MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 500,000 Max Cl/Cd: 76.2 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh43-il-500000-n5.txt Download as CSV file: xf-mh43-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 43 8.5%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5415 0.07918 0.07710 -0.0076 1.0000 0.0053
-8.250 -0.5465 0.07430 0.07226 -0.0107 1.0000 0.0052
-8.000 -0.5567 0.06899 0.06700 -0.0151 1.0000 0.0052
-7.750 -0.5622 0.06128 0.05925 -0.0228 1.0000 0.0051
-7.500 -0.5631 0.05346 0.05131 -0.0280 1.0000 0.0049
-7.250 -0.5622 0.04540 0.04301 -0.0311 1.0000 0.0047
-7.000 -0.5587 0.03765 0.03488 -0.0324 1.0000 0.0044
-6.750 -0.5468 0.02815 0.02458 -0.0341 0.9589 0.0039
-6.500 -0.5289 0.02235 0.01795 -0.0337 0.9267 0.0036
-6.250 -0.5092 0.01990 0.01502 -0.0323 0.9031 0.0035
-6.000 -0.4877 0.01814 0.01289 -0.0312 0.8849 0.0034
-5.750 -0.4647 0.01670 0.01114 -0.0302 0.8692 0.0034
-5.500 -0.4408 0.01550 0.00968 -0.0294 0.8555 0.0033
-5.250 -0.4164 0.01441 0.00837 -0.0287 0.8430 0.0033
-5.000 -0.3916 0.01345 0.00722 -0.0281 0.8314 0.0034
-4.750 -0.3664 0.01259 0.00618 -0.0275 0.8201 0.0034
-4.500 -0.3406 0.01189 0.00533 -0.0270 0.8093 0.0035
-4.250 -0.3144 0.01129 0.00455 -0.0266 0.7991 0.0036
-4.000 -0.2879 0.01082 0.00394 -0.0263 0.7893 0.0038
-3.750 -0.2610 0.01044 0.00343 -0.0259 0.7794 0.0042
-3.500 -0.2338 0.01013 0.00300 -0.0257 0.7696 0.0048
-3.250 -0.2065 0.00983 0.00262 -0.0254 0.7604 0.0079
-3.000 -0.1797 0.00945 0.00231 -0.0252 0.7512 0.0313
-2.750 -0.1536 0.00889 0.00204 -0.0251 0.7419 0.0988
-2.500 -0.1270 0.00852 0.00184 -0.0250 0.7328 0.1592
-2.250 -0.0998 0.00831 0.00169 -0.0249 0.7239 0.1944
-2.000 -0.0726 0.00806 0.00156 -0.0248 0.7146 0.2418
-1.750 -0.0459 0.00773 0.00144 -0.0248 0.7056 0.3136
-1.500 -0.0190 0.00749 0.00134 -0.0246 0.6967 0.3747
-1.250 0.0079 0.00723 0.00125 -0.0245 0.6873 0.4424
-1.000 0.0347 0.00700 0.00118 -0.0243 0.6780 0.5077
-0.750 0.0612 0.00679 0.00113 -0.0241 0.6686 0.5721
-0.500 0.0876 0.00660 0.00110 -0.0237 0.6586 0.6356
-0.250 0.1138 0.00642 0.00108 -0.0233 0.6483 0.6970
0.000 0.1397 0.00627 0.00108 -0.0227 0.6379 0.7540
0.250 0.1652 0.00615 0.00108 -0.0220 0.6272 0.8064
0.500 0.1905 0.00606 0.00110 -0.0212 0.6163 0.8568
0.750 0.2173 0.00599 0.00112 -0.0206 0.6050 0.9082
1.000 0.2534 0.00600 0.00114 -0.0222 0.5925 0.9513
1.250 0.2935 0.00605 0.00114 -0.0248 0.5788 0.9783
1.500 0.3322 0.00612 0.00115 -0.0272 0.5641 0.9957
1.750 0.3622 0.00621 0.00118 -0.0277 0.5494 1.0000
2.000 0.3883 0.00631 0.00122 -0.0273 0.5340 1.0000
2.250 0.4145 0.00642 0.00127 -0.0270 0.5172 1.0000
2.500 0.4407 0.00655 0.00133 -0.0267 0.4983 1.0000
2.750 0.4670 0.00670 0.00143 -0.0264 0.4780 1.0000
3.000 0.4932 0.00687 0.00152 -0.0261 0.4553 1.0000
3.250 0.5195 0.00706 0.00163 -0.0258 0.4300 1.0000
3.500 0.5457 0.00728 0.00176 -0.0256 0.4027 1.0000
3.750 0.5716 0.00755 0.00194 -0.0253 0.3703 1.0000
4.000 0.5976 0.00785 0.00212 -0.0251 0.3369 1.0000
4.250 0.6233 0.00818 0.00233 -0.0249 0.3025 1.0000
4.500 0.6489 0.00855 0.00257 -0.0246 0.2671 1.0000
4.750 0.6744 0.00895 0.00283 -0.0244 0.2310 1.0000
5.000 0.6999 0.00935 0.00312 -0.0242 0.1991 1.0000
5.250 0.7250 0.00979 0.00347 -0.0239 0.1646 1.0000
5.500 0.7499 0.01028 0.00382 -0.0237 0.1320 1.0000
5.750 0.7745 0.01081 0.00420 -0.0234 0.0986 1.0000
6.000 0.7992 0.01131 0.00460 -0.0231 0.0746 1.0000
6.250 0.8242 0.01176 0.00500 -0.0228 0.0585 1.0000
6.500 0.8487 0.01228 0.00545 -0.0225 0.0423 1.0000
6.750 0.8728 0.01283 0.00594 -0.0221 0.0271 1.0000
7.000 0.8967 0.01340 0.00646 -0.0217 0.0169 1.0000
7.250 0.9207 0.01394 0.00704 -0.0213 0.0110 1.0000
7.500 0.9443 0.01453 0.00763 -0.0209 0.0069 1.0000
7.750 0.9677 0.01514 0.00829 -0.0204 0.0042 1.0000
8.000 0.9901 0.01592 0.00916 -0.0197 0.0029 1.0000
8.250 1.0124 0.01665 0.01001 -0.0190 0.0025 1.0000
8.500 1.0340 0.01745 0.01092 -0.0183 0.0022 1.0000
8.750 1.0550 0.01829 0.01189 -0.0176 0.0021 1.0000
9.000 1.0748 0.01925 0.01298 -0.0167 0.0020 1.0000
9.250 1.0935 0.02030 0.01417 -0.0157 0.0019 1.0000
9.500 1.1110 0.02144 0.01545 -0.0146 0.0018 1.0000
9.750 1.1267 0.02272 0.01693 -0.0133 0.0018 1.0000
10.000 1.1407 0.02411 0.01847 -0.0119 0.0017 1.0000
10.250 1.1526 0.02563 0.02017 -0.0103 0.0017 1.0000
10.500 1.1622 0.02725 0.02197 -0.0086 0.0017 1.0000
10.750 1.1689 0.02890 0.02380 -0.0066 0.0017 1.0000
11.000 1.1664 0.03092 0.02602 -0.0036 0.0016 1.0000
11.250 1.1662 0.03281 0.02808 -0.0014 0.0016 1.0000
11.500 1.1641 0.03507 0.03053 0.0002 0.0016 1.0000
11.750 1.1592 0.03784 0.03349 0.0012 0.0016 1.0000
12.000 1.1545 0.04079 0.03664 0.0016 0.0016 1.0000
12.250 1.1455 0.04453 0.04058 0.0015 0.0016 1.0000
12.500 1.1365 0.04855 0.04479 0.0006 0.0016 1.0000
12.750 1.1250 0.05325 0.04969 -0.0010 0.0016 1.0000
13.000 1.1151 0.05809 0.05470 -0.0032 0.0016 1.0000
13.250 1.0973 0.06464 0.06145 -0.0066 0.0016 1.0000
13.500 1.0847 0.07079 0.06776 -0.0101 0.0016 1.0000
13.750 1.0671 0.07841 0.07555 -0.0147 0.0017 1.0000
14.000 1.0477 0.08704 0.08434 -0.0200 0.0017 1.0000
14.250 1.0285 0.09636 0.09382 -0.0256 0.0017 1.0000
14.500 1.0081 0.10650 0.10408 -0.0315 0.0017 1.0000
14.750 0.9818 0.11877 0.11650 -0.0382 0.0018 1.0000
15.000 0.9536 0.13228 0.13012 -0.0453 0.0018 1.0000
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Polar data table (+)
Polar graphs
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