0.05816 0.05258 -0.1248 0.0369 1.0000
16.000 1.8924 0.07292 0.06770 -0.1296 0.0358 1.0000
16.250 1.8688 0.08090 0.07585 -0.1322 0.0356 1.0000
16.500 1.8451 0.08895 0.08407 -0.1350 0.0353 1.0000
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Polar data table (+)
Polar graphs
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