S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4094-il-1000000-n5.txt Download as CSV file: xf-s4094-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4094 (root airfoil designed for and used on the
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6430 0.13110 0.12952 0.0335 1.0004 0.0063
-10.750 -0.6436 0.12572 0.12415 0.0312 1.0004 0.0064
-10.250 -0.9063 0.03910 0.03673 -0.0243 1.0004 0.0073
-10.000 -0.8923 0.03420 0.03142 -0.0264 1.0004 0.0074
-9.750 -0.8717 0.03125 0.02816 -0.0276 1.0004 0.0074
-9.500 -0.8486 0.02891 0.02555 -0.0285 1.0004 0.0075
-9.250 -0.8238 0.02705 0.02345 -0.0292 1.0004 0.0075
-9.000 -0.7992 0.02449 0.02058 -0.0302 1.0004 0.0076
-8.750 -0.7736 0.02196 0.01772 -0.0311 1.0004 0.0078
-8.500 -0.7461 0.02056 0.01615 -0.0317 1.0004 0.0079
-8.250 -0.7181 0.01953 0.01499 -0.0322 1.0004 0.0081
-8.000 -0.6897 0.01869 0.01403 -0.0327 1.0004 0.0082
-7.750 -0.6610 0.01793 0.01318 -0.0332 1.0004 0.0083
-7.500 -0.6322 0.01732 0.01251 -0.0337 1.0004 0.0085
-7.250 -0.6032 0.01673 0.01185 -0.0341 1.0004 0.0087
-7.000 -0.5740 0.01611 0.01116 -0.0346 1.0004 0.0090
-6.750 -0.5447 0.01543 0.01039 -0.0350 1.0004 0.0092
-6.500 -0.5153 0.01479 0.00967 -0.0355 1.0004 0.0094
-6.250 -0.4850 0.01431 0.00912 -0.0361 0.9695 0.0097
-6.000 -0.4611 0.01411 0.00874 -0.0350 0.9098 0.0099
-5.750 -0.4348 0.01384 0.00828 -0.0345 0.8699 0.0101
-5.500 -0.4066 0.01355 0.00781 -0.0345 0.8374 0.0103
-5.250 -0.3779 0.01328 0.00739 -0.0347 0.8084 0.0105
-5.000 -0.3487 0.01302 0.00699 -0.0349 0.7827 0.0106
-4.750 -0.3194 0.01277 0.00662 -0.0352 0.7599 0.0108
-4.500 -0.2898 0.01246 0.00618 -0.0356 0.7386 0.0109
-4.250 -0.2600 0.01207 0.00567 -0.0360 0.7193 0.0113
-4.000 -0.2303 0.01179 0.00529 -0.0364 0.7014 0.0117
-3.750 -0.2006 0.01158 0.00500 -0.0368 0.6849 0.0122
-3.500 -0.1709 0.01142 0.00477 -0.0372 0.6690 0.0128
-3.250 -0.1411 0.01127 0.00455 -0.0375 0.6541 0.0135
-3.000 -0.1114 0.01113 0.00434 -0.0379 0.6403 0.0140
-2.750 -0.0816 0.01103 0.00417 -0.0383 0.6270 0.0146
-2.500 -0.0519 0.01093 0.00401 -0.0386 0.6141 0.0152
-2.250 -0.0221 0.01083 0.00385 -0.0390 0.6017 0.0168
-2.000 0.0076 0.01073 0.00372 -0.0393 0.5897 0.0196
-1.750 0.0375 0.01054 0.00359 -0.0398 0.5780 0.0439
-1.500 0.0674 0.01038 0.00350 -0.0403 0.5669 0.0718
-1.250 0.0972 0.01023 0.00343 -0.0407 0.5559 0.1054
-1.000 0.1270 0.01010 0.00337 -0.0412 0.5441 0.1425
-0.750 0.1569 0.00994 0.00333 -0.0417 0.5326 0.1890
-0.500 0.1867 0.00982 0.00330 -0.0422 0.5208 0.2340
-0.250 0.2166 0.00969 0.00328 -0.0427 0.5083 0.2866
0.000 0.2465 0.00943 0.00329 -0.0434 0.4950 0.3906
0.250 0.2764 0.00921 0.00331 -0.0440 0.4806 0.4893
0.500 0.3061 0.00907 0.00334 -0.0446 0.4659 0.5675
0.750 0.3358 0.00891 0.00338 -0.0451 0.4508 0.6523
1.000 0.3648 0.00867 0.00346 -0.0454 0.4341 0.7733
1.250 0.3885 0.00834 0.00349 -0.0442 0.4188 0.9112
1.500 0.4150 0.00802 0.00319 -0.0437 0.4033 0.9996
1.750 0.4447 0.00816 0.00323 -0.0441 0.3873 0.9996
2.000 0.4743 0.00831 0.00329 -0.0445 0.3705 0.9996
2.250 0.5039 0.00845 0.00336 -0.0449 0.3549 0.9996
2.500 0.5334 0.00860 0.00343 -0.0453 0.3398 0.9996
3.000 0.5924 0.00893 0.00360 -0.0461 0.3095 0.9996
3.250 0.6218 0.00910 0.00370 -0.0465 0.2942 0.9996
3.500 0.6512 0.00927 0.00381 -0.0469 0.2805 0.9996
3.750 0.6805 0.00946 0.00393 -0.0473 0.2658 0.9996
4.000 0.7098 0.00965 0.00405 -0.0477 0.2517 0.9996
4.250 0.7390 0.00985 0.00420 -0.0481 0.2371 0.9996
4.500 0.7682 0.01006 0.00434 -0.0485 0.2236 0.9996
4.750 0.7973 0.01028 0.00450 -0.0489 0.2094 0.9996
5.000 0.8264 0.01049 0.00466 -0.0493 0.1973 0.9996
5.250 0.8555 0.01070 0.00484 -0.0496 0.1862 0.9996
5.500 0.8844 0.01094 0.00503 -0.0500 0.1734 0.9996
5.750 0.9133 0.01117 0.00523 -0.0504 0.1629 0.9996
6.000 0.9420 0.01144 0.00544 -0.0508 0.1512 0.9996
6.250 0.9707 0.01173 0.00568 -0.0511 0.1385 0.9996
6.500 0.9991 0.01207 0.00594 -0.0515 0.1224 0.9996
6.750 1.0275 0.01241 0.00622 -0.0519 0.1085 0.9996
7.000 1.0558 0.01275 0.00650 -0.0522 0.0971 0.9996
7.250 1.0840 0.01311 0.00682 -0.0525 0.0859 0.9996
7.500 1.1120 0.01349 0.00714 -0.0529 0.0757 0.9996
7.750 1.1399 0.01387 0.00749 -0.0532 0.0660 0.9996
8.000 1.1677 0.01428 0.00785 -0.0535 0.0562 0.9996
8.250 1.1953 0.01470 0.00824 -0.0537 0.0479 0.9996
8.500 1.2225 0.01517 0.00867 -0.0540 0.0394 0.9996
8.750 1.2496 0.01566 0.00912 -0.0542 0.0320 0.9996
9.000 1.2764 0.01617 0.00960 -0.0544 0.0256 0.9996
9.250 1.3028 0.01674 0.01015 -0.0546 0.0193 0.9996
9.500 1.3280 0.01760 0.01093 -0.0547 0.0084 0.9996
9.750 1.3536 0.01825 0.01159 -0.0547 0.0058 0.9996
10.000 1.3795 0.01877 0.01216 -0.0547 0.0050 0.9996
10.250 1.4049 0.01935 0.01278 -0.0547 0.0045 0.9996
10.500 1.4299 0.01997 0.01346 -0.0547 0.0040 0.9996
10.750 1.4543 0.02064 0.01420 -0.0545 0.0037 0.9996
11.000 1.4787 0.02123 0.01485 -0.0544 0.0036 0.9996
11.250 1.5025 0.02187 0.01555 -0.0542 0.0035 0.9996
11.500 1.5257 0.02255 0.01630 -0.0539 0.0033 0.9996
11.750 1.5480 0.02328 0.01710 -0.0535 0.0032 0.9996
12.000 1.5695 0.02406 0.01798 -0.0530 0.0031 0.9996
12.250 1.5900 0.02490 0.01889 -0.0524 0.0030 0.9996
12.500 1.6094 0.02579 0.01986 -0.0517 0.0029 0.9996
12.750 1.6273 0.02675 0.02091 -0.0507 0.0028 0.9996
13.000 1.6435 0.02780 0.02205 -0.0496 0.0027 0.9996
13.250 1.6573 0.02897 0.02331 -0.0482 0.0026 0.9996
13.500 1.6681 0.03028 0.02472 -0.0465 0.0026 0.9996
13.750 1.6749 0.03178 0.02633 -0.0443 0.0025 0.9996
14.000 1.6711 0.03365 0.02833 -0.0408 0.0024 0.9996
14.250 1.6639 0.03613 0.03094 -0.0380 0.0024 0.9996
14.500 1.6580 0.03921 0.03417 -0.0368 0.0024 0.9996
14.750 1.6511 0.04300 0.03811 -0.0368 0.0023 0.9996
15.000 1.6415 0.04756 0.04283 -0.0376 0.0023 0.9996
15.250 1.6303 0.05269 0.04811 -0.0390 0.0023 0.9996
15.500 1.6157 0.05853 0.05411 -0.0410 0.0022 0.9996
15.750 1.5995 0.06470 0.06043 -0.0431 0.0022 0.9996
16.000 1.5823 0.07116 0.06704 -0.0455 0.0022 0.9996
16.250 1.5610 0.07840 0.07444 -0.0482 0.0022 0.9996
16.500 1.5368 0.08627 0.08246 -0.0513 0.0022 0.9996
16.750 1.5107 0.09473 0.09107 -0.0547 0.0022 0.9996
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Polar data table (+)
Polar graphs
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