MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 100,000 Max Cl/Cd: 47.15 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh61-il-100000-n5.txt Download as CSV file: xf-mh61-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
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 -0.5795 0.08827 0.08405 0.0013 1.0000 0.0143
-9.000 -0.5835 0.08206 0.07791 -0.0030 1.0000 0.0140
-8.750 -0.5902 0.07439 0.07028 -0.0092 1.0000 0.0137
-8.500 -0.6021 0.06643 0.06230 -0.0172 1.0000 0.0134
-8.250 -0.6154 0.06094 0.05668 -0.0205 1.0000 0.0132
-8.000 -0.6223 0.05564 0.05117 -0.0228 1.0000 0.0130
-7.750 -0.6235 0.05065 0.04588 -0.0242 1.0000 0.0128
-7.500 -0.6195 0.04590 0.04074 -0.0250 1.0000 0.0125
-7.250 -0.6103 0.04159 0.03599 -0.0252 1.0000 0.0123
-7.000 -0.5972 0.03775 0.03166 -0.0251 1.0000 0.0122
-6.750 -0.5774 0.03422 0.02760 -0.0255 0.9760 0.0121
-6.500 -0.5512 0.03108 0.02391 -0.0263 0.9567 0.0123
-6.000 -0.5018 0.02666 0.01863 -0.0257 0.9295 0.0131
-5.750 -0.4784 0.02531 0.01699 -0.0249 0.9177 0.0152
-5.500 -0.4552 0.02410 0.01552 -0.0239 0.9069 0.0166
-5.250 -0.4343 0.02248 0.01374 -0.0225 0.8970 0.0181
-5.000 -0.4148 0.02114 0.01225 -0.0209 0.8878 0.0199
-4.750 -0.3933 0.02012 0.01107 -0.0197 0.8784 0.0224
-4.500 -0.3713 0.01923 0.00998 -0.0184 0.8697 0.0286
-4.250 -0.3505 0.01812 0.00882 -0.0169 0.8619 0.0436
-4.000 -0.3328 0.01623 0.00784 -0.0157 0.8532 0.1857
-3.750 -0.3133 0.01535 0.00750 -0.0145 0.8458 0.3240
-3.500 -0.2913 0.01489 0.00728 -0.0133 0.8377 0.4075
-3.250 -0.2680 0.01457 0.00704 -0.0122 0.8304 0.4641
-3.000 -0.2442 0.01430 0.00679 -0.0111 0.8230 0.5118
-2.750 -0.2196 0.01405 0.00658 -0.0102 0.8156 0.5576
-2.500 -0.1952 0.01381 0.00638 -0.0091 0.8087 0.6043
-2.250 -0.1692 0.01359 0.00618 -0.0084 0.8012 0.6545
-2.000 -0.1431 0.01338 0.00603 -0.0075 0.7947 0.7083
-1.750 -0.1137 0.01321 0.00595 -0.0072 0.7871 0.7662
-1.500 -0.0797 0.01309 0.00585 -0.0076 0.7809 0.8244
-1.250 -0.0373 0.01307 0.00576 -0.0100 0.7733 0.8754
-1.000 0.0049 0.01307 0.00564 -0.0123 0.7669 0.9145
-0.750 0.0486 0.01310 0.00556 -0.0153 0.7586 0.9438
-0.500 0.0887 0.01311 0.00540 -0.0176 0.7517 0.9687
-0.250 0.1317 0.01310 0.00529 -0.0208 0.7429 0.9894
0.000 0.1670 0.01308 0.00516 -0.0225 0.7346 1.0000
0.250 0.1896 0.01309 0.00507 -0.0216 0.7265 1.0000
0.500 0.2138 0.01313 0.00504 -0.0211 0.7170 1.0000
0.750 0.2374 0.01316 0.00500 -0.0203 0.7085 1.0000
1.000 0.2613 0.01320 0.00497 -0.0196 0.6996 1.0000
1.250 0.2860 0.01327 0.00500 -0.0191 0.6897 1.0000
1.500 0.3103 0.01332 0.00502 -0.0184 0.6805 1.0000
1.750 0.3345 0.01337 0.00502 -0.0176 0.6714 1.0000
2.000 0.3596 0.01345 0.00510 -0.0171 0.6605 1.0000
2.250 0.3846 0.01352 0.00517 -0.0165 0.6499 1.0000
2.500 0.4094 0.01359 0.00527 -0.0159 0.6393 1.0000
2.750 0.4342 0.01366 0.00532 -0.0151 0.6287 1.0000
3.000 0.4593 0.01374 0.00543 -0.0145 0.6170 1.0000
3.250 0.4845 0.01385 0.00556 -0.0140 0.6044 1.0000
3.500 0.5097 0.01395 0.00570 -0.0134 0.5914 1.0000
3.750 0.5349 0.01407 0.00589 -0.0128 0.5778 1.0000
4.000 0.5600 0.01419 0.00605 -0.0122 0.5636 1.0000
4.250 0.5850 0.01433 0.00622 -0.0115 0.5486 1.0000
4.500 0.6102 0.01449 0.00645 -0.0110 0.5315 1.0000
4.750 0.6352 0.01467 0.00674 -0.0104 0.5131 1.0000
5.000 0.6598 0.01486 0.00694 -0.0097 0.4938 1.0000
5.250 0.6845 0.01510 0.00724 -0.0091 0.4712 1.0000
5.500 0.7089 0.01537 0.00755 -0.0085 0.4474 1.0000
5.750 0.7329 0.01569 0.00789 -0.0078 0.4211 1.0000
6.000 0.7565 0.01607 0.00829 -0.0071 0.3920 1.0000
6.250 0.7794 0.01653 0.00874 -0.0065 0.3595 1.0000
6.500 0.8016 0.01709 0.00934 -0.0058 0.3217 1.0000
6.750 0.8224 0.01780 0.00995 -0.0051 0.2773 1.0000
7.000 0.8416 0.01871 0.01069 -0.0043 0.2238 1.0000
7.250 0.8588 0.01988 0.01161 -0.0034 0.1673 1.0000
7.500 0.8739 0.02131 0.01274 -0.0025 0.1159 1.0000
7.750 0.8878 0.02284 0.01406 -0.0013 0.0787 1.0000
8.000 0.9008 0.02440 0.01550 0.0000 0.0547 1.0000
8.250 0.9122 0.02603 0.01713 0.0016 0.0418 1.0000
8.500 0.9233 0.02760 0.01878 0.0032 0.0327 1.0000
8.750 0.9310 0.02938 0.02063 0.0050 0.0271 1.0000
9.000 0.9391 0.03112 0.02252 0.0069 0.0233 1.0000
9.250 0.9444 0.03291 0.02437 0.0087 0.0202 1.0000
9.500 0.9489 0.03478 0.02645 0.0107 0.0181 1.0000
9.750 0.9557 0.03675 0.02862 0.0125 0.0162 1.0000
10.000 0.9632 0.03894 0.03099 0.0142 0.0151 1.0000
10.250 0.9700 0.04125 0.03348 0.0155 0.0142 1.0000
10.500 0.9752 0.04361 0.03602 0.0167 0.0135 1.0000
10.750 0.9770 0.04612 0.03869 0.0175 0.0127 1.0000
11.000 0.9732 0.04931 0.04201 0.0181 0.0117 1.0000
11.250 0.9680 0.05322 0.04615 0.0185 0.0113 1.0000
11.500 0.9643 0.05639 0.04958 0.0184 0.0110 1.0000
11.750 0.9577 0.06018 0.05362 0.0179 0.0109 1.0000
12.000 0.9488 0.06435 0.05805 0.0167 0.0107 1.0000
12.250 0.9375 0.06905 0.06299 0.0149 0.0104 1.0000
12.500 0.9244 0.07436 0.06852 0.0124 0.0102 1.0000
12.750 0.9091 0.08042 0.07478 0.0092 0.0102 1.0000
13.000 0.8934 0.08700 0.08154 0.0053 0.0102 1.0000
13.250 0.8775 0.09411 0.08878 0.0012 0.0106 1.0000
13.500 0.8605 0.10210 0.09690 -0.0037 0.0108 1.0000
13.750 0.8441 0.11050 0.10538 -0.0085 0.0112 1.0000
14.000 0.8276 0.11967 0.11462 -0.0139 0.0113 1.0000
14.250 0.6591 0.13003 0.12550 -0.0145 0.0162 1.0000
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Polar data table (+)
Polar graphs
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