MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 200,000 Max Cl/Cd: 60.36 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh61-il-200000-n5.txt Download as CSV file: xf-mh61-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5968 0.08517 0.08223 0.0043 1.0000 0.0083
-9.000 -0.6027 0.07851 0.07561 -0.0003 1.0000 0.0081
-8.750 -0.6123 0.06926 0.06641 -0.0081 1.0000 0.0080
-8.500 -0.6279 0.06099 0.05804 -0.0166 1.0000 0.0078
-8.250 -0.6399 0.05534 0.05221 -0.0197 0.9635 0.0077
-8.000 -0.6472 0.05057 0.04712 -0.0202 0.9206 0.0076
-7.750 -0.6519 0.04633 0.04254 -0.0191 0.9012 0.0074
-7.500 -0.6513 0.04206 0.03786 -0.0178 0.8875 0.0072
-7.250 -0.6455 0.03799 0.03334 -0.0164 0.8764 0.0070
-7.000 -0.6352 0.03417 0.02902 -0.0149 0.8669 0.0068
-6.750 -0.6213 0.03086 0.02518 -0.0133 0.8587 0.0066
-6.500 -0.6038 0.02802 0.02186 -0.0119 0.8508 0.0065
-6.250 -0.5838 0.02565 0.01906 -0.0106 0.8436 0.0065
-6.000 -0.5623 0.02367 0.01668 -0.0095 0.8366 0.0065
-5.750 -0.5395 0.02196 0.01468 -0.0085 0.8300 0.0066
-5.500 -0.5163 0.02050 0.01299 -0.0075 0.8233 0.0067
-5.250 -0.4926 0.01920 0.01151 -0.0066 0.8171 0.0069
-5.000 -0.4689 0.01807 0.01022 -0.0058 0.8105 0.0072
-4.750 -0.4452 0.01710 0.00909 -0.0049 0.8046 0.0076
-4.500 -0.4206 0.01624 0.00807 -0.0042 0.7980 0.0083
-4.250 -0.3959 0.01555 0.00719 -0.0035 0.7924 0.0091
-4.000 -0.3706 0.01480 0.00633 -0.0030 0.7857 0.0131
-3.750 -0.3456 0.01412 0.00551 -0.0023 0.7803 0.0230
-3.500 -0.3232 0.01278 0.00478 -0.0017 0.7737 0.1359
-3.250 -0.3014 0.01179 0.00446 -0.0011 0.7679 0.2836
-3.000 -0.2759 0.01140 0.00423 -0.0007 0.7616 0.3468
-2.750 -0.2508 0.01105 0.00402 -0.0002 0.7555 0.4062
-2.500 -0.2250 0.01078 0.00383 0.0003 0.7495 0.4512
-2.250 -0.1990 0.01054 0.00365 0.0007 0.7429 0.4923
-2.000 -0.1732 0.01032 0.00346 0.0013 0.7371 0.5326
-1.750 -0.1472 0.01010 0.00333 0.0018 0.7301 0.5746
-1.500 -0.1219 0.00988 0.00319 0.0025 0.7243 0.6195
-1.250 -0.0962 0.00965 0.00310 0.0031 0.7169 0.6685
-1.000 -0.0709 0.00943 0.00299 0.0040 0.7109 0.7225
-0.750 -0.0436 0.00922 0.00295 0.0045 0.7033 0.7824
-0.500 -0.0106 0.00908 0.00291 0.0039 0.6969 0.8447
-0.250 0.0341 0.00904 0.00291 0.0007 0.6887 0.8970
0.000 0.0794 0.00905 0.00286 -0.0027 0.6811 0.9315
0.250 0.1202 0.00908 0.00282 -0.0052 0.6729 0.9555
0.500 0.1600 0.00911 0.00279 -0.0077 0.6641 0.9724
0.750 0.1974 0.00914 0.00275 -0.0097 0.6558 0.9875
1.000 0.2370 0.00916 0.00271 -0.0123 0.6461 0.9989
1.250 0.2646 0.00918 0.00269 -0.0123 0.6366 1.0000
1.500 0.2902 0.00921 0.00267 -0.0119 0.6273 1.0000
1.750 0.3160 0.00925 0.00267 -0.0115 0.6173 1.0000
2.000 0.3421 0.00930 0.00269 -0.0112 0.6065 1.0000
2.250 0.3681 0.00936 0.00272 -0.0109 0.5955 1.0000
2.500 0.3942 0.00943 0.00276 -0.0106 0.5841 1.0000
2.750 0.4204 0.00951 0.00285 -0.0103 0.5721 1.0000
3.000 0.4466 0.00961 0.00292 -0.0100 0.5594 1.0000
3.250 0.4728 0.00971 0.00302 -0.0097 0.5458 1.0000
3.500 0.4991 0.00983 0.00313 -0.0094 0.5313 1.0000
3.750 0.5253 0.00997 0.00328 -0.0091 0.5156 1.0000
4.000 0.5515 0.01013 0.00342 -0.0088 0.4984 1.0000
4.250 0.5774 0.01031 0.00358 -0.0085 0.4799 1.0000
4.500 0.6035 0.01051 0.00377 -0.0083 0.4588 1.0000
4.750 0.6293 0.01075 0.00402 -0.0080 0.4366 1.0000
5.000 0.6549 0.01103 0.00426 -0.0077 0.4126 1.0000
5.250 0.6804 0.01134 0.00454 -0.0075 0.3868 1.0000
5.500 0.7055 0.01169 0.00485 -0.0072 0.3592 1.0000
5.750 0.7303 0.01210 0.00520 -0.0069 0.3292 1.0000
6.000 0.7545 0.01257 0.00560 -0.0066 0.2938 1.0000
6.250 0.7779 0.01316 0.00607 -0.0063 0.2519 1.0000
6.500 0.8005 0.01386 0.00666 -0.0059 0.2075 1.0000
6.750 0.8220 0.01468 0.00730 -0.0055 0.1604 1.0000
7.000 0.8420 0.01568 0.00806 -0.0049 0.1135 1.0000
7.500 0.8805 0.01769 0.00977 -0.0035 0.0511 1.0000
7.750 0.8992 0.01868 0.01071 -0.0026 0.0333 1.0000
8.000 0.9169 0.01975 0.01178 -0.0016 0.0227 1.0000
8.250 0.9337 0.02084 0.01292 -0.0005 0.0159 1.0000
8.500 0.9461 0.02234 0.01451 0.0010 0.0115 1.0000
8.750 0.9625 0.02330 0.01558 0.0022 0.0093 1.0000
9.000 0.9771 0.02435 0.01680 0.0034 0.0074 1.0000
9.250 0.9862 0.02586 0.01843 0.0052 0.0066 1.0000
9.500 0.9892 0.02776 0.02048 0.0074 0.0061 1.0000
9.750 0.9914 0.02945 0.02231 0.0099 0.0058 1.0000
10.000 0.9959 0.03114 0.02414 0.0118 0.0055 1.0000
10.250 1.0006 0.03301 0.02617 0.0134 0.0053 1.0000
10.500 1.0052 0.03503 0.02836 0.0147 0.0052 1.0000
10.750 1.0091 0.03726 0.03078 0.0159 0.0051 1.0000
11.000 1.0118 0.03970 0.03341 0.0170 0.0049 1.0000
11.250 1.0127 0.04241 0.03634 0.0178 0.0048 1.0000
11.500 1.0119 0.04533 0.03947 0.0183 0.0047 1.0000
11.750 1.0091 0.04854 0.04290 0.0185 0.0047 1.0000
12.000 1.0034 0.05218 0.04677 0.0183 0.0047 1.0000
12.250 0.9952 0.05626 0.05107 0.0175 0.0046 1.0000
12.500 0.9852 0.06075 0.05579 0.0162 0.0046 1.0000
12.750 0.9731 0.06580 0.06105 0.0142 0.0046 1.0000
13.000 0.9601 0.07127 0.06671 0.0116 0.0046 1.0000
13.250 0.9460 0.07730 0.07293 0.0085 0.0047 1.0000
13.500 0.9302 0.08412 0.07993 0.0046 0.0047 1.0000
13.750 0.9137 0.09166 0.08764 0.0001 0.0047 1.0000
14.000 0.8958 0.10015 0.09629 -0.0050 0.0048 1.0000
14.250 0.8780 0.10921 0.10548 -0.0104 0.0049 1.0000
14.500 0.8586 0.11937 0.11575 -0.0163 0.0050 1.0000
14.750 0.8393 0.13030 0.12676 -0.0221 0.0051 1.0000
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Polar data table (+)
Polar graphs
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