MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 100,000 Max Cl/Cd: 53.35 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh18-il-100000-n5.txt Download as CSV file: xf-mh18-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4055 0.08579 0.08157 -0.0370 1.0000 0.0178
-9.000 -0.4051 0.08121 0.07705 -0.0404 1.0000 0.0175
-8.750 -0.3993 0.07574 0.07158 -0.0466 0.9597 0.0173
-8.500 -0.4001 0.06895 0.06477 -0.0544 0.9388 0.0171
-8.250 -0.4071 0.06380 0.05952 -0.0576 0.9208 0.0169
-8.000 -0.4166 0.05919 0.05476 -0.0585 0.9066 0.0167
-7.750 -0.4225 0.05495 0.05033 -0.0587 0.8948 0.0165
-7.500 -0.4264 0.05078 0.04590 -0.0581 0.8848 0.0163
-7.250 -0.4275 0.04676 0.04154 -0.0569 0.8763 0.0162
-7.000 -0.4242 0.04288 0.03727 -0.0557 0.8679 0.0161
-6.750 -0.4187 0.03931 0.03323 -0.0537 0.8613 0.0160
-6.500 -0.4084 0.03591 0.02931 -0.0520 0.8537 0.0161
-6.250 -0.3956 0.03299 0.02587 -0.0499 0.8482 0.0163
-6.000 -0.3781 0.03038 0.02268 -0.0485 0.8419 0.0166
-5.750 -0.3587 0.02819 0.02003 -0.0469 0.8368 0.0171
-5.500 -0.3374 0.02634 0.01780 -0.0457 0.8319 0.0182
-5.250 -0.3161 0.02496 0.01629 -0.0450 0.8262 0.0207
-5.000 -0.2933 0.02381 0.01491 -0.0439 0.8219 0.0238
-4.750 -0.2697 0.02250 0.01334 -0.0428 0.8172 0.0266
-4.500 -0.2480 0.02132 0.01213 -0.0418 0.8121 0.0324
-4.250 -0.2260 0.02037 0.01107 -0.0406 0.8080 0.0435
-4.000 -0.2030 0.01957 0.01024 -0.0397 0.8033 0.0641
-3.750 -0.1803 0.01883 0.00957 -0.0389 0.7985 0.0950
-3.500 -0.1573 0.01821 0.00905 -0.0380 0.7947 0.1351
-3.250 -0.1340 0.01768 0.00868 -0.0373 0.7904 0.1895
-3.000 -0.1106 0.01718 0.00839 -0.0368 0.7855 0.2557
-2.750 -0.0878 0.01660 0.00810 -0.0360 0.7817 0.3433
-2.500 -0.0655 0.01589 0.00786 -0.0349 0.7783 0.4759
-2.250 -0.0377 0.01510 0.00782 -0.0346 0.7735 0.6798
-2.000 0.0566 0.01487 0.00783 -0.0462 0.7722 0.8840
-1.750 0.1011 0.01506 0.00781 -0.0489 0.7688 0.9296
-1.500 0.1435 0.01520 0.00770 -0.0515 0.7658 0.9596
-1.250 0.1902 0.01533 0.00765 -0.0555 0.7613 0.9822
-1.000 0.2452 0.01521 0.00734 -0.0613 0.7572 0.9994
-0.750 0.2685 0.01519 0.00716 -0.0606 0.7529 1.0000
-0.500 0.2919 0.01526 0.00714 -0.0602 0.7473 1.0000
-0.250 0.3149 0.01531 0.00709 -0.0595 0.7419 1.0000
0.000 0.3374 0.01531 0.00695 -0.0585 0.7378 1.0000
0.250 0.3613 0.01546 0.00707 -0.0582 0.7311 1.0000
0.500 0.3843 0.01549 0.00702 -0.0573 0.7262 1.0000
0.750 0.4077 0.01559 0.00707 -0.0566 0.7205 1.0000
1.000 0.4312 0.01569 0.00712 -0.0560 0.7144 1.0000
1.250 0.4544 0.01568 0.00705 -0.0549 0.7100 1.0000
1.500 0.4781 0.01588 0.00726 -0.0545 0.7025 1.0000
1.750 0.5016 0.01589 0.00722 -0.0536 0.6975 1.0000
2.000 0.5252 0.01607 0.00741 -0.0530 0.6902 1.0000
2.250 0.5489 0.01610 0.00744 -0.0521 0.6845 1.0000
2.500 0.5724 0.01625 0.00762 -0.0515 0.6772 1.0000
2.750 0.5962 0.01628 0.00764 -0.0506 0.6709 1.0000
3.000 0.6196 0.01643 0.00784 -0.0499 0.6630 1.0000
3.250 0.6436 0.01643 0.00788 -0.0490 0.6565 1.0000
3.500 0.6668 0.01659 0.00812 -0.0482 0.6476 1.0000
3.750 0.6910 0.01658 0.00811 -0.0473 0.6407 1.0000
4.000 0.7141 0.01672 0.00834 -0.0465 0.6309 1.0000
4.250 0.7373 0.01683 0.00857 -0.0457 0.6213 1.0000
4.500 0.7612 0.01684 0.00864 -0.0447 0.6122 1.0000
4.750 0.7845 0.01691 0.00879 -0.0438 0.6015 1.0000
5.000 0.8072 0.01702 0.00902 -0.0429 0.5891 1.0000
5.250 0.8299 0.01712 0.00922 -0.0419 0.5760 1.0000
5.500 0.8526 0.01720 0.00944 -0.0408 0.5616 1.0000
5.750 0.8752 0.01726 0.00959 -0.0397 0.5460 1.0000
6.000 0.8966 0.01743 0.00986 -0.0386 0.5268 1.0000
6.250 0.9183 0.01754 0.01003 -0.0373 0.5070 1.0000
6.500 0.9390 0.01773 0.01027 -0.0359 0.4847 1.0000
6.750 0.9592 0.01798 0.01051 -0.0345 0.4608 1.0000
7.000 0.9778 0.01834 0.01086 -0.0328 0.4348 1.0000
7.250 0.9949 0.01883 0.01138 -0.0310 0.4068 1.0000
7.500 1.0098 0.01944 0.01194 -0.0290 0.3761 1.0000
7.750 1.0221 0.02017 0.01259 -0.0267 0.3425 1.0000
8.000 1.0314 0.02102 0.01333 -0.0242 0.3055 1.0000
8.250 1.0372 0.02203 0.01418 -0.0212 0.2649 1.0000
8.500 1.0398 0.02317 0.01513 -0.0179 0.2234 1.0000
8.750 1.0391 0.02446 0.01621 -0.0143 0.1836 1.0000
9.000 1.0360 0.02580 0.01736 -0.0106 0.1502 1.0000
9.250 1.0340 0.02734 0.01872 -0.0074 0.1166 1.0000
9.500 1.0306 0.02920 0.02034 -0.0045 0.0849 1.0000
9.750 1.0283 0.03116 0.02212 -0.0019 0.0613 1.0000
10.000 1.0257 0.03328 0.02415 0.0005 0.0472 1.0000
10.250 1.0246 0.03537 0.02624 0.0025 0.0382 1.0000
10.500 1.0246 0.03747 0.02850 0.0044 0.0311 1.0000
10.750 1.0199 0.04006 0.03108 0.0061 0.0265 1.0000
11.000 1.0233 0.04200 0.03321 0.0074 0.0231 1.0000
11.250 1.0227 0.04440 0.03573 0.0087 0.0204 1.0000
11.500 1.0194 0.04713 0.03854 0.0098 0.0187 1.0000
11.750 1.0173 0.04988 0.04139 0.0110 0.0171 1.0000
12.000 1.0210 0.05212 0.04381 0.0119 0.0156 1.0000
12.250 1.0228 0.05460 0.04644 0.0125 0.0138 1.0000
12.500 1.0230 0.05730 0.04925 0.0130 0.0127 1.0000
12.750 1.0236 0.06006 0.05213 0.0136 0.0122 1.0000
13.000 1.0218 0.06326 0.05545 0.0141 0.0116 1.0000
13.250 1.0208 0.06674 0.05906 0.0148 0.0110 1.0000
13.500 1.0207 0.07003 0.06258 0.0150 0.0108 1.0000
13.750 1.0179 0.07377 0.06656 0.0148 0.0107 1.0000
14.000 1.0118 0.07810 0.07114 0.0143 0.0105 1.0000
14.250 1.0039 0.08275 0.07603 0.0132 0.0103 1.0000
14.500 0.9946 0.08777 0.08127 0.0116 0.0103 1.0000
14.750 0.9814 0.09372 0.08746 0.0094 0.0102 1.0000
15.000 0.9685 0.09987 0.09382 0.0067 0.0102 1.0000
15.250 0.9556 0.10631 0.10044 0.0035 0.0103 1.0000
15.500 0.9395 0.11385 0.10818 -0.0005 0.0103 1.0000
15.750 0.9255 0.12129 0.11576 -0.0046 0.0104 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 18 11.16% (mh18-il)