MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 100,000 Max Cl/Cd: 50.15 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh20-il-100000-n5.txt Download as CSV file: xf-mh20-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5234 0.12261 0.11791 0.0103 1.0000 0.0237
-10.250 -0.5178 0.11855 0.11387 0.0092 1.0000 0.0219
-10.000 -0.5141 0.11442 0.10977 0.0073 1.0000 0.0207
-9.750 -0.5114 0.11007 0.10546 0.0052 1.0000 0.0195
-9.500 -0.5105 0.10527 0.10071 0.0027 1.0000 0.0183
-9.250 -0.5114 0.09996 0.09547 -0.0004 1.0000 0.0171
-9.000 -0.5125 0.09399 0.08958 -0.0045 1.0000 0.0159
-8.500 -0.5067 0.08562 0.08126 -0.0094 1.0000 0.0150
-8.250 -0.5084 0.08099 0.07670 -0.0124 1.0000 0.0148
-8.000 -0.5121 0.07602 0.07181 -0.0165 1.0000 0.0146
-7.750 -0.5153 0.07108 0.06688 -0.0201 1.0000 0.0145
-7.500 -0.5149 0.06588 0.06166 -0.0236 1.0000 0.0142
-7.250 -0.5131 0.06049 0.05619 -0.0264 1.0000 0.0140
-7.000 -0.5091 0.05520 0.05076 -0.0284 1.0000 0.0138
-6.750 -0.5030 0.05025 0.04560 -0.0297 1.0000 0.0136
-6.500 -0.4953 0.04547 0.04054 -0.0303 1.0000 0.0134
-6.250 -0.4862 0.04116 0.03590 -0.0302 0.9994 0.0132
-6.000 -0.4629 0.03614 0.03027 -0.0320 0.9644 0.0131
-5.750 -0.4381 0.03218 0.02569 -0.0329 0.9457 0.0129
-5.500 -0.4136 0.02887 0.02177 -0.0329 0.9305 0.0130
-5.250 -0.3893 0.02625 0.01850 -0.0322 0.9170 0.0132
-5.000 -0.3651 0.02412 0.01593 -0.0313 0.9047 0.0135
-4.750 -0.3409 0.02243 0.01389 -0.0302 0.8934 0.0141
-4.500 -0.3174 0.02105 0.01226 -0.0292 0.8831 0.0160
-4.250 -0.2948 0.01993 0.01100 -0.0282 0.8738 0.0200
-4.000 -0.2714 0.01892 0.00977 -0.0270 0.8642 0.0238
-3.750 -0.2487 0.01775 0.00847 -0.0257 0.8554 0.0334
-3.500 -0.2271 0.01655 0.00762 -0.0245 0.8478 0.0923
-3.250 -0.2036 0.01581 0.00711 -0.0238 0.8393 0.1596
-3.000 -0.1800 0.01523 0.00671 -0.0231 0.8321 0.2273
-2.750 -0.1565 0.01463 0.00628 -0.0223 0.8246 0.3119
-2.500 -0.1336 0.01394 0.00600 -0.0214 0.8177 0.4330
-2.250 -0.1110 0.01309 0.00582 -0.0200 0.8109 0.6189
-2.000 -0.0451 0.01249 0.00576 -0.0257 0.8075 0.8713
-1.750 0.0118 0.01258 0.00562 -0.0310 0.8012 0.9433
-1.500 0.0557 0.01267 0.00541 -0.0340 0.7952 0.9796
-1.250 0.1053 0.01260 0.00512 -0.0386 0.7880 1.0000
-1.000 0.1277 0.01262 0.00496 -0.0376 0.7809 1.0000
-0.750 0.1518 0.01266 0.00486 -0.0371 0.7723 1.0000
-0.500 0.1751 0.01270 0.00473 -0.0362 0.7650 1.0000
-0.250 0.1989 0.01276 0.00468 -0.0355 0.7570 1.0000
0.000 0.2229 0.01282 0.00464 -0.0348 0.7490 1.0000
0.250 0.2465 0.01289 0.00460 -0.0339 0.7417 1.0000
0.500 0.2710 0.01297 0.00463 -0.0334 0.7332 1.0000
0.750 0.2949 0.01304 0.00461 -0.0325 0.7260 1.0000
1.000 0.3194 0.01313 0.00466 -0.0319 0.7172 1.0000
1.250 0.3439 0.01323 0.00472 -0.0312 0.7090 1.0000
1.500 0.3680 0.01330 0.00475 -0.0304 0.7011 1.0000
1.750 0.3928 0.01341 0.00487 -0.0298 0.6916 1.0000
2.000 0.4173 0.01350 0.00495 -0.0291 0.6828 1.0000
2.250 0.4417 0.01358 0.00501 -0.0283 0.6740 1.0000
2.500 0.4664 0.01369 0.00515 -0.0277 0.6634 1.0000
2.750 0.4911 0.01380 0.00528 -0.0270 0.6529 1.0000
3.000 0.5156 0.01389 0.00546 -0.0263 0.6423 1.0000
3.250 0.5402 0.01398 0.00558 -0.0255 0.6311 1.0000
3.500 0.5648 0.01407 0.00572 -0.0247 0.6190 1.0000
3.750 0.5894 0.01417 0.00589 -0.0240 0.6055 1.0000
4.000 0.6141 0.01427 0.00609 -0.0233 0.5902 1.0000
4.250 0.6386 0.01439 0.00636 -0.0226 0.5734 1.0000
4.500 0.6630 0.01448 0.00654 -0.0217 0.5552 1.0000
4.750 0.6872 0.01461 0.00675 -0.0209 0.5343 1.0000
5.000 0.7111 0.01474 0.00694 -0.0200 0.5113 1.0000
5.250 0.7347 0.01493 0.00716 -0.0190 0.4855 1.0000
5.500 0.7577 0.01520 0.00745 -0.0180 0.4568 1.0000
5.750 0.7803 0.01556 0.00791 -0.0170 0.4257 1.0000
6.000 0.8019 0.01602 0.00834 -0.0159 0.3917 1.0000
6.250 0.8226 0.01660 0.00886 -0.0148 0.3509 1.0000
6.500 0.8417 0.01733 0.00946 -0.0136 0.2992 1.0000
6.750 0.8584 0.01833 0.01019 -0.0124 0.2325 1.0000
7.000 0.8722 0.01972 0.01114 -0.0110 0.1525 1.0000
7.250 0.8836 0.02149 0.01243 -0.0094 0.0803 1.0000
7.500 0.8935 0.02347 0.01411 -0.0073 0.0425 1.0000
7.750 0.9034 0.02533 0.01596 -0.0052 0.0286 1.0000
8.000 0.9147 0.02689 0.01764 -0.0033 0.0212 1.0000
8.250 0.9213 0.02883 0.01967 -0.0010 0.0172 1.0000
8.500 0.9286 0.03074 0.02173 0.0014 0.0159 1.0000
8.750 0.9391 0.03252 0.02370 0.0035 0.0142 1.0000
9.000 0.9502 0.03414 0.02550 0.0052 0.0122 1.0000
9.250 0.9597 0.03584 0.02734 0.0069 0.0109 1.0000
9.500 0.9645 0.03767 0.02942 0.0089 0.0098 1.0000
9.750 0.9704 0.03990 0.03183 0.0107 0.0094 1.0000
10.000 0.9729 0.04318 0.03535 0.0126 0.0089 1.0000
10.250 0.9733 0.04662 0.03904 0.0142 0.0087 1.0000
10.500 0.9721 0.04947 0.04217 0.0156 0.0086 1.0000
10.750 0.9679 0.05264 0.04561 0.0166 0.0085 1.0000
11.000 0.9619 0.05604 0.04925 0.0170 0.0086 1.0000
11.250 0.9525 0.05984 0.05330 0.0170 0.0085 1.0000
11.500 0.9408 0.06408 0.05779 0.0163 0.0084 1.0000
11.750 0.9289 0.06858 0.06250 0.0149 0.0085 1.0000
12.000 0.9144 0.07377 0.06789 0.0128 0.0085 1.0000
12.250 0.9011 0.07914 0.07342 0.0102 0.0086 1.0000
12.500 0.8850 0.08544 0.07989 0.0067 0.0086 1.0000
12.750 0.8697 0.09217 0.08676 0.0027 0.0087 1.0000
13.000 0.8535 0.09975 0.09447 -0.0020 0.0087 1.0000
13.500 0.7249 0.10979 0.10509 -0.0040 0.0096 1.0000
13.750 0.6892 0.12262 0.11798 -0.0108 0.0110 1.0000
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Polar data table (+)
Polar graphs
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