MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.02 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh84-il-1000000-n5.txt Download as CSV file: xf-mh84-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6689 0.06942 0.06659 -0.0288 0.8227 0.0076
-12.000 -0.7029 0.06116 0.05818 -0.0343 0.8029 0.0076
-11.750 -0.7642 0.05079 0.04765 -0.0407 0.7835 0.0075
-11.500 -0.8164 0.03161 0.02796 -0.0636 0.7680 0.0075
-11.250 -0.8021 0.02842 0.02453 -0.0666 0.7548 0.0075
-10.750 -0.7611 0.02475 0.02048 -0.0689 0.7290 0.0075
-10.500 -0.7381 0.02336 0.01892 -0.0695 0.7170 0.0076
-10.250 -0.7138 0.02217 0.01757 -0.0700 0.7045 0.0076
-10.000 -0.6887 0.02112 0.01638 -0.0703 0.6934 0.0076
-9.750 -0.6630 0.02016 0.01527 -0.0706 0.6815 0.0076
-9.500 -0.6368 0.01929 0.01427 -0.0707 0.6706 0.0076
-9.250 -0.6103 0.01840 0.01324 -0.0709 0.6594 0.0077
-9.000 -0.5837 0.01743 0.01213 -0.0711 0.6484 0.0077
-8.750 -0.5566 0.01662 0.01119 -0.0713 0.6377 0.0078
-8.500 -0.5290 0.01592 0.01036 -0.0713 0.6267 0.0079
-8.250 -0.5011 0.01530 0.00963 -0.0714 0.6163 0.0080
-8.000 -0.4729 0.01473 0.00897 -0.0714 0.6054 0.0080
-7.750 -0.4445 0.01424 0.00839 -0.0714 0.5954 0.0081
-7.500 -0.4160 0.01379 0.00785 -0.0713 0.5846 0.0082
-7.250 -0.3873 0.01339 0.00736 -0.0713 0.5748 0.0083
-7.000 -0.3585 0.01302 0.00691 -0.0712 0.5638 0.0084
-6.750 -0.3295 0.01268 0.00650 -0.0712 0.5544 0.0085
-6.500 -0.3005 0.01238 0.00611 -0.0711 0.5436 0.0087
-6.250 -0.2714 0.01208 0.00576 -0.0710 0.5344 0.0088
-6.000 -0.2423 0.01182 0.00542 -0.0710 0.5238 0.0090
-5.750 -0.2131 0.01156 0.00509 -0.0709 0.5146 0.0092
-5.500 -0.1839 0.01132 0.00478 -0.0708 0.5045 0.0094
-5.250 -0.1545 0.01109 0.00449 -0.0707 0.4953 0.0096
-4.750 -0.0958 0.01067 0.00394 -0.0706 0.4765 0.0100
-4.250 -0.0370 0.01027 0.00343 -0.0704 0.4577 0.0110
-3.750 0.0219 0.01000 0.00306 -0.0703 0.4393 0.0122
-3.500 0.0513 0.00988 0.00288 -0.0702 0.4297 0.0132
-3.250 0.0807 0.00976 0.00273 -0.0701 0.4212 0.0145
-3.000 0.1102 0.00966 0.00259 -0.0700 0.4121 0.0165
-2.750 0.1397 0.00955 0.00247 -0.0700 0.4044 0.0195
-2.500 0.1691 0.00947 0.00235 -0.0699 0.3950 0.0242
-2.250 0.1986 0.00937 0.00225 -0.0699 0.3874 0.0311
-2.000 0.2280 0.00927 0.00215 -0.0698 0.3786 0.0413
-1.750 0.2574 0.00917 0.00207 -0.0698 0.3707 0.0557
-1.500 0.2868 0.00907 0.00201 -0.0698 0.3627 0.0734
-1.250 0.3162 0.00898 0.00196 -0.0698 0.3555 0.0947
-1.000 0.3456 0.00890 0.00193 -0.0698 0.3478 0.1167
-0.750 0.3749 0.00886 0.00192 -0.0698 0.3394 0.1412
-0.500 0.4043 0.00882 0.00192 -0.0698 0.3331 0.1614
-0.250 0.4336 0.00881 0.00193 -0.0697 0.3260 0.1814
0.000 0.4629 0.00883 0.00195 -0.0697 0.3196 0.1954
0.250 0.4922 0.00885 0.00197 -0.0697 0.3120 0.2100
0.500 0.5214 0.00890 0.00201 -0.0696 0.3050 0.2230
0.750 0.5507 0.00893 0.00204 -0.0696 0.2995 0.2357
1.000 0.5799 0.00897 0.00208 -0.0695 0.2929 0.2505
1.250 0.6090 0.00902 0.00214 -0.0695 0.2867 0.2668
1.500 0.6381 0.00907 0.00219 -0.0695 0.2803 0.2840
1.750 0.6671 0.00914 0.00227 -0.0694 0.2739 0.3042
2.000 0.6962 0.00917 0.00234 -0.0694 0.2693 0.3287
2.250 0.7251 0.00921 0.00242 -0.0694 0.2633 0.3572
2.500 0.7539 0.00928 0.00253 -0.0694 0.2569 0.3919
2.750 0.7828 0.00930 0.00262 -0.0694 0.2525 0.4314
3.000 0.8116 0.00933 0.00274 -0.0694 0.2473 0.4769
3.250 0.8401 0.00939 0.00287 -0.0694 0.2414 0.5292
3.500 0.8687 0.00938 0.00300 -0.0694 0.2372 0.5885
3.750 0.8970 0.00940 0.00314 -0.0693 0.2324 0.6531
4.000 0.9247 0.00941 0.00331 -0.0692 0.2274 0.7300
4.250 0.9498 0.00923 0.00345 -0.0684 0.2237 0.8553
4.500 0.9784 0.00918 0.00355 -0.0682 0.2192 1.0000
4.750 1.0068 0.00937 0.00369 -0.0681 0.2148 1.0000
5.000 1.0350 0.00956 0.00385 -0.0681 0.2110 1.0000
5.250 1.0634 0.00972 0.00399 -0.0680 0.2080 1.0000
5.500 1.0915 0.00991 0.00414 -0.0680 0.2040 1.0000
5.750 1.1193 0.01013 0.00432 -0.0679 0.1997 1.0000
6.000 1.1472 0.01033 0.00450 -0.0678 0.1964 1.0000
6.250 1.1752 0.01051 0.00467 -0.0678 0.1938 1.0000
6.500 1.2029 0.01071 0.00485 -0.0677 0.1907 1.0000
6.750 1.2303 0.01094 0.00505 -0.0676 0.1871 1.0000
7.000 1.2575 0.01119 0.00528 -0.0675 0.1835 1.0000
7.250 1.2850 0.01139 0.00547 -0.0674 0.1810 1.0000
7.500 1.3122 0.01161 0.00569 -0.0673 0.1783 1.0000
7.750 1.3392 0.01185 0.00592 -0.0671 0.1754 1.0000
8.000 1.3657 0.01213 0.00617 -0.0670 0.1724 1.0000
8.250 1.3924 0.01238 0.00642 -0.0668 0.1698 1.0000
8.500 1.4190 0.01261 0.00666 -0.0667 0.1675 1.0000
8.750 1.4453 0.01287 0.00692 -0.0665 0.1647 1.0000
9.000 1.4712 0.01317 0.00720 -0.0663 0.1619 1.0000
9.250 1.4967 0.01349 0.00751 -0.0660 0.1592 1.0000
9.500 1.5223 0.01377 0.00781 -0.0658 0.1572 1.0000
9.750 1.5479 0.01404 0.00810 -0.0656 0.1553 1.0000
10.000 1.5730 0.01434 0.00841 -0.0653 0.1530 1.0000
10.250 1.5974 0.01469 0.00875 -0.0649 0.1502 1.0000
10.500 1.6211 0.01507 0.00913 -0.0645 0.1475 1.0000
10.750 1.6449 0.01543 0.00950 -0.0641 0.1455 1.0000
11.000 1.6688 0.01575 0.00986 -0.0637 0.1439 1.0000
11.250 1.6919 0.01611 0.01023 -0.0633 0.1421 1.0000
11.500 1.7142 0.01650 0.01065 -0.0627 0.1400 1.0000
11.750 1.7354 0.01695 0.01111 -0.0620 0.1379 1.0000
12.000 1.7553 0.01746 0.01162 -0.0612 0.1355 1.0000
12.250 1.7754 0.01789 0.01210 -0.0604 0.1338 1.0000
12.500 1.7947 0.01835 0.01259 -0.0596 0.1324 1.0000
12.750 1.8120 0.01885 0.01313 -0.0584 0.1308 1.0000
13.000 1.8237 0.01943 0.01375 -0.0565 0.1293 1.0000
13.250 1.8326 0.02018 0.01453 -0.0545 0.1277 1.0000
13.500 1.8409 0.02108 0.01548 -0.0528 0.1262 1.0000
13.750 1.8484 0.02218 0.01661 -0.0513 0.1244 1.0000
14.000 1.8586 0.02320 0.01769 -0.0503 0.1234 1.0000
14.250 1.8688 0.02431 0.01887 -0.0493 0.1221 1.0000
14.500 1.8777 0.02558 0.02020 -0.0485 0.1209 1.0000
14.750 1.8856 0.02703 0.02169 -0.0478 0.1196 1.0000
15.000 1.8919 0.02867 0.02339 -0.0472 0.1182 1.0000
15.250 1.8964 0.03055 0.02532 -0.0467 0.1168 1.0000
15.500 1.8988 0.03270 0.02753 -0.0464 0.1153 1.0000
15.750 1.9000 0.03506 0.02995 -0.0461 0.1138 1.0000
16.000 1.9047 0.03714 0.03211 -0.0460 0.1130 1.0000
16.250 1.9073 0.03945 0.03451 -0.0460 0.1120 1.0000
16.500 1.9086 0.04200 0.03714 -0.0462 0.1109 1.0000
16.750 1.9071 0.04488 0.04008 -0.0464 0.1096 1.0000
17.000 1.9034 0.04808 0.04336 -0.0468 0.1082 1.0000
17.250 1.8971 0.05167 0.04702 -0.0474 0.1068 1.0000
17.500 1.8896 0.05558 0.05101 -0.0483 0.1056 1.0000
17.750 1.8807 0.05978 0.05528 -0.0493 0.1042 1.0000
18.000 1.8774 0.06334 0.05894 -0.0503 0.1034 1.0000
18.250 1.8727 0.06717 0.06287 -0.0514 0.1022 1.0000
18.500 1.8665 0.07130 0.06708 -0.0527 0.1010 1.0000
18.750 1.8583 0.07573 0.07160 -0.0542 0.0998 1.0000
19.000 1.8473 0.08069 0.07664 -0.0560 0.0983 1.0000
19.250 1.8333 0.08619 0.08221 -0.0581 0.0969 1.0000
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Polar data table (+)
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