MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 100,000 Max Cl/Cd: 39.75 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh93-il-100000-n5.txt Download as CSV file: xf-mh93-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6983 0.09981 0.09460 -0.0032 1.0000 0.0233
-13.250 -0.7524 0.08505 0.07950 -0.0138 1.0000 0.0226
-13.000 -0.7922 0.07552 0.06964 -0.0198 1.0000 0.0223
-12.750 -0.8193 0.06905 0.06289 -0.0227 1.0000 0.0222
-12.500 -0.8408 0.06390 0.05744 -0.0241 1.0000 0.0221
-12.250 -0.8562 0.05976 0.05304 -0.0244 1.0000 0.0221
-12.000 -0.8659 0.05636 0.04942 -0.0239 1.0000 0.0221
-11.750 -0.8724 0.05332 0.04616 -0.0230 1.0000 0.0222
-11.500 -0.8753 0.05062 0.04325 -0.0218 1.0000 0.0223
-11.250 -0.8750 0.04816 0.04059 -0.0204 1.0000 0.0225
-11.000 -0.8719 0.04584 0.03807 -0.0189 1.0000 0.0227
-10.750 -0.8657 0.04366 0.03570 -0.0175 1.0000 0.0229
-10.500 -0.8567 0.04160 0.03345 -0.0161 1.0000 0.0233
-10.250 -0.8443 0.03964 0.03130 -0.0148 1.0000 0.0237
-10.000 -0.8290 0.03775 0.02921 -0.0138 1.0000 0.0242
-9.750 -0.8111 0.03596 0.02724 -0.0129 1.0000 0.0247
-9.500 -0.7916 0.03433 0.02546 -0.0122 1.0000 0.0253
-9.250 -0.7745 0.03302 0.02418 -0.0114 1.0000 0.0261
-9.000 -0.7572 0.03184 0.02297 -0.0105 1.0000 0.0273
-8.750 -0.7384 0.03063 0.02164 -0.0095 1.0000 0.0291
-8.500 -0.7216 0.02946 0.02053 -0.0086 1.0000 0.0305
-8.250 -0.7046 0.02841 0.01948 -0.0075 1.0000 0.0319
-8.000 -0.6879 0.02737 0.01839 -0.0064 1.0000 0.0334
-7.500 -0.6399 0.02530 0.01620 -0.0069 0.9234 0.0387
-7.250 -0.6222 0.02447 0.01534 -0.0055 0.8967 0.0428
-7.000 -0.6081 0.02372 0.01450 -0.0033 0.8746 0.0471
-6.750 -0.5944 0.02299 0.01371 -0.0009 0.8553 0.0533
-6.500 -0.5805 0.02222 0.01294 0.0015 0.8382 0.0631
-6.250 -0.5667 0.02138 0.01215 0.0039 0.8228 0.0806
-6.000 -0.5533 0.02042 0.01140 0.0062 0.8083 0.1156
-5.750 -0.5408 0.01935 0.01074 0.0084 0.7938 0.1837
-5.500 -0.5284 0.01840 0.01023 0.0108 0.7803 0.2672
-5.250 -0.5141 0.01772 0.00984 0.0132 0.7679 0.3399
-5.000 -0.4983 0.01716 0.00954 0.0154 0.7553 0.4034
-4.750 -0.4804 0.01674 0.00933 0.0175 0.7426 0.4623
-4.500 -0.4612 0.01642 0.00916 0.0196 0.7311 0.5149
-4.250 -0.4399 0.01620 0.00908 0.0214 0.7190 0.5627
-4.000 -0.4162 0.01609 0.00904 0.0228 0.7068 0.6034
-3.750 -0.3906 0.01607 0.00901 0.0240 0.6959 0.6350
-3.500 -0.3643 0.01609 0.00898 0.0250 0.6834 0.6613
-3.250 -0.3364 0.01618 0.00902 0.0257 0.6717 0.6838
-3.000 -0.3092 0.01628 0.00901 0.0266 0.6609 0.7044
-2.750 -0.2814 0.01640 0.00904 0.0272 0.6483 0.7231
-2.500 -0.2537 0.01653 0.00904 0.0279 0.6372 0.7393
-2.250 -0.2262 0.01664 0.00904 0.0285 0.6258 0.7538
-2.000 -0.1997 0.01674 0.00903 0.0293 0.6140 0.7680
-1.750 -0.1733 0.01685 0.00898 0.0301 0.6037 0.7811
-1.500 -0.1424 0.01704 0.00908 0.0300 0.5914 0.7908
-1.250 -0.1170 0.01712 0.00904 0.0309 0.5805 0.8029
-1.000 -0.0862 0.01730 0.00909 0.0309 0.5696 0.8118
-0.750 -0.0593 0.01741 0.00911 0.0314 0.5581 0.8221
-0.500 -0.0292 0.01758 0.00915 0.0315 0.5476 0.8307
-0.250 -0.0016 0.01770 0.00918 0.0318 0.5362 0.8401
0.000 0.0300 0.01787 0.00926 0.0315 0.5253 0.8479
0.250 0.0565 0.01798 0.00925 0.0321 0.5153 0.8574
0.500 0.0907 0.01817 0.00937 0.0312 0.5036 0.8638
0.750 0.1138 0.01824 0.00932 0.0322 0.4945 0.8739
1.000 0.1504 0.01840 0.00943 0.0308 0.4827 0.8785
1.250 0.1804 0.01852 0.00946 0.0305 0.4725 0.8855
1.500 0.2072 0.01861 0.00946 0.0307 0.4630 0.8930
1.750 0.2428 0.01875 0.00955 0.0293 0.4521 0.8974
2.000 0.2715 0.01885 0.00954 0.0291 0.4433 0.9042
2.250 0.2999 0.01896 0.00964 0.0289 0.4331 0.9106
2.500 0.3363 0.01908 0.00965 0.0272 0.4239 0.9145
2.750 0.3673 0.01921 0.00977 0.0264 0.4139 0.9202
3.000 0.3936 0.01932 0.00981 0.0266 0.4060 0.9268
3.250 0.4303 0.01946 0.00995 0.0246 0.3960 0.9304
3.500 0.4623 0.01961 0.01002 0.0236 0.3879 0.9354
3.750 0.4876 0.01976 0.01019 0.0238 0.3794 0.9421
4.000 0.5236 0.01991 0.01027 0.0220 0.3717 0.9455
4.250 0.5563 0.02009 0.01047 0.0207 0.3627 0.9502
4.500 0.5817 0.02027 0.01059 0.0209 0.3563 0.9564
4.750 0.6173 0.02047 0.01085 0.0189 0.3476 0.9597
5.000 0.6496 0.02065 0.01098 0.0177 0.3405 0.9640
5.250 0.6773 0.02091 0.01128 0.0173 0.3335 0.9693
5.500 0.7102 0.02112 0.01151 0.0158 0.3262 0.9729
5.750 0.7421 0.02136 0.01174 0.0145 0.3199 0.9768
6.000 0.7708 0.02166 0.01211 0.0138 0.3127 0.9815
6.250 0.8026 0.02190 0.01231 0.0125 0.3067 0.9850
6.500 0.8338 0.02223 0.01274 0.0111 0.3001 0.9889
6.750 0.8635 0.02256 0.01311 0.0101 0.2936 0.9930
7.000 0.8945 0.02286 0.01337 0.0089 0.2882 0.9965
7.250 0.9237 0.02328 0.01396 0.0078 0.2815 1.0000
7.500 0.9401 0.02365 0.01436 0.0093 0.2766 1.0000
8.000 0.9705 0.02453 0.01534 0.0125 0.2671 1.0000
8.250 0.9845 0.02497 0.01585 0.0144 0.2622 1.0000
8.500 0.9989 0.02537 0.01624 0.0162 0.2581 1.0000
8.750 1.0111 0.02589 0.01683 0.0182 0.2537 1.0000
9.000 1.0213 0.02644 0.01750 0.0205 0.2488 1.0000
9.250 1.0323 0.02690 0.01800 0.0228 0.2445 1.0000
9.500 1.0449 0.02732 0.01836 0.0249 0.2409 1.0000
9.750 1.0502 0.02800 0.01922 0.0278 0.2363 1.0000
10.000 1.0569 0.02859 0.01990 0.0305 0.2318 1.0000
10.250 1.0658 0.02908 0.02039 0.0329 0.2278 1.0000
10.500 1.0750 0.02964 0.02094 0.0352 0.2241 1.0000
10.750 1.0766 0.03048 0.02196 0.0382 0.2196 1.0000
11.000 1.0817 0.03121 0.02275 0.0406 0.2154 1.0000
11.250 1.0888 0.03181 0.02334 0.0429 0.2117 1.0000
11.500 1.0914 0.03272 0.02431 0.0453 0.2080 1.0000
11.750 1.0896 0.03401 0.02575 0.0475 0.2040 1.0000
12.000 1.0932 0.03516 0.02698 0.0489 0.1999 1.0000
12.250 1.1031 0.03604 0.02784 0.0499 0.1963 1.0000
12.500 1.1019 0.03780 0.02973 0.0509 0.1925 1.0000
12.750 1.0980 0.03989 0.03198 0.0516 0.1884 1.0000
13.000 1.1010 0.04154 0.03370 0.0521 0.1846 1.0000
13.250 1.1139 0.04243 0.03453 0.0525 0.1810 1.0000
13.500 1.0980 0.04599 0.03833 0.0522 0.1772 1.0000
13.750 1.0878 0.04928 0.04177 0.0517 0.1733 1.0000
14.000 1.0902 0.05137 0.04390 0.0514 0.1696 1.0000
14.250 1.0980 0.05295 0.04548 0.0514 0.1663 1.0000
14.500 1.0620 0.05972 0.05253 0.0488 0.1625 1.0000
14.750 1.0361 0.06578 0.05874 0.0463 0.1586 1.0000
15.000 1.0492 0.06679 0.05973 0.0463 0.1551 1.0000
15.250 1.0200 0.07383 0.06691 0.0431 0.1515 1.0000
15.500 0.8287 0.10932 0.10263 0.0253 0.1375 1.0000
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