MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 100,000 Max Cl/Cd: 50.66 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh20-il-100000.txt Download as CSV file: xf-mh20-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4164 0.10286 0.09874 -0.0010 1.0000 0.0838
-9.000 -0.5039 0.10432 0.09997 0.0002 1.0000 0.0787
-8.750 -0.4967 0.10074 0.09634 -0.0006 1.0000 0.0815
-8.500 -0.4346 0.08992 0.08599 -0.0102 1.0000 0.0899
-8.250 -0.4170 0.08574 0.08180 -0.0084 1.0000 0.0930
-8.000 -0.4148 0.08166 0.07776 -0.0099 1.0000 0.0964
-7.750 -0.4256 0.07740 0.07359 -0.0142 1.0000 0.1003
-7.500 -0.4545 0.07298 0.06923 -0.0228 1.0000 0.1017
-7.250 -0.4452 0.06747 0.06379 -0.0223 1.0000 0.1037
-7.000 -0.4316 0.06359 0.05994 -0.0212 1.0000 0.1070
-6.750 -0.4904 0.06840 0.06435 -0.0237 1.0000 0.1057
-6.500 -0.4843 0.06473 0.06057 -0.0272 1.0000 0.1141
-6.250 -0.4759 0.06022 0.05604 -0.0284 1.0000 0.1180
-5.000 -0.4645 0.03660 0.03065 -0.0207 0.9964 0.0440
-4.750 -0.4286 0.03232 0.02520 -0.0215 0.9883 0.0372
-4.500 -0.3936 0.02839 0.02074 -0.0233 0.9820 0.0362
-4.250 -0.3591 0.02568 0.01749 -0.0245 0.9748 0.0365
-4.000 -0.3210 0.02291 0.01448 -0.0267 0.9694 0.0412
-3.750 -0.2843 0.02147 0.01274 -0.0280 0.9625 0.0494
-3.500 -0.2471 0.01921 0.01061 -0.0296 0.9571 0.0687
-3.250 -0.2175 0.01737 0.00941 -0.0302 0.9499 0.1917
-3.000 -0.1864 0.01595 0.00872 -0.0313 0.9434 0.3301
-2.750 -0.0863 0.01376 0.00848 -0.0418 0.9516 0.9210
-2.500 0.0255 0.01368 0.00778 -0.0571 0.9587 1.0000
-2.250 0.0646 0.01363 0.00742 -0.0601 0.9486 1.0000
-2.000 0.1004 0.01362 0.00713 -0.0623 0.9386 1.0000
-1.750 0.1331 0.01366 0.00695 -0.0636 0.9283 1.0000
-1.500 0.1584 0.01378 0.00691 -0.0636 0.9167 1.0000
-1.250 0.1815 0.01394 0.00693 -0.0630 0.9055 1.0000
-1.000 0.2039 0.01412 0.00695 -0.0621 0.8947 1.0000
-0.750 0.2255 0.01431 0.00702 -0.0610 0.8844 1.0000
-0.500 0.2466 0.01449 0.00710 -0.0596 0.8748 1.0000
-0.250 0.2669 0.01473 0.00726 -0.0584 0.8639 1.0000
0.000 0.2875 0.01498 0.00744 -0.0571 0.8534 1.0000
0.250 0.3081 0.01521 0.00761 -0.0556 0.8436 1.0000
0.500 0.3283 0.01539 0.00772 -0.0538 0.8346 1.0000
0.750 0.3492 0.01565 0.00794 -0.0525 0.8235 1.0000
1.000 0.3701 0.01590 0.00816 -0.0511 0.8129 1.0000
1.250 0.3910 0.01613 0.00836 -0.0496 0.8025 1.0000
1.500 0.4117 0.01629 0.00851 -0.0478 0.7929 1.0000
1.750 0.4327 0.01647 0.00868 -0.0462 0.7821 1.0000
2.000 0.4541 0.01669 0.00890 -0.0447 0.7704 1.0000
2.250 0.4754 0.01688 0.00910 -0.0432 0.7587 1.0000
2.500 0.4969 0.01704 0.00927 -0.0416 0.7469 1.0000
2.750 0.5185 0.01717 0.00942 -0.0399 0.7351 1.0000
3.000 0.5402 0.01726 0.00960 -0.0382 0.7231 1.0000
3.250 0.5622 0.01732 0.00970 -0.0365 0.7108 1.0000
3.500 0.5845 0.01737 0.00979 -0.0348 0.6977 1.0000
3.750 0.6069 0.01741 0.00988 -0.0332 0.6838 1.0000
4.000 0.6294 0.01743 0.01004 -0.0316 0.6689 1.0000
4.250 0.6522 0.01741 0.01009 -0.0300 0.6533 1.0000
4.500 0.6753 0.01733 0.01007 -0.0283 0.6373 1.0000
4.750 0.6987 0.01718 0.00998 -0.0266 0.6210 1.0000
5.000 0.7218 0.01712 0.01003 -0.0251 0.6012 1.0000
5.250 0.7454 0.01694 0.00991 -0.0234 0.5813 1.0000
5.500 0.7687 0.01683 0.00992 -0.0219 0.5578 1.0000
5.750 0.7919 0.01670 0.00997 -0.0204 0.5319 1.0000
6.000 0.8147 0.01660 0.00992 -0.0187 0.5020 1.0000
6.250 0.8363 0.01665 0.00998 -0.0170 0.4645 1.0000
6.500 0.8561 0.01690 0.01012 -0.0152 0.4187 1.0000
6.750 0.8738 0.01742 0.01056 -0.0135 0.3595 1.0000
7.000 0.8879 0.01835 0.01121 -0.0116 0.2765 1.0000
7.250 0.8868 0.02134 0.01302 -0.0085 0.1233 1.0000
7.500 0.8883 0.02433 0.01545 -0.0053 0.0683 1.0000
7.750 0.8948 0.02675 0.01771 -0.0024 0.0512 1.0000
8.000 0.9072 0.02870 0.01966 -0.0003 0.0407 1.0000
8.250 0.9261 0.03178 0.02272 0.0015 0.0364 1.0000
8.500 0.9478 0.03414 0.02533 0.0029 0.0335 1.0000
8.750 0.9636 0.03625 0.02758 0.0043 0.0294 1.0000
9.000 0.9795 0.04064 0.03212 0.0051 0.0270 1.0000
9.250 0.9913 0.04474 0.03660 0.0067 0.0268 1.0000
9.500 1.0002 0.04800 0.04036 0.0085 0.0269 1.0000
9.750 1.0076 0.05039 0.04309 0.0104 0.0273 1.0000
10.000 1.0089 0.05315 0.04625 0.0127 0.0279 1.0000
10.250 1.0020 0.05639 0.04997 0.0153 0.0290 1.0000
10.500 0.9821 0.05971 0.05366 0.0182 0.0297 1.0000
10.750 0.9609 0.06355 0.05780 0.0196 0.0305 1.0000
11.000 0.9410 0.06778 0.06227 0.0194 0.0314 1.0000
11.250 0.9201 0.07261 0.06729 0.0181 0.0318 1.0000
11.500 0.8981 0.07816 0.07301 0.0156 0.0320 1.0000
11.750 0.8770 0.08429 0.07928 0.0120 0.0323 1.0000
12.000 0.8538 0.09175 0.08673 0.0071 0.0326 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 20 9.01% (mh20-il)