S2027 (s2027-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S2027 (s2027-il) Reynolds number: 500,000 Max Cl/Cd: 95.23 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2027-il-500000-n5.txt Download as CSV file: xf-s2027-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2027
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6645 0.07531 0.07242 -0.0488 1.0000 0.0092
-13.500 -0.6865 0.06707 0.06404 -0.0546 1.0000 0.0091
-13.250 -0.7133 0.05878 0.05556 -0.0604 1.0000 0.0091
-13.000 -0.7290 0.05296 0.04957 -0.0646 1.0000 0.0091
-12.750 -0.7417 0.04814 0.04460 -0.0677 1.0000 0.0091
-12.500 -0.7517 0.04410 0.04040 -0.0700 1.0000 0.0091
-12.250 -0.7597 0.04066 0.03680 -0.0714 1.0000 0.0092
-12.000 -0.7708 0.03721 0.03317 -0.0722 1.0000 0.0092
-11.750 -0.7761 0.03466 0.03047 -0.0721 1.0000 0.0092
-11.250 -0.7603 0.02961 0.02503 -0.0748 0.9429 0.0096
-11.000 -0.7554 0.02843 0.02370 -0.0728 0.9205 0.0098
-10.750 -0.7469 0.02734 0.02245 -0.0710 0.9043 0.0099
-10.500 -0.7359 0.02627 0.02124 -0.0694 0.8910 0.0101
-10.250 -0.7221 0.02534 0.02016 -0.0680 0.8795 0.0102
-10.000 -0.7072 0.02431 0.01898 -0.0667 0.8686 0.0104
-9.750 -0.6906 0.02328 0.01779 -0.0656 0.8583 0.0106
-9.500 -0.6730 0.02228 0.01663 -0.0646 0.8491 0.0108
-9.250 -0.6539 0.02137 0.01557 -0.0637 0.8397 0.0110
-9.000 -0.6339 0.02048 0.01454 -0.0629 0.8310 0.0112
-8.500 -0.5917 0.01888 0.01269 -0.0614 0.8136 0.0116
-8.250 -0.5697 0.01817 0.01185 -0.0607 0.8054 0.0118
-8.000 -0.5468 0.01752 0.01110 -0.0601 0.7967 0.0121
-7.750 -0.5236 0.01691 0.01037 -0.0596 0.7889 0.0122
-7.500 -0.5000 0.01634 0.00971 -0.0591 0.7803 0.0124
-7.250 -0.4759 0.01583 0.00910 -0.0586 0.7723 0.0126
-7.000 -0.4533 0.01507 0.00825 -0.0580 0.7640 0.0129
-6.750 -0.4298 0.01442 0.00755 -0.0576 0.7558 0.0134
-6.500 -0.4049 0.01397 0.00702 -0.0572 0.7477 0.0139
-6.250 -0.3794 0.01356 0.00655 -0.0570 0.7395 0.0144
-6.000 -0.3538 0.01317 0.00608 -0.0567 0.7315 0.0149
-5.750 -0.3277 0.01280 0.00564 -0.0565 0.7232 0.0154
-5.500 -0.3014 0.01248 0.00523 -0.0563 0.7152 0.0159
-5.250 -0.2747 0.01219 0.00487 -0.0561 0.7066 0.0163
-5.000 -0.2480 0.01189 0.00449 -0.0560 0.6989 0.0171
-4.750 -0.2212 0.01161 0.00415 -0.0558 0.6902 0.0181
-4.500 -0.1940 0.01137 0.00385 -0.0558 0.6824 0.0195
-4.250 -0.1667 0.01117 0.00359 -0.0557 0.6739 0.0214
-4.000 -0.1398 0.01088 0.00333 -0.0556 0.6659 0.0310
-3.750 -0.1136 0.01048 0.00304 -0.0555 0.6578 0.0661
-3.500 -0.0870 0.01011 0.00281 -0.0555 0.6496 0.1065
-3.000 -0.0339 0.00939 0.00242 -0.0555 0.6334 0.2117
-2.750 -0.0072 0.00909 0.00226 -0.0555 0.6256 0.2657
-2.500 0.0197 0.00877 0.00213 -0.0555 0.6174 0.3284
-2.250 0.0461 0.00844 0.00203 -0.0555 0.6098 0.4027
-2.000 0.0731 0.00821 0.00199 -0.0554 0.6016 0.4659
-1.750 0.1008 0.00812 0.00195 -0.0554 0.5939 0.4993
-1.500 0.1289 0.00808 0.00192 -0.0554 0.5857 0.5234
-1.250 0.1570 0.00806 0.00190 -0.0555 0.5781 0.5441
-1.000 0.1852 0.00806 0.00189 -0.0555 0.5700 0.5619
-0.750 0.2134 0.00806 0.00189 -0.0556 0.5625 0.5771
-0.500 0.2417 0.00808 0.00188 -0.0556 0.5546 0.5910
-0.250 0.2700 0.00811 0.00189 -0.0557 0.5471 0.6039
0.000 0.2981 0.00813 0.00190 -0.0557 0.5391 0.6159
0.250 0.3263 0.00816 0.00192 -0.0558 0.5316 0.6271
0.500 0.3544 0.00821 0.00194 -0.0559 0.5237 0.6378
0.750 0.3827 0.00825 0.00198 -0.0559 0.5163 0.6484
1.000 0.4106 0.00830 0.00201 -0.0559 0.5085 0.6584
1.250 0.4388 0.00834 0.00206 -0.0560 0.5012 0.6686
1.500 0.4666 0.00841 0.00211 -0.0560 0.4934 0.6790
1.750 0.4945 0.00845 0.00217 -0.0561 0.4859 0.6891
2.000 0.5222 0.00853 0.00223 -0.0561 0.4781 0.6996
2.250 0.5500 0.00859 0.00231 -0.0561 0.4703 0.7107
2.500 0.5773 0.00867 0.00239 -0.0560 0.4626 0.7219
2.750 0.6050 0.00872 0.00247 -0.0560 0.4548 0.7333
3.000 0.6321 0.00882 0.00257 -0.0559 0.4470 0.7454
3.500 0.6862 0.00898 0.00279 -0.0557 0.4311 0.7719
3.750 0.7130 0.00906 0.00290 -0.0556 0.4229 0.7864
4.000 0.7394 0.00916 0.00304 -0.0554 0.4151 0.8021
4.250 0.7656 0.00925 0.00317 -0.0551 0.4067 0.8193
4.500 0.7911 0.00934 0.00332 -0.0547 0.3989 0.8383
4.750 0.8160 0.00944 0.00348 -0.0541 0.3905 0.8602
5.000 0.8403 0.00953 0.00363 -0.0534 0.3826 0.8856
5.250 0.8643 0.00964 0.00379 -0.0526 0.3743 0.9173
5.500 0.8951 0.00976 0.00396 -0.0533 0.3656 0.9537
5.750 0.9321 0.00996 0.00415 -0.0556 0.3563 1.0000
6.000 0.9577 0.01017 0.00434 -0.0553 0.3471 1.0000
6.250 0.9831 0.01039 0.00455 -0.0551 0.3387 1.0000
6.500 1.0079 0.01064 0.00478 -0.0548 0.3297 1.0000
6.750 1.0332 0.01085 0.00500 -0.0545 0.3213 1.0000
7.000 1.0576 0.01112 0.00525 -0.0541 0.3127 1.0000
7.250 1.0822 0.01137 0.00550 -0.0538 0.3037 1.0000
7.500 1.1062 0.01165 0.00578 -0.0534 0.2942 1.0000
7.750 1.1290 0.01199 0.00609 -0.0528 0.2821 1.0000
8.000 1.1512 0.01235 0.00641 -0.0521 0.2694 1.0000
8.250 1.1725 0.01275 0.00677 -0.0513 0.2548 1.0000
8.500 1.1930 0.01318 0.00716 -0.0504 0.2392 1.0000
8.750 1.2127 0.01363 0.00756 -0.0494 0.2245 1.0000
9.000 1.2312 0.01412 0.00800 -0.0482 0.2094 1.0000
9.250 1.2480 0.01467 0.00849 -0.0467 0.1929 1.0000
9.500 1.2610 0.01528 0.00903 -0.0447 0.1754 1.0000
9.750 1.2702 0.01600 0.00966 -0.0421 0.1577 1.0000
10.000 1.2790 0.01678 0.01038 -0.0397 0.1398 1.0000
10.250 1.2842 0.01780 0.01129 -0.0370 0.1194 1.0000
10.500 1.2881 0.01897 0.01235 -0.0343 0.0984 1.0000
10.750 1.2940 0.02011 0.01342 -0.0322 0.0840 1.0000
11.000 1.2998 0.02131 0.01459 -0.0302 0.0719 1.0000
11.250 1.3061 0.02256 0.01581 -0.0284 0.0620 1.0000
11.500 1.3126 0.02387 0.01712 -0.0269 0.0541 1.0000
11.750 1.3174 0.02537 0.01862 -0.0253 0.0463 1.0000
12.000 1.3228 0.02690 0.02015 -0.0240 0.0399 1.0000
12.250 1.3282 0.02850 0.02178 -0.0229 0.0347 1.0000
12.750 1.3348 0.03225 0.02556 -0.0209 0.0252 1.0000
13.000 1.3388 0.03417 0.02753 -0.0201 0.0223 1.0000
13.250 1.3415 0.03629 0.02970 -0.0195 0.0191 1.0000
13.500 1.3425 0.03865 0.03210 -0.0190 0.0161 1.0000
14.000 1.3442 0.04365 0.03721 -0.0184 0.0124 1.0000
14.250 1.3429 0.04653 0.04015 -0.0183 0.0109 1.0000
14.500 1.3438 0.04926 0.04298 -0.0184 0.0104 1.0000
14.750 1.3435 0.05224 0.04604 -0.0186 0.0097 1.0000
15.000 1.3428 0.05534 0.04923 -0.0190 0.0091 1.0000
15.250 1.3417 0.05857 0.05256 -0.0195 0.0087 1.0000
15.500 1.3396 0.06203 0.05611 -0.0202 0.0084 1.0000
15.750 1.3361 0.06577 0.05993 -0.0210 0.0080 1.0000
16.000 1.3320 0.06967 0.06393 -0.0220 0.0078 1.0000
16.250 1.3276 0.07373 0.06808 -0.0232 0.0075 1.0000
16.500 1.3244 0.07771 0.07217 -0.0244 0.0072 1.0000
16.750 1.3202 0.08190 0.07646 -0.0257 0.0071 1.0000
17.000 1.3155 0.08626 0.08094 -0.0272 0.0070 1.0000
17.250 1.3104 0.09078 0.08556 -0.0289 0.0068 1.0000
17.500 1.3054 0.09535 0.09023 -0.0307 0.0066 1.0000
17.750 1.3000 0.10005 0.09503 -0.0325 0.0064 1.0000
18.000 1.2942 0.10489 0.09999 -0.0346 0.0063 1.0000
18.250 1.2884 0.10981 0.10500 -0.0367 0.0061 1.0000
18.500 1.2825 0.11481 0.11011 -0.0390 0.0060 1.0000
18.750 1.2746 0.12020 0.11560 -0.0415 0.0059 1.0000
19.000 1.2691 0.12525 0.12074 -0.0439 0.0058 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2027 (s2027-il)