MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.33 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh44-il-1000000-n5.txt Download as CSV file: xf-mh44-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7188 0.07434 0.07281 -0.0098 1.0000 0.0021
-10.750 -0.7173 0.07044 0.06895 -0.0124 1.0000 0.0022
-10.250 -0.7962 0.04367 0.04181 -0.0307 1.0000 0.0019
-10.000 -0.8174 0.03927 0.03719 -0.0291 1.0000 0.0019
-9.750 -0.8613 0.02958 0.02669 -0.0261 1.0000 0.0020
-9.500 -0.8551 0.02647 0.02324 -0.0246 1.0000 0.0021
-9.250 -0.8404 0.02454 0.02109 -0.0236 0.9989 0.0022
-9.000 -0.8143 0.02294 0.01926 -0.0245 0.9556 0.0023
-8.750 -0.7969 0.02165 0.01774 -0.0232 0.9322 0.0023
-8.500 -0.7772 0.02088 0.01681 -0.0220 0.9170 0.0024
-8.250 -0.7588 0.01955 0.01525 -0.0207 0.9048 0.0025
-8.000 -0.7382 0.01850 0.01401 -0.0196 0.8948 0.0025
-7.750 -0.7164 0.01763 0.01297 -0.0186 0.8858 0.0026
-7.500 -0.6941 0.01671 0.01188 -0.0178 0.8774 0.0027
-7.250 -0.6716 0.01579 0.01079 -0.0169 0.8698 0.0028
-7.000 -0.6484 0.01494 0.00977 -0.0161 0.8621 0.0028
-6.750 -0.6244 0.01425 0.00896 -0.0154 0.8550 0.0029
-6.500 -0.6003 0.01356 0.00814 -0.0147 0.8477 0.0030
-6.250 -0.5760 0.01292 0.00738 -0.0140 0.8411 0.0030
-6.000 -0.5512 0.01232 0.00668 -0.0134 0.8339 0.0031
-5.750 -0.5257 0.01188 0.00616 -0.0129 0.8273 0.0032
-5.500 -0.4997 0.01152 0.00572 -0.0125 0.8201 0.0034
-5.250 -0.4739 0.01112 0.00524 -0.0120 0.8135 0.0035
-5.000 -0.4478 0.01075 0.00480 -0.0116 0.8058 0.0036
-4.750 -0.4218 0.01035 0.00433 -0.0112 0.7985 0.0037
-4.500 -0.3960 0.00989 0.00377 -0.0106 0.7900 0.0037
-4.250 -0.3698 0.00950 0.00330 -0.0102 0.7813 0.0039
-4.000 -0.3432 0.00921 0.00292 -0.0098 0.7718 0.0041
-3.750 -0.3164 0.00897 0.00262 -0.0095 0.7608 0.0046
-3.500 -0.2893 0.00877 0.00236 -0.0092 0.7490 0.0054
-3.250 -0.2624 0.00857 0.00212 -0.0089 0.7363 0.0084
-3.000 -0.2357 0.00834 0.00190 -0.0086 0.7226 0.0210
-2.750 -0.2091 0.00811 0.00170 -0.0083 0.7084 0.0410
-2.500 -0.1842 0.00764 0.00146 -0.0078 0.6938 0.1104
-2.250 -0.1588 0.00728 0.00131 -0.0074 0.6786 0.1766
-2.000 -0.1323 0.00709 0.00120 -0.0071 0.6632 0.2166
-1.750 -0.1056 0.00695 0.00111 -0.0069 0.6476 0.2521
-1.250 -0.0523 0.00667 0.00097 -0.0063 0.6159 0.3312
-1.000 -0.0253 0.00659 0.00092 -0.0061 0.5993 0.3601
-0.750 0.0018 0.00653 0.00087 -0.0059 0.5826 0.3897
-0.500 0.0287 0.00647 0.00084 -0.0057 0.5656 0.4203
-0.250 0.0556 0.00642 0.00082 -0.0055 0.5480 0.4532
0.000 0.0823 0.00637 0.00080 -0.0053 0.5302 0.4882
0.250 0.1089 0.00631 0.00080 -0.0050 0.5127 0.5260
0.500 0.1353 0.00626 0.00080 -0.0047 0.4948 0.5660
0.750 0.1614 0.00620 0.00081 -0.0043 0.4775 0.6102
1.000 0.1869 0.00612 0.00083 -0.0038 0.4612 0.6601
1.250 0.2118 0.00602 0.00086 -0.0032 0.4453 0.7160
1.500 0.2356 0.00589 0.00090 -0.0022 0.4294 0.7806
1.750 0.2590 0.00574 0.00095 -0.0011 0.4134 0.8547
2.000 0.3049 0.00570 0.00106 -0.0050 0.3931 0.9348
2.250 0.3648 0.00588 0.00115 -0.0123 0.3680 0.9590
2.500 0.4017 0.00606 0.00126 -0.0143 0.3489 0.9718
2.750 0.4319 0.00624 0.00136 -0.0148 0.3310 0.9822
3.000 0.4643 0.00641 0.00146 -0.0158 0.3113 0.9888
3.250 0.4967 0.00662 0.00158 -0.0169 0.2911 0.9933
3.500 0.5317 0.00680 0.00169 -0.0186 0.2720 0.9962
3.750 0.5669 0.00702 0.00180 -0.0204 0.2488 0.9986
4.000 0.6003 0.00722 0.00193 -0.0217 0.2277 1.0000
4.250 0.6256 0.00742 0.00207 -0.0213 0.2115 1.0000
4.500 0.6507 0.00765 0.00222 -0.0208 0.1940 1.0000
4.750 0.6759 0.00787 0.00238 -0.0204 0.1777 1.0000
5.000 0.7010 0.00812 0.00256 -0.0199 0.1603 1.0000
5.250 0.7261 0.00835 0.00275 -0.0195 0.1472 1.0000
5.500 0.7510 0.00860 0.00295 -0.0190 0.1334 1.0000
5.750 0.7757 0.00889 0.00318 -0.0185 0.1180 1.0000
6.000 0.8002 0.00919 0.00342 -0.0180 0.1031 1.0000
6.250 0.8249 0.00946 0.00367 -0.0175 0.0924 1.0000
6.500 0.8492 0.00980 0.00394 -0.0169 0.0788 1.0000
6.750 0.8732 0.01015 0.00423 -0.0164 0.0663 1.0000
7.000 0.8975 0.01046 0.00452 -0.0158 0.0582 1.0000
7.250 0.9215 0.01081 0.00484 -0.0152 0.0498 1.0000
7.500 0.9451 0.01119 0.00520 -0.0146 0.0413 1.0000
7.750 0.9684 0.01160 0.00557 -0.0140 0.0326 1.0000
8.000 0.9918 0.01198 0.00594 -0.0133 0.0271 1.0000
8.250 1.0145 0.01243 0.00636 -0.0126 0.0208 1.0000
8.500 1.0369 0.01289 0.00680 -0.0119 0.0161 1.0000
8.750 1.0598 0.01329 0.00721 -0.0112 0.0135 1.0000
9.000 1.0819 0.01375 0.00768 -0.0104 0.0110 1.0000
9.250 1.1043 0.01418 0.00815 -0.0096 0.0096 1.0000
9.500 1.1259 0.01465 0.00863 -0.0088 0.0078 1.0000
9.750 1.1472 0.01515 0.00915 -0.0080 0.0067 1.0000
10.000 1.1687 0.01561 0.00966 -0.0071 0.0059 1.0000
10.250 1.1897 0.01609 0.01018 -0.0063 0.0053 1.0000
10.500 1.2096 0.01665 0.01078 -0.0053 0.0044 1.0000
10.750 1.2293 0.01721 0.01138 -0.0042 0.0035 1.0000
11.250 1.2655 0.01854 0.01280 -0.0019 0.0018 1.0000
11.500 1.2813 0.01935 0.01366 -0.0005 0.0011 1.0000
11.750 1.2981 0.02001 0.01439 0.0008 0.0011 1.0000
12.000 1.3124 0.02082 0.01529 0.0024 0.0008 1.0000
12.250 1.3241 0.02177 0.01632 0.0043 0.0006 1.0000
12.500 1.3315 0.02272 0.01736 0.0069 0.0005 1.0000
12.750 1.3365 0.02376 0.01851 0.0095 0.0005 1.0000
13.000 1.3435 0.02484 0.01968 0.0114 0.0005 1.0000
13.250 1.3502 0.02607 0.02101 0.0130 0.0005 1.0000
13.500 1.3563 0.02746 0.02250 0.0143 0.0004 1.0000
13.750 1.3601 0.02916 0.02432 0.0154 0.0004 1.0000
14.000 1.3652 0.03084 0.02610 0.0162 0.0004 1.0000
14.250 1.3689 0.03278 0.02814 0.0167 0.0004 1.0000
14.500 1.3681 0.03532 0.03082 0.0169 0.0004 1.0000
14.750 1.3670 0.03809 0.03372 0.0167 0.0004 1.0000
15.000 1.3638 0.04129 0.03704 0.0161 0.0004 1.0000
15.250 1.3626 0.04441 0.04027 0.0151 0.0004 1.0000
15.500 1.3530 0.04886 0.04487 0.0135 0.0004 1.0000
15.750 1.3441 0.05342 0.04956 0.0116 0.0004 1.0000
16.000 1.3310 0.05881 0.05509 0.0091 0.0004 1.0000
16.250 1.3184 0.06431 0.06072 0.0065 0.0004 1.0000
16.500 1.3010 0.07078 0.06733 0.0034 0.0004 1.0000
16.750 1.2806 0.07800 0.07469 -0.0002 0.0004 1.0000
17.000 1.2488 0.08746 0.08432 -0.0050 0.0004 1.0000
17.250 1.2316 0.09447 0.09144 -0.0084 0.0004 1.0000
17.500 1.1972 0.10492 0.10205 -0.0136 0.0004 1.0000
17.750 1.1682 0.11459 0.11185 -0.0183 0.0004 1.0000
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Polar data table (+)
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