MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 100,000 Max Cl/Cd: 33.36 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh93-il-100000.txt Download as CSV file: xf-mh93-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6802 0.08055 0.07580 -0.0197 1.0000 0.0725
-11.000 -0.7445 0.07188 0.06683 -0.0236 1.0000 0.0696
-10.750 -0.7783 0.06649 0.06114 -0.0229 1.0000 0.0650
-10.500 -0.7985 0.06221 0.05667 -0.0211 1.0000 0.0628
-10.250 -0.8523 0.05802 0.05172 -0.0147 1.0000 0.0582
-10.000 -0.8437 0.05413 0.04774 -0.0138 1.0000 0.0570
-9.750 -0.8436 0.05054 0.04387 -0.0117 1.0000 0.0555
-9.500 -0.8443 0.04683 0.03971 -0.0090 1.0000 0.0538
-9.250 -0.8496 0.04354 0.03560 -0.0049 1.0000 0.0519
-9.000 -0.8359 0.04121 0.03290 -0.0031 1.0000 0.0515
-8.750 -0.8154 0.03839 0.02985 -0.0024 1.0000 0.0517
-8.500 -0.7904 0.03575 0.02710 -0.0024 1.0000 0.0523
-8.250 -0.7636 0.03363 0.02494 -0.0025 1.0000 0.0533
-8.000 -0.7380 0.03197 0.02326 -0.0025 1.0000 0.0555
-7.750 -0.7178 0.03066 0.02172 -0.0015 1.0000 0.0584
-7.500 -0.6959 0.02904 0.02023 -0.0011 1.0000 0.0608
-7.250 -0.6949 0.02841 0.01964 0.0026 1.0000 0.0627
-7.000 -0.6759 0.02740 0.01859 0.0033 0.9959 0.0659
-6.750 -0.6238 0.02546 0.01680 -0.0016 0.9847 0.0754
-6.500 -0.5780 0.02340 0.01499 -0.0058 0.9726 0.0912
-6.250 -0.5441 0.02117 0.01319 -0.0081 0.9572 0.1342
-6.000 -0.5406 0.01849 0.01192 -0.0056 0.9357 0.3180
-5.750 -0.5282 0.01777 0.01174 -0.0028 0.9161 0.4325
-5.500 -0.5129 0.01758 0.01174 0.0001 0.8982 0.4992
-5.250 -0.4968 0.01755 0.01184 0.0032 0.8813 0.5503
-5.000 -0.4784 0.01766 0.01206 0.0062 0.8652 0.5949
-4.750 -0.4584 0.01793 0.01238 0.0091 0.8499 0.6349
-4.500 -0.4356 0.01838 0.01285 0.0118 0.8354 0.6699
-4.250 -0.4107 0.01899 0.01341 0.0145 0.8220 0.6996
-4.000 -0.3823 0.01969 0.01402 0.0166 0.8085 0.7229
-3.750 -0.3526 0.02033 0.01455 0.0181 0.7938 0.7422
-3.500 -0.3198 0.02100 0.01508 0.0191 0.7798 0.7577
-3.250 -0.2874 0.02159 0.01552 0.0202 0.7670 0.7720
-3.000 -0.2576 0.02205 0.01580 0.0215 0.7542 0.7866
-2.750 -0.2290 0.02244 0.01606 0.0224 0.7397 0.8017
-2.500 -0.1811 0.02310 0.01655 0.0207 0.7255 0.8089
-2.250 -0.1512 0.02330 0.01658 0.0214 0.7133 0.8221
-2.000 -0.1235 0.02346 0.01660 0.0222 0.7001 0.8363
-1.750 -0.0687 0.02377 0.01675 0.0185 0.6847 0.8419
-1.500 -0.0419 0.02383 0.01667 0.0191 0.6720 0.8559
-1.250 0.0075 0.02392 0.01656 0.0162 0.6588 0.8628
-1.000 0.0375 0.02391 0.01644 0.0160 0.6450 0.8754
-0.750 0.0796 0.02396 0.01637 0.0137 0.6306 0.8848
-0.500 0.1149 0.02389 0.01617 0.0126 0.6180 0.8956
-0.250 0.1424 0.02384 0.01597 0.0128 0.6064 0.9087
0.000 0.1908 0.02370 0.01574 0.0091 0.5913 0.9165
0.250 0.2242 0.02361 0.01555 0.0079 0.5786 0.9280
0.500 0.2630 0.02341 0.01518 0.0059 0.5671 0.9382
0.750 0.3033 0.02318 0.01488 0.0033 0.5531 0.9475
1.000 0.3383 0.02306 0.01471 0.0015 0.5403 0.9579
1.250 0.3786 0.02279 0.01430 -0.0011 0.5288 0.9668
1.500 0.4185 0.02247 0.01390 -0.0038 0.5164 0.9753
1.750 0.4569 0.02229 0.01370 -0.0064 0.5037 0.9840
2.000 0.4979 0.02197 0.01326 -0.0094 0.4927 0.9921
2.250 0.5396 0.02161 0.01283 -0.0127 0.4809 0.9994
2.500 0.5619 0.02171 0.01294 -0.0125 0.4709 1.0000
2.750 0.5822 0.02174 0.01288 -0.0117 0.4628 1.0000
3.000 0.6028 0.02195 0.01313 -0.0111 0.4534 1.0000
3.250 0.6233 0.02203 0.01312 -0.0103 0.4454 1.0000
3.500 0.6439 0.02230 0.01342 -0.0097 0.4366 1.0000
3.750 0.6646 0.02244 0.01353 -0.0088 0.4287 1.0000
4.000 0.6852 0.02273 0.01382 -0.0081 0.4208 1.0000
4.250 0.7057 0.02297 0.01407 -0.0074 0.4126 1.0000
4.500 0.7267 0.02322 0.01422 -0.0065 0.4063 1.0000
4.750 0.7464 0.02365 0.01480 -0.0058 0.3977 1.0000
5.000 0.7677 0.02380 0.01483 -0.0049 0.3915 1.0000
5.250 0.7866 0.02437 0.01556 -0.0041 0.3835 1.0000
5.500 0.8069 0.02465 0.01583 -0.0032 0.3768 1.0000
5.750 0.8270 0.02510 0.01626 -0.0023 0.3709 1.0000
6.000 0.8445 0.02570 0.01701 -0.0012 0.3633 1.0000
6.250 0.8653 0.02595 0.01717 -0.0002 0.3577 1.0000
6.500 0.8816 0.02673 0.01810 0.0010 0.3511 1.0000
6.750 0.8988 0.02731 0.01876 0.0022 0.3447 1.0000
7.000 0.9202 0.02758 0.01890 0.0033 0.3398 1.0000
7.250 0.9317 0.02864 0.02022 0.0049 0.3330 1.0000
7.500 0.9480 0.02920 0.02083 0.0063 0.3271 1.0000
7.750 0.9699 0.02949 0.02097 0.0074 0.3226 1.0000
8.000 0.9756 0.03082 0.02262 0.0096 0.3164 1.0000
8.250 0.9895 0.03146 0.02332 0.0114 0.3107 1.0000
8.500 1.0121 0.03166 0.02339 0.0125 0.3062 1.0000
8.750 1.0122 0.03322 0.02524 0.0154 0.3008 1.0000
9.000 1.0201 0.03411 0.02625 0.0178 0.2952 1.0000
9.250 1.0429 0.03421 0.02624 0.0189 0.2906 1.0000
9.500 1.0432 0.03563 0.02784 0.0219 0.2859 1.0000
9.750 1.0375 0.03712 0.02953 0.0256 0.2807 1.0000
10.000 1.0582 0.03724 0.02961 0.0269 0.2757 1.0000
10.250 1.0743 0.03792 0.03025 0.0285 0.2712 1.0000
10.500 1.0460 0.04053 0.03317 0.0338 0.2668 1.0000
10.750 1.0507 0.04152 0.03423 0.0361 0.2619 1.0000
11.000 1.1097 0.04025 0.03268 0.0341 0.2564 1.0000
11.250 1.0561 0.04425 0.03708 0.0404 0.2532 1.0000
11.500 0.5031 0.11934 0.11233 0.0130 0.2918 1.0000
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Polar data table (+)
Polar graphs
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