MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 94 16.03% (mh94-il) Reynolds number: 100,000 Max Cl/Cd: 36.46 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh94-il-100000-n5.txt Download as CSV file: xf-mh94-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 94 16.03%
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5955 0.11377 0.10755 -0.0501 1.0000 0.0246
-15.000 -0.6279 0.10297 0.09662 -0.0560 1.0000 0.0243
-14.750 -0.6606 0.09330 0.08676 -0.0615 1.0000 0.0240
-14.500 -0.6870 0.08576 0.07905 -0.0653 1.0000 0.0239
-14.250 -0.7105 0.07938 0.07247 -0.0682 1.0000 0.0238
-14.000 -0.7303 0.07407 0.06697 -0.0701 1.0000 0.0237
-13.750 -0.7474 0.06946 0.06217 -0.0712 1.0000 0.0237
-13.500 -0.7620 0.06542 0.05794 -0.0717 1.0000 0.0237
-13.250 -0.7746 0.06180 0.05412 -0.0717 1.0000 0.0238
-13.000 -0.7852 0.05855 0.05068 -0.0712 1.0000 0.0240
-12.750 -0.7930 0.05570 0.04762 -0.0702 1.0000 0.0241
-12.500 -0.7983 0.05314 0.04488 -0.0689 1.0000 0.0243
-12.250 -0.8022 0.05079 0.04233 -0.0674 1.0000 0.0245
-12.000 -0.8030 0.04871 0.04008 -0.0656 1.0000 0.0248
-11.750 -0.8011 0.04711 0.03848 -0.0639 1.0000 0.0252
-11.500 -0.7989 0.04558 0.03689 -0.0620 1.0000 0.0255
-11.250 -0.7983 0.04413 0.03539 -0.0599 1.0000 0.0262
-11.000 -0.7961 0.04271 0.03388 -0.0576 1.0000 0.0268
-10.750 -0.7940 0.04135 0.03241 -0.0551 1.0000 0.0275
-10.500 -0.7922 0.04002 0.03090 -0.0524 1.0000 0.0285
-10.250 -0.7893 0.03884 0.02974 -0.0498 1.0000 0.0291
-10.000 -0.7893 0.03777 0.02868 -0.0468 1.0000 0.0298
-9.750 -0.7884 0.03672 0.02760 -0.0436 1.0000 0.0304
-9.500 -0.7895 0.03574 0.02657 -0.0400 1.0000 0.0311
-9.250 -0.7925 0.03480 0.02556 -0.0359 1.0000 0.0318
-9.000 -0.7956 0.03391 0.02459 -0.0317 1.0000 0.0326
-8.750 -0.7968 0.03295 0.02365 -0.0279 1.0000 0.0333
-8.500 -0.7963 0.03203 0.02272 -0.0243 1.0000 0.0342
-8.250 -0.7940 0.03113 0.02179 -0.0209 1.0000 0.0354
-8.000 -0.7895 0.03029 0.02084 -0.0177 1.0000 0.0374
-7.750 -0.7831 0.02937 0.01996 -0.0151 0.9996 0.0391
-7.500 -0.7575 0.02838 0.01891 -0.0160 0.9950 0.0432
-7.250 -0.7328 0.02741 0.01788 -0.0166 0.9902 0.0478
-7.000 -0.7078 0.02645 0.01692 -0.0173 0.9852 0.0546
-6.750 -0.6828 0.02544 0.01597 -0.0180 0.9804 0.0651
-6.500 -0.6599 0.02438 0.01504 -0.0182 0.9747 0.0844
-6.250 -0.6338 0.02315 0.01415 -0.0194 0.9703 0.1283
-6.000 -0.6165 0.02190 0.01335 -0.0187 0.9633 0.1997
-5.750 -0.5906 0.02090 0.01281 -0.0196 0.9583 0.2829
-5.500 -0.5682 0.02027 0.01248 -0.0192 0.9520 0.3453
-5.250 -0.5405 0.01989 0.01230 -0.0195 0.9462 0.3975
-5.000 -0.5082 0.01970 0.01221 -0.0206 0.9419 0.4442
-4.750 -0.4857 0.01954 0.01212 -0.0195 0.9340 0.4791
-4.500 -0.4530 0.01952 0.01215 -0.0203 0.9292 0.5107
-4.250 -0.4268 0.01946 0.01205 -0.0199 0.9221 0.5337
-4.000 -0.3962 0.01940 0.01197 -0.0202 0.9159 0.5507
-3.750 -0.3595 0.01935 0.01187 -0.0217 0.9119 0.5653
-3.500 -0.3369 0.01927 0.01175 -0.0206 0.9028 0.5779
-3.250 -0.3021 0.01916 0.01155 -0.0218 0.8976 0.5921
-3.000 -0.2741 0.01911 0.01150 -0.0215 0.8903 0.6036
-2.750 -0.2435 0.01902 0.01137 -0.0218 0.8832 0.6155
-2.500 -0.2056 0.01886 0.01113 -0.0235 0.8790 0.6288
-2.250 -0.1830 0.01884 0.01114 -0.0221 0.8688 0.6378
-2.000 -0.1468 0.01864 0.01087 -0.0235 0.8634 0.6494
-1.750 -0.1195 0.01856 0.01081 -0.0230 0.8547 0.6582
-1.500 -0.0865 0.01835 0.01055 -0.0236 0.8476 0.6688
-1.000 -0.0242 0.01801 0.01018 -0.0241 0.8312 0.6876
-0.750 0.0165 0.01778 0.00996 -0.0259 0.8259 0.6954
-0.500 0.0403 0.01765 0.00979 -0.0249 0.8133 0.7056
-0.250 0.0782 0.01745 0.00960 -0.0261 0.8055 0.7129
0.000 0.1071 0.01729 0.00943 -0.0259 0.7931 0.7222
0.250 0.1375 0.01714 0.00929 -0.0259 0.7806 0.7301
0.500 0.1752 0.01692 0.00904 -0.0272 0.7696 0.7385
0.750 0.2054 0.01677 0.00887 -0.0272 0.7547 0.7473
1.000 0.2352 0.01668 0.00879 -0.0270 0.7387 0.7547
1.250 0.2665 0.01655 0.00861 -0.0273 0.7220 0.7642
1.500 0.2971 0.01649 0.00854 -0.0273 0.7041 0.7709
1.750 0.3272 0.01644 0.00845 -0.0272 0.6851 0.7794
2.000 0.3564 0.01641 0.00836 -0.0271 0.6646 0.7874
2.250 0.3844 0.01644 0.00834 -0.0266 0.6430 0.7950
2.500 0.4107 0.01647 0.00828 -0.0261 0.6200 0.8043
2.750 0.4341 0.01656 0.00833 -0.0247 0.5949 0.8114
3.000 0.4579 0.01666 0.00832 -0.0237 0.5686 0.8208
3.250 0.4797 0.01681 0.00838 -0.0222 0.5405 0.8286
3.500 0.5005 0.01698 0.00842 -0.0206 0.5114 0.8380
3.750 0.5199 0.01717 0.00852 -0.0188 0.4822 0.8468
4.250 0.5568 0.01763 0.00875 -0.0150 0.4261 0.8661
4.500 0.5743 0.01790 0.00889 -0.0130 0.4002 0.8775
4.750 0.5925 0.01817 0.00909 -0.0111 0.3753 0.8875
5.000 0.6104 0.01846 0.00929 -0.0093 0.3514 0.8990
5.250 0.6285 0.01878 0.00952 -0.0076 0.3292 0.9119
5.500 0.6493 0.01915 0.00981 -0.0065 0.3077 0.9238
5.750 0.6728 0.01953 0.01013 -0.0060 0.2863 0.9365
6.000 0.6992 0.01999 0.01052 -0.0063 0.2657 0.9496
6.250 0.7285 0.02051 0.01098 -0.0072 0.2456 0.9629
6.500 0.7598 0.02109 0.01148 -0.0087 0.2270 0.9773
6.750 0.7905 0.02168 0.01200 -0.0102 0.2100 0.9990
7.000 0.7979 0.02204 0.01229 -0.0072 0.2000 1.0000
7.250 0.8106 0.02252 0.01269 -0.0052 0.1897 1.0000
7.500 0.8262 0.02306 0.01319 -0.0037 0.1803 1.0000
7.750 0.8408 0.02370 0.01373 -0.0021 0.1723 1.0000
8.000 0.8583 0.02429 0.01433 -0.0009 0.1644 1.0000
8.250 0.8735 0.02499 0.01496 0.0006 0.1580 1.0000
8.500 0.8910 0.02567 0.01564 0.0017 0.1520 1.0000
8.750 0.9077 0.02638 0.01636 0.0029 0.1468 1.0000
9.000 0.9229 0.02720 0.01709 0.0042 0.1427 1.0000
9.250 0.9410 0.02794 0.01789 0.0052 0.1382 1.0000
9.500 0.9578 0.02872 0.01871 0.0063 0.1341 1.0000
9.750 0.9737 0.02957 0.01952 0.0074 0.1308 1.0000
10.000 0.9907 0.03048 0.02041 0.0083 0.1279 1.0000
10.250 1.0084 0.03136 0.02140 0.0092 0.1250 1.0000
10.500 1.0251 0.03228 0.02237 0.0101 0.1221 1.0000
10.750 1.0411 0.03322 0.02333 0.0111 0.1196 1.0000
11.000 1.0572 0.03420 0.02429 0.0120 0.1174 1.0000
11.250 1.0742 0.03528 0.02541 0.0127 0.1152 1.0000
11.500 1.0890 0.03640 0.02668 0.0137 0.1130 1.0000
11.750 1.1040 0.03756 0.02795 0.0146 0.1112 1.0000
12.000 1.1182 0.03875 0.02923 0.0155 0.1093 1.0000
12.250 1.1320 0.03994 0.03048 0.0164 0.1076 1.0000
12.500 1.1469 0.04113 0.03168 0.0171 0.1060 1.0000
12.750 1.1651 0.04237 0.03286 0.0175 0.1044 1.0000
13.000 1.1708 0.04403 0.03478 0.0188 0.1030 1.0000
13.250 1.1766 0.04579 0.03675 0.0200 0.1017 1.0000
13.500 1.1819 0.04765 0.03880 0.0210 0.1003 1.0000
13.750 1.1864 0.04959 0.04091 0.0219 0.0991 1.0000
14.000 1.1899 0.05161 0.04307 0.0227 0.0979 1.0000
14.250 1.1939 0.05362 0.04521 0.0234 0.0968 1.0000
14.500 1.1992 0.05560 0.04727 0.0238 0.0957 1.0000
14.750 1.2082 0.05740 0.04910 0.0241 0.0946 1.0000
15.000 1.2192 0.05925 0.05096 0.0243 0.0936 1.0000
15.250 1.2029 0.06310 0.05511 0.0245 0.0929 1.0000
15.500 1.1829 0.06764 0.05994 0.0241 0.0923 1.0000
15.750 1.1570 0.07321 0.06582 0.0227 0.0917 1.0000
16.000 1.1199 0.08076 0.07369 0.0197 0.0912 1.0000
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Polar data table (+)
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