S2027 (s2027-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S2027 (s2027-il) Reynolds number: 500,000 Max Cl/Cd: 99.61 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2027-il-500000.txt Download as CSV file: xf-s2027-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4192 0.09014 0.08799 -0.0434 1.0000 0.0299
-10.750 -0.4227 0.08517 0.08305 -0.0461 1.0000 0.0305
-9.250 -0.6022 0.03147 0.02721 -0.0725 0.9158 0.0205
-9.000 -0.5970 0.02812 0.02349 -0.0704 0.9034 0.0196
-8.750 -0.5827 0.02642 0.02153 -0.0689 0.8931 0.0199
-8.500 -0.5672 0.02445 0.01928 -0.0674 0.8836 0.0198
-8.250 -0.5489 0.02249 0.01705 -0.0662 0.8740 0.0196
-8.000 -0.5288 0.02095 0.01528 -0.0651 0.8658 0.0196
-7.750 -0.5068 0.01968 0.01384 -0.0643 0.8568 0.0197
-7.500 -0.4844 0.01859 0.01261 -0.0635 0.8486 0.0199
-7.250 -0.4614 0.01765 0.01154 -0.0627 0.8401 0.0201
-7.000 -0.4379 0.01682 0.01061 -0.0621 0.8319 0.0204
-6.750 -0.4145 0.01605 0.00972 -0.0613 0.8237 0.0207
-6.500 -0.3904 0.01537 0.00895 -0.0608 0.8152 0.0210
-6.250 -0.3663 0.01479 0.00827 -0.0601 0.8074 0.0213
-6.000 -0.3430 0.01399 0.00740 -0.0595 0.7986 0.0219
-5.750 -0.3200 0.01322 0.00655 -0.0588 0.7909 0.0230
-5.500 -0.2949 0.01270 0.00597 -0.0584 0.7820 0.0239
-5.250 -0.2693 0.01229 0.00548 -0.0581 0.7742 0.0248
-5.000 -0.2430 0.01192 0.00503 -0.0578 0.7656 0.0261
-4.750 -0.2164 0.01161 0.00464 -0.0575 0.7575 0.0274
-4.500 -0.1900 0.01122 0.00418 -0.0572 0.7492 0.0306
-4.250 -0.1633 0.01087 0.00383 -0.0570 0.7408 0.0393
-4.000 -0.1399 0.00998 0.00335 -0.0567 0.7329 0.1315
-3.750 -0.1150 0.00931 0.00306 -0.0566 0.7243 0.2239
-3.500 -0.0893 0.00887 0.00283 -0.0564 0.7165 0.2998
-3.250 -0.0629 0.00848 0.00268 -0.0564 0.7077 0.3691
-3.000 -0.0362 0.00823 0.00256 -0.0562 0.6998 0.4259
-2.750 -0.0088 0.00805 0.00248 -0.0562 0.6911 0.4704
-2.500 0.0187 0.00794 0.00243 -0.0561 0.6831 0.5107
-2.250 0.0462 0.00786 0.00241 -0.0560 0.6746 0.5485
-2.000 0.0740 0.00783 0.00241 -0.0559 0.6664 0.5791
-1.750 0.1020 0.00783 0.00238 -0.0558 0.6582 0.5986
-1.500 0.1303 0.00782 0.00236 -0.0558 0.6497 0.6144
-1.250 0.1584 0.00785 0.00233 -0.0558 0.6419 0.6289
-1.000 0.1867 0.00784 0.00233 -0.0558 0.6333 0.6424
-0.750 0.2148 0.00788 0.00231 -0.0558 0.6256 0.6549
-0.500 0.2433 0.00789 0.00230 -0.0558 0.6171 0.6672
-0.250 0.2713 0.00792 0.00231 -0.0558 0.6093 0.6787
0.000 0.2994 0.00792 0.00232 -0.0558 0.6009 0.6898
0.250 0.3275 0.00796 0.00232 -0.0558 0.5932 0.7010
0.750 0.3836 0.00801 0.00237 -0.0558 0.5772 0.7232
1.000 0.4114 0.00805 0.00239 -0.0558 0.5691 0.7341
1.250 0.4394 0.00808 0.00243 -0.0558 0.5614 0.7457
1.500 0.4671 0.00814 0.00247 -0.0557 0.5535 0.7578
1.750 0.4947 0.00816 0.00253 -0.0557 0.5455 0.7699
2.000 0.5219 0.00822 0.00258 -0.0555 0.5378 0.7827
2.250 0.5493 0.00824 0.00265 -0.0554 0.5297 0.7965
2.500 0.5761 0.00832 0.00272 -0.0552 0.5221 0.8113
2.750 0.6030 0.00833 0.00280 -0.0550 0.5138 0.8273
3.000 0.6291 0.00841 0.00289 -0.0546 0.5063 0.8451
3.250 0.6551 0.00843 0.00298 -0.0542 0.4980 0.8651
3.500 0.6796 0.00849 0.00307 -0.0534 0.4904 0.8875
3.750 0.7039 0.00851 0.00317 -0.0525 0.4821 0.9145
4.000 0.7309 0.00857 0.00326 -0.0522 0.4742 0.9452
4.250 0.7680 0.00867 0.00336 -0.0542 0.4649 0.9726
4.500 0.8093 0.00879 0.00347 -0.0573 0.4555 0.9972
4.750 0.8360 0.00898 0.00360 -0.0574 0.4471 1.0000
5.000 0.8622 0.00910 0.00373 -0.0572 0.4382 1.0000
5.250 0.8879 0.00929 0.00388 -0.0570 0.4299 1.0000
5.500 0.9139 0.00946 0.00404 -0.0569 0.4209 1.0000
5.750 0.9399 0.00964 0.00421 -0.0567 0.4122 1.0000
6.250 0.9912 0.01003 0.00458 -0.0562 0.3940 1.0000
6.500 1.0164 0.01026 0.00480 -0.0560 0.3851 1.0000
6.750 1.0415 0.01049 0.00501 -0.0557 0.3759 1.0000
7.000 1.0668 0.01071 0.00524 -0.0554 0.3669 1.0000
7.250 1.0909 0.01099 0.00550 -0.0550 0.3579 1.0000
7.500 1.1156 0.01122 0.00575 -0.0546 0.3477 1.0000
7.750 1.1396 0.01148 0.00602 -0.0542 0.3367 1.0000
8.000 1.1628 0.01179 0.00630 -0.0536 0.3257 1.0000
8.250 1.1851 0.01212 0.00661 -0.0529 0.3133 1.0000
8.500 1.2070 0.01247 0.00694 -0.0522 0.3006 1.0000
8.750 1.2293 0.01278 0.00726 -0.0515 0.2888 1.0000
9.000 1.2504 0.01315 0.00762 -0.0507 0.2761 1.0000
9.250 1.2703 0.01356 0.00801 -0.0497 0.2630 1.0000
9.500 1.2890 0.01401 0.00843 -0.0485 0.2492 1.0000
9.750 1.3058 0.01451 0.00891 -0.0470 0.2338 1.0000
10.000 1.3189 0.01507 0.00941 -0.0450 0.2178 1.0000
10.250 1.3294 0.01570 0.00999 -0.0425 0.2019 1.0000
10.500 1.3383 0.01645 0.01068 -0.0401 0.1853 1.0000
10.750 1.3477 0.01725 0.01143 -0.0379 0.1692 1.0000
11.000 1.3551 0.01819 0.01231 -0.0356 0.1521 1.0000
11.250 1.3601 0.01933 0.01338 -0.0332 0.1346 1.0000
11.500 1.3635 0.02064 0.01462 -0.0310 0.1179 1.0000
11.750 1.3661 0.02211 0.01602 -0.0288 0.1005 1.0000
12.000 1.3667 0.02379 0.01763 -0.0268 0.0846 1.0000
12.250 1.3670 0.02560 0.01938 -0.0250 0.0716 1.0000
12.500 1.3685 0.02744 0.02120 -0.0235 0.0615 1.0000
12.750 1.3672 0.02960 0.02333 -0.0221 0.0508 1.0000
13.000 1.3675 0.03172 0.02547 -0.0210 0.0432 1.0000
13.250 1.3663 0.03409 0.02783 -0.0200 0.0364 1.0000
13.500 1.3614 0.03692 0.03066 -0.0192 0.0290 1.0000
13.750 1.3538 0.04014 0.03389 -0.0185 0.0233 1.0000
14.000 1.3522 0.04291 0.03673 -0.0182 0.0204 1.0000
14.250 1.3434 0.04659 0.04046 -0.0181 0.0177 1.0000
14.500 1.3431 0.04949 0.04347 -0.0182 0.0169 1.0000
14.750 1.3399 0.05282 0.04689 -0.0184 0.0156 1.0000
15.000 1.3342 0.05656 0.05071 -0.0189 0.0147 1.0000
15.250 1.3261 0.06075 0.05499 -0.0197 0.0140 1.0000
15.500 1.3170 0.06523 0.05958 -0.0207 0.0136 1.0000
15.750 1.3149 0.06888 0.06334 -0.0216 0.0132 1.0000
16.000 1.3099 0.07302 0.06759 -0.0227 0.0129 1.0000
16.250 1.3068 0.07698 0.07165 -0.0239 0.0123 1.0000
16.500 1.3017 0.08133 0.07609 -0.0253 0.0118 1.0000
16.750 1.2957 0.08587 0.08073 -0.0268 0.0117 1.0000
17.000 1.2893 0.09060 0.08555 -0.0285 0.0114 1.0000
17.250 1.2813 0.09567 0.09071 -0.0305 0.0111 1.0000
17.500 1.2725 0.10091 0.09604 -0.0325 0.0108 1.0000
17.750 1.2640 0.10619 0.10141 -0.0347 0.0106 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S2027 (s2027-il)